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source: palm/trunk/SOURCE/wind_turbine_model_mod.f90 @ 2060

Last change on this file since 2060 was 2016, checked in by lvollmer, 8 years ago
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[1820]	1	!> @file wind_turbine_model_mod.f90
[1912]	2	!------------------------------------------------------------------------------!
[1819]	3	! This file is part of PALM.
	4	!
[2000]	5	! PALM is free software: you can redistribute it and/or modify it under the
	6	! terms of the GNU General Public License as published by the Free Software
	7	! Foundation, either version 3 of the License, or (at your option) any later
	8	! version.
[1819]	9	!
	10	! PALM is distributed in the hope that it will be useful, but WITHOUT ANY
	11	! WARRANTY; without even the implied warranty of MERCHANTABILITY or FITNESS FOR
	12	! A PARTICULAR PURPOSE. See the GNU General Public License for more details.
	13	!
	14	! You should have received a copy of the GNU General Public License along with
	15	! PALM. If not, see <http://www.gnu.org/licenses/>.
	16	!
	17	! Copyright 1997-2016 Leibniz Universitaet Hannover
[1912]	18	!------------------------------------------------------------------------------!
[1819]	19	!
	20	! Current revisions:
	21	! -----------------
[1913]	22	!
[2016]	23	!
[1913]	24	! Former revisions:
	25	! -----------------
	26	! $Id: wind_turbine_model_mod.f90 2016 2016-09-28 08:51:19Z maronga $
[1844]	27	!
[2016]	28	! 2015 2016-09-28 08:45:18Z lvollmer
	29	! Bugfix of pitch control
	30	!
[2001]	31	! 2000 2016-08-20 18:09:15Z knoop
	32	! Forced header and separation lines into 80 columns
	33	!
[1930]	34	! 1929 2016-06-09 16:25:25Z suehring
	35	! Bugfix: added preprocessor directives for parallel and serial mode
	36	!
[1917]	37	! 1914 2016-05-26 14:44:07Z witha
[1821]	38	! Initial revision
	39	!
[1819]	40	!
	41	! Description:
	42	! ------------
	43	!> This module calculates the effect of wind turbines on the flow fields. The
	44	!> initial version contains only the advanced actuator disk with rotation method
	45	!> (ADM-R).
	46	!> The wind turbines include the tower effect, can be yawed and tilted.
	47	!> The wind turbine model includes controllers for rotational speed, pitch and
	48	!> yaw.
	49	!> Currently some specifications of the NREL 5 MW reference turbine
	50	!> are hardcoded whereas most input data comes from separate files (currently
	51	!> external, planned to be included as namelist which will be read in
	52	!> automatically).
	53	!>
	54	!> @todo Revise code according to PALM Coding Standard
	55	!> @todo Implement ADM and ALM turbine models
	56	!> @todo Generate header information
[1917]	57	!> @todo Implement further parameter checks and error messages
[1819]	58	!> @todo Revise and add code documentation
	59	!> @todo Output turbine parameters as timeseries
	60	!> @todo Include additional output variables
[1864]	61	!> @todo Revise smearing the forces for turbines in yaw
	62	!> @todo Revise nacelle and tower parameterization
	63	!> @todo Allow different turbine types in one simulation
[1819]	64	!
	65	!------------------------------------------------------------------------------!
	66	MODULE wind_turbine_model_mod
	67
	68	USE arrays_3d, &
	69	ONLY: dd2zu, tend, u, v, w, zu, zw
	70
	71	USE constants
	72
	73	USE control_parameters, &
	74	ONLY: dt_3d, dz, message_string, simulated_time
	75
	76	USE cpulog, &
	77	ONLY: cpu_log, log_point_s
	78
	79	USE grid_variables, &
	80	ONLY: ddx, dx, ddy, dy
	81
	82	USE indices, &
	83	ONLY: nbgp, nx, nxl, nxlg, nxr, nxrg, ny, nyn, nyng, nys, nysg, nz, &
	84	nzb, nzb_u_inner, nzb_v_inner, nzb_w_inner, nzt
	85
	86	USE kinds
	87
	88	USE pegrid
	89
	90
	91	IMPLICIT NONE
	92
[1864]	93	PRIVATE
[1819]	94
[1839]	95	LOGICAL :: wind_turbine=.FALSE. !< switch for use of wind turbine model
[1819]	96
	97	!
	98	!-- Variables specified in the namelist wind_turbine_par
	99
[1864]	100	INTEGER(iwp) :: nairfoils = 8 !< number of airfoils of the used turbine model (for ADM-R and ALM)
[1839]	101	INTEGER(iwp) :: nturbines = 1 !< number of turbines
[1819]	102
[1839]	103	LOGICAL :: pitch_control = .FALSE. !< switch for use of pitch controller
	104	LOGICAL :: speed_control = .FALSE. !< switch for use of speed controller
	105	LOGICAL :: yaw_control = .FALSE. !< switch for use of yaw controller
[1819]	106
[1839]	107	REAL(wp) :: segment_length = 1.0_wp !< length of the segments, the rotor area is divided into
	108	!< (in tangential direction, as factor of MIN(dx,dy,dz))
	109	REAL(wp) :: segment_width = 0.5_wp !< width of the segments, the rotor area is divided into
	110	!< (in radial direction, as factor of MIN(dx,dy,dz))
	111	REAL(wp) :: time_turbine_on = 0.0_wp !< time at which turbines are started
	112	REAL(wp) :: tilt = 0.0_wp !< vertical tilt of the rotor [degree] ( positive = backwards )
[1819]	113
[1912]	114	REAL(wp), DIMENSION(1:100) :: dtow = 0.0_wp !< tower diameter [m]
	115	REAL(wp), DIMENSION(1:100) :: omega_rot = 0.0_wp !< inital or constant rotor speed [rad/s]
	116	REAL(wp), DIMENSION(1:100) :: phi_yaw = 0.0_wp !< yaw angle [degree] ( clockwise, 0 = facing west )
	117	REAL(wp), DIMENSION(1:100) :: pitch_add = 0.0_wp !< constant pitch angle
	118	REAL(wp), DIMENSION(1:100) :: rcx = 9999999.9_wp !< position of hub in x-direction
	119	REAL(wp), DIMENSION(1:100) :: rcy = 9999999.9_wp !< position of hub in y-direction
	120	REAL(wp), DIMENSION(1:100) :: rcz = 9999999.9_wp !< position of hub in z-direction
	121	REAL(wp), DIMENSION(1:100) :: rnac = 0.0_wp !< nacelle diameter [m]
	122	REAL(wp), DIMENSION(1:100) :: rr = 63.0_wp !< rotor radius [m]
	123	REAL(wp), DIMENSION(1:100) :: turb_cd_nacelle = 0.85_wp !< drag coefficient for nacelle
	124	REAL(wp), DIMENSION(1:100) :: turb_cd_tower = 1.2_wp !< drag coefficient for tower
[1839]	125
[1819]	126	!
	127	!-- Variables specified in the namelist for speed controller
	128	!-- Default values are from the NREL 5MW research turbine (Jonkman, 2008)
	129
[1912]	130	REAL(wp) :: rated_power = 5296610.0_wp !< rated turbine power [W]
[1839]	131	REAL(wp) :: gear_ratio = 97.0_wp !< Gear ratio from rotor to generator
	132	REAL(wp) :: inertia_rot = 34784179.0_wp !< Inertia of the rotor [kg/m2]
	133	REAL(wp) :: inertia_gen = 534.116_wp !< Inertia of the generator [kg/m2]
	134	REAL(wp) :: gen_eff = 0.944_wp !< Electric efficiency of the generator
	135	REAL(wp) :: gear_eff = 1.0_wp !< Loss between rotor and generator
	136	REAL(wp) :: air_dens = 1.225_wp !< Air density to convert to W [kg/m3]
	137	REAL(wp) :: rated_genspeed = 121.6805_wp !< Rated generator speed [rad/s]
[1912]	138	REAL(wp) :: max_torque_gen = 47402.91_wp !< Maximum of the generator torque [Nm]
[1839]	139	REAL(wp) :: slope2 = 2.332287_wp !< Slope constant for region 2
	140	REAL(wp) :: min_reg2 = 91.21091_wp !< Lower generator speed boundary of region 2 [rad/s]
	141	REAL(wp) :: min_reg15 = 70.16224_wp !< Lower generator speed boundary of region 1.5 [rad/s]
[1912]	142	REAL(wp) :: max_trq_rate = 15000.0_wp !< Max generator torque increase [Nm/s]
	143	REAL(wp) :: pitch_rate = 8.0_wp !< Max pitch rate [degree/s]
[1839]	144
[1912]	145
[1819]	146	!
	147	!-- Variables specified in the namelist for yaw control
	148
[1839]	149	REAL(wp) :: yaw_speed = 0.005236_wp !< speed of the yaw actuator [rad/s]
	150	REAL(wp) :: max_miss = 0.08726_wp !< maximum tolerated yaw missalignment [rad]
	151	REAL(wp) :: min_miss = 0.008726_wp !< minimum yaw missalignment for which the actuator stops [rad]
	152
[1819]	153	!
	154	!-- Set flag for output files TURBINE_PARAMETERS
	155	TYPE file_status
	156	LOGICAL :: opened, opened_before
	157	END TYPE file_status
	158
[1912]	159	TYPE(file_status), DIMENSION(500) :: openfile_turb_mod = &
	160	file_status(.FALSE.,.FALSE.)
[1819]	161
	162	!
	163	!-- Variables for initialization of the turbine model
	164
[1839]	165	INTEGER(iwp) :: inot !< turbine loop index (turbine id)
	166	INTEGER(iwp) :: nsegs_max !< maximum number of segments (all turbines, required for allocation of arrays)
	167	INTEGER(iwp) :: nrings_max !< maximum number of rings (all turbines, required for allocation of arrays)
	168	INTEGER(iwp) :: ring !< ring loop index (ring number)
	169	INTEGER(iwp) :: rr_int !<
	170	INTEGER(iwp) :: upper_end !<
[1819]	171
[1839]	172	INTEGER(iwp), DIMENSION(1) :: lct !<
[1819]	173
[1912]	174	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: i_hub !< index belonging to x-position of the turbine
	175	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: i_smear !< index defining the area for the smearing of the forces (x-direction)
	176	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: j_hub !< index belonging to y-position of the turbine
	177	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: j_smear !< index defining the area for the smearing of the forces (y-direction)
	178	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: k_hub !< index belonging to hub height
	179	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: k_smear !< index defining the area for the smearing of the forces (z-direction)
	180	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: nrings !< number of rings per turbine
	181	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: nsegs_total !< total number of segments per turbine
[1819]	182
[1912]	183	INTEGER(iwp), DIMENSION(:,:), ALLOCATABLE :: nsegs !< number of segments per ring and turbine
[1819]	184
[1912]	185	!
	186	!- parameters for the smearing from the rotor to the cartesian grid
[1864]	187	REAL(wp) :: pol_a !< parameter for the polynomial smearing fct
	188	REAL(wp) :: pol_b !< parameter for the polynomial smearing fct
[1912]	189	REAL(wp) :: delta_t_factor !<
[1864]	190	REAL(wp) :: eps_factor !<
[1839]	191	REAL(wp) :: eps_min !<
	192	REAL(wp) :: eps_min2 !<
	193	REAL(wp) :: sqrt_arg !<
[1819]	194
[1839]	195	!
	196	!-- Variables for the calculation of lift and drag coefficients
[1912]	197	REAL(wp), DIMENSION(:), ALLOCATABLE :: ard !<
	198	REAL(wp), DIMENSION(:), ALLOCATABLE :: crd !<
	199	REAL(wp), DIMENSION(:), ALLOCATABLE :: delta_r !< radial segment length
	200	REAL(wp), DIMENSION(:), ALLOCATABLE :: lrd !<
[1864]	201
[1912]	202	REAL(wp) :: accu_cl_cd_tab = 0.1_wp !< Accuracy of the interpolation of
	203	!< the lift and drag coeff [deg]
[1819]	204
[1912]	205	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: turb_cd_tab !< table of the blade drag coefficient
	206	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: turb_cl_tab !< table of the blade lift coefficient
[1819]	207
[1912]	208	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: nac_cd_surf !< 3d field of the tower drag coefficient
	209	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: tow_cd_surf !< 3d field of the nacelle drag coefficient
[1819]	210
	211	!
	212	!-- Variables for the calculation of the forces
[1912]	213
[1839]	214	REAL(wp) :: cur_r !<
[1912]	215	REAL(wp) :: delta_t !< tangential segment length
[1839]	216	REAL(wp) :: phi_rotor !<
	217	REAL(wp) :: pre_factor !<
	218	REAL(wp) :: torque_seg !<
	219	REAL(wp) :: u_int_l !<
	220	REAL(wp) :: u_int_u !<
	221	REAL(wp) :: u_rot !<
	222	REAL(wp) :: v_int_l !<
	223	REAL(wp) :: v_int_u !<
	224	REAL(wp) :: w_int_l !<
	225	REAL(wp) :: w_int_u !<
[1912]	226	!
	227	!- Tendencies from the nacelle and tower thrust
	228	REAL(wp) :: tend_nac_x = 0.0_wp !<
	229	REAL(wp) :: tend_tow_x = 0.0_wp !<
	230	REAL(wp) :: tend_nac_y = 0.0_wp !<
	231	REAL(wp) :: tend_tow_y = 0.0_wp !<
[1819]	232
[1912]	233	REAL(wp), DIMENSION(:), ALLOCATABLE :: alpha_attack !<
	234	REAL(wp), DIMENSION(:), ALLOCATABLE :: chord !<
	235	REAL(wp), DIMENSION(:), ALLOCATABLE :: omega_gen !< curr. generator speed
	236	REAL(wp), DIMENSION(:), ALLOCATABLE :: phi_rel !<
	237	REAL(wp), DIMENSION(:), ALLOCATABLE :: pitch_add_old!<
	238	REAL(wp), DIMENSION(:), ALLOCATABLE :: torque_total !<
	239	REAL(wp), DIMENSION(:), ALLOCATABLE :: thrust_rotor !<
	240	REAL(wp), DIMENSION(:), ALLOCATABLE :: turb_cl !<
	241	REAL(wp), DIMENSION(:), ALLOCATABLE :: turb_cd !<
	242	REAL(wp), DIMENSION(:), ALLOCATABLE :: vrel !<
	243	REAL(wp), DIMENSION(:), ALLOCATABLE :: vtheta !<
	244
	245	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: rbx, rby, rbz !< coordinates of the blade elements
	246	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: rotx, roty, rotz !< normal vectors to the rotor coordinates
	247
	248	!
	249	!- Fields for the interpolation of velocities on the rotor grid
	250	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: u_int !<
	251	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: u_int_1_l !<
	252	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: v_int !<
	253	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: v_int_1_l !<
	254	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: w_int !<
	255	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: w_int_1_l !<
	256
	257	!
	258	!- rotor tendencies on the segments
	259	REAL(wp), DIMENSION(:), ALLOCATABLE :: thrust_seg !<
	260	REAL(wp), DIMENSION(:), ALLOCATABLE :: torque_seg_y !<
	261	REAL(wp), DIMENSION(:), ALLOCATABLE :: torque_seg_z !<
	262
	263	!
	264	!- rotor tendencies on the rings
	265	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: thrust_ring !<
	266	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: torque_ring_y !<
	267	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: torque_ring_z !<
	268
	269	!
	270	!- rotor tendencies on rotor grids for all turbines
	271	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: thrust !<
	272	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: torque_y !<
	273	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: torque_z !<
	274
	275	!
	276	!- rotor tendencies on coordinate grid
	277	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: rot_tend_x !<
	278	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: rot_tend_y !<
	279	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: rot_tend_z !<
	280	!
	281	!- variables for the rotation of the rotor coordinates
	282	REAL(wp), DIMENSION(1:100,1:3,1:3) :: rot_coord_trans !< matrix for rotation of rotor coordinates
	283
[1839]	284	REAL(wp), DIMENSION(1:3) :: rot_eigen_rad !<
	285	REAL(wp), DIMENSION(1:3) :: rot_eigen_azi !<
	286	REAL(wp), DIMENSION(1:3) :: rot_eigen_nor !<
	287	REAL(wp), DIMENSION(1:3) :: re !<
	288	REAL(wp), DIMENSION(1:3) :: rea !<
	289	REAL(wp), DIMENSION(1:3) :: ren !<
	290	REAL(wp), DIMENSION(1:3) :: rote !<
	291	REAL(wp), DIMENSION(1:3) :: rota !<
	292	REAL(wp), DIMENSION(1:3) :: rotn !<
[1819]	293
[1839]	294	!
	295	!-- Fixed variables for the speed controller
[1819]	296
[1912]	297	LOGICAL :: start_up = .TRUE. !<
[1864]	298
[1912]	299	REAL(wp) :: Fcorner !< corner freq for the controller low pass filter
	300	REAL(wp) :: min_reg25 !< min region 2.5
	301	REAL(wp) :: om_rate !< rotor speed change
	302	REAL(wp) :: slope15 !< slope in region 1.5
	303	REAL(wp) :: slope25 !< slope in region 2.5
	304	REAL(wp) :: trq_rate !< torque change
	305	REAL(wp) :: vs_sysp !<
	306	REAL(wp) :: lp_coeff !< coeff for the controller low pass filter
[1864]	307
	308	REAL(wp), DIMENSION(:), ALLOCATABLE :: omega_gen_old !< last gen. speed
	309	REAL(wp), DIMENSION(:), ALLOCATABLE :: omega_gen_f !< filtered gen. sp
	310	REAL(wp), DIMENSION(:), ALLOCATABLE :: omega_gen_f_old !< last filt. gen. sp
	311	REAL(wp), DIMENSION(:), ALLOCATABLE :: torque_gen !< generator torque
	312	REAL(wp), DIMENSION(:), ALLOCATABLE :: torque_gen_old !< last gen. torque
[1819]	313
[1864]	314	REAL(wp), DIMENSION(100) :: omega_rot_l = 0.0_wp !< local rot speed [rad/s]
[1839]	315	!
	316	!-- Fixed variables for the yaw controller
[1819]	317
[1912]	318	REAL(wp), DIMENSION(:) , ALLOCATABLE :: yawdir !< direction to yaw
	319	REAL(wp), DIMENSION(:) , ALLOCATABLE :: phi_yaw_l !< local (cpu) yaw angle
	320	REAL(wp), DIMENSION(:) , ALLOCATABLE :: wd30_l !< local (cpu) long running avg of the wd
	321	REAL(wp), DIMENSION(:) , ALLOCATABLE :: wd2_l !< local (cpu) short running avg of the wd
	322	REAL(wp), DIMENSION(:) , ALLOCATABLE :: wdir !< wind direction at hub
	323	REAL(wp), DIMENSION(:) , ALLOCATABLE :: u_inflow !< wind speed at hub
	324	REAL(wp), DIMENSION(:) , ALLOCATABLE :: wdir_l !<
	325	REAL(wp), DIMENSION(:) , ALLOCATABLE :: u_inflow_l !<
	326	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: wd30 !<
	327	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: wd2 !<
	328	LOGICAL, DIMENSION(1:100) :: doyaw = .FALSE. !<
	329	INTEGER(iwp) :: WDLON !<
	330	INTEGER(iwp) :: WDSHO !<
[1819]	331
	332
[1839]	333	SAVE
[1819]	334
[1839]	335
	336	INTERFACE wtm_parin
	337	MODULE PROCEDURE wtm_parin
	338	END INTERFACE wtm_parin
[1912]	339
	340	INTERFACE wtm_check_parameters
	341	MODULE PROCEDURE wtm_check_parameters
	342	END INTERFACE wtm_check_parameters
[1839]	343
	344	INTERFACE wtm_init_arrays
	345	MODULE PROCEDURE wtm_init_arrays
	346	END INTERFACE wtm_init_arrays
	347
	348	INTERFACE wtm_init
	349	MODULE PROCEDURE wtm_init
	350	END INTERFACE wtm_init
	351
[1912]	352	INTERFACE wtm_read_blade_tables
	353	MODULE PROCEDURE wtm_read_blade_tables
	354	END INTERFACE wtm_read_blade_tables
[1839]	355
[1819]	356	INTERFACE wtm_forces
	357	MODULE PROCEDURE wtm_forces
[1839]	358	MODULE PROCEDURE wtm_yawcontrol
[1819]	359	END INTERFACE wtm_forces
[1864]	360
	361	INTERFACE wtm_rotate_rotor
	362	MODULE PROCEDURE wtm_rotate_rotor
	363	END INTERFACE wtm_rotate_rotor
	364
	365	INTERFACE wtm_speed_control
	366	MODULE PROCEDURE wtm_init_speed_control
	367	MODULE PROCEDURE wtm_speed_control
	368	END INTERFACE wtm_speed_control
[1819]	369
	370	INTERFACE wtm_tendencies
	371	MODULE PROCEDURE wtm_tendencies
	372	MODULE PROCEDURE wtm_tendencies_ij
	373	END INTERFACE wtm_tendencies
[1864]	374
	375
[1912]	376	PUBLIC wtm_check_parameters, wtm_forces, wtm_init, wtm_init_arrays, &
	377	wtm_parin, wtm_tendencies, wtm_tendencies_ij, wind_turbine
[1819]	378
	379	CONTAINS
	380
	381
	382	!------------------------------------------------------------------------------!
	383	! Description:
	384	! ------------
[1839]	385	!> Parin for &wind_turbine_par for wind turbine model
[1819]	386	!------------------------------------------------------------------------------!
[1839]	387	SUBROUTINE wtm_parin
[1819]	388
	389
	390	IMPLICIT NONE
[1912]	391
	392	INTEGER(iwp) :: ierrn !<
[1819]	393
[1839]	394	CHARACTER (LEN=80) :: line !< dummy string that contains the current line of the parameter file
	395
	396	NAMELIST /wind_turbine_par/ air_dens, dtow, gear_eff, gear_ratio, &
[1864]	397	gen_eff, inertia_gen, inertia_rot, max_miss, &
[1839]	398	max_torque_gen, max_trq_rate, min_miss, &
[1864]	399	min_reg15, min_reg2, nairfoils, nturbines, &
[1912]	400	omega_rot, phi_yaw, pitch_add, pitch_control,&
[1839]	401	rated_genspeed, rated_power, rcx, rcy, rcz, &
	402	rnac, rr, segment_length, segment_width, &
[1864]	403	slope2, speed_control, tilt, time_turbine_on,&
[1912]	404	turb_cd_nacelle, turb_cd_tower, &
[1839]	405	yaw_control, yaw_speed
	406
[1819]	407	!
[1839]	408	!-- Try to find wind turbine model package
	409	REWIND ( 11 )
	410	line = ' '
	411	DO WHILE ( INDEX( line, '&wind_turbine_par' ) == 0 )
	412	READ ( 11, '(A)', END=10 ) line
	413	ENDDO
	414	BACKSPACE ( 11 )
	415
	416	!
	417	!-- Read user-defined namelist
[1912]	418	READ ( 11, wind_turbine_par, IOSTAT=ierrn )
	419
	420	IF ( ierrn < 0 ) THEN
	421	message_string = 'errors in \$wind_turbine_par'
	422	CALL message( 'wtm_parin', 'PA0???', 1, 2, 0, 6, 0 )
	423	ENDIF
	424
[1839]	425	!
	426	!-- Set flag that indicates that the wind turbine model is switched on
	427	wind_turbine = .TRUE.
	428
[1912]	429	10 CONTINUE ! TBD Change from continue, mit ierrn machen
[1839]	430
	431
	432	END SUBROUTINE wtm_parin
	433
[1912]	434	SUBROUTINE wtm_check_parameters
	435
	436
	437	IMPLICIT NONE
	438
	439	IF ( ( .NOT.speed_control ) .AND. pitch_control ) THEN
	440	message_string = 'pitch_control = .TRUE. requires '// &
	441	'speed_control = .TRUE.'
	442	CALL message( 'wtm_check_parameters', 'PA0???', 1, 2, 0, 6, 0 )
	443	ENDIF
	444
	445	IF ( ANY( omega_rot(1:nturbines) <= 0.0 ) ) THEN
	446	message_string = 'omega_rot <= 0.0, Please set omega_rot to ' // &
	447	'a value larger than zero'
	448	CALL message( 'wtm_check_parameters', 'PA0???', 1, 2, 0, 6, 0 )
	449	ENDIF
	450
	451
	452	IF ( ANY( rcx(1:nturbines) == 9999999.9_wp ) .OR. &
	453	ANY( rcy(1:nturbines) == 9999999.9_wp ) .OR. &
	454	ANY( rcz(1:nturbines) == 9999999.9_wp ) ) THEN
	455
	456	message_string = 'rcx, rcy, rcz ' // &
	457	'have to be given for each turbine.'
	458	CALL message( 'wtm_check_parameters', 'PA0???', 1, 2, 0, 6, 0 )
	459
	460	ENDIF
	461
	462
	463	END SUBROUTINE wtm_check_parameters
	464
	465
[1839]	466	!------------------------------------------------------------------------------!
	467	! Description:
	468	! ------------
	469	!> Allocate wind turbine model arrays
	470	!------------------------------------------------------------------------------!
	471	SUBROUTINE wtm_init_arrays
	472
	473
	474	IMPLICIT NONE
	475
[1864]	476	REAL(wp) :: delta_r_factor !<
	477	REAL(wp) :: delta_r_init !<
	478
[1839]	479	!
	480	!-- To be able to allocate arrays with dimension of rotor rings and segments,
[1819]	481	!-- the maximum possible numbers of rings and segments have to be calculated:
	482
	483	ALLOCATE( nrings(1:nturbines) )
	484	ALLOCATE( delta_r(1:nturbines) )
	485
	486	nrings(:) = 0
	487	delta_r(:) = 0.0_wp
	488
	489	!
	490	!-- Thickness (radial) of each ring and length (tangential) of each segment:
	491	delta_r_factor = segment_width
	492	delta_t_factor = segment_length
	493	delta_r_init = delta_r_factor * MIN( dx, dy, dz)
	494	delta_t = delta_t_factor * MIN( dx, dy, dz)
	495
	496	DO inot = 1, nturbines
	497	!
	498	!-- Determine number of rings:
	499	nrings(inot) = NINT( rr(inot) / delta_r_init )
	500
	501	delta_r(inot) = rr(inot) / nrings(inot)
	502
	503	ENDDO
	504
	505	nrings_max = MAXVAL(nrings)
	506
	507	ALLOCATE( nsegs(1:nrings_max,1:nturbines) )
	508	ALLOCATE( nsegs_total(1:nturbines) )
	509
	510	nsegs(:,:) = 0
	511	nsegs_total(:) = 0
	512
	513
	514	DO inot = 1, nturbines
	515	DO ring = 1, nrings(inot)
	516	!
	517	!-- Determine number of segments for each ring:
[1839]	518	nsegs(ring,inot) = MAX( 8, CEILING( delta_r_factor * pi * &
	519	( 2.0_wp * ring - 1.0_wp ) / &
	520	delta_t_factor ) )
[1819]	521	ENDDO
	522	!
	523	!-- Total sum of all rotor segments:
[1839]	524	nsegs_total(inot) = SUM( nsegs(:,inot) )
[1819]	525
	526	ENDDO
	527
	528	!
	529	!-- Maximum number of segments per ring:
	530	nsegs_max = MAXVAL(nsegs)
	531
[1864]	532	!!
	533	!!-- TODO: Folgendes im Header ausgeben!
	534	! IF ( myid == 0 ) THEN
	535	! PRINT*, 'nrings(1) = ', nrings(1)
	536	! PRINT*, '--------------------------------------------------'
	537	! PRINT*, 'nsegs(:,1) = ', nsegs(:,1)
	538	! PRINT*, '--------------------------------------------------'
	539	! PRINT*, 'nrings_max = ', nrings_max
	540	! PRINT*, 'nsegs_max = ', nsegs_max
	541	! PRINT*, 'nsegs_total(1) = ', nsegs_total(1)
	542	! ENDIF
[1819]	543
	544
	545	!
	546	!-- Allocate 1D arrays (dimension = number of turbines)
	547	ALLOCATE( i_hub(1:nturbines) )
	548	ALLOCATE( i_smear(1:nturbines) )
	549	ALLOCATE( j_hub(1:nturbines) )
	550	ALLOCATE( j_smear(1:nturbines) )
	551	ALLOCATE( k_hub(1:nturbines) )
	552	ALLOCATE( k_smear(1:nturbines) )
	553	ALLOCATE( torque_total(1:nturbines) )
[1912]	554	ALLOCATE( thrust_rotor(1:nturbines) )
[1819]	555
	556	!
	557	!-- Allocation of the 1D arrays for speed pitch_control
	558	ALLOCATE( omega_gen(1:nturbines) )
[1864]	559	ALLOCATE( omega_gen_old(1:nturbines) )
[1819]	560	ALLOCATE( omega_gen_f(1:nturbines) )
	561	ALLOCATE( omega_gen_f_old(1:nturbines) )
[1912]	562	ALLOCATE( pitch_add_old(1:nturbines) )
[1819]	563	ALLOCATE( torque_gen(1:nturbines) )
	564	ALLOCATE( torque_gen_old(1:nturbines) )
	565
	566	!
	567	!-- Allocation of the 1D arrays for yaw control
	568	ALLOCATE( yawdir(1:nturbines) )
	569	ALLOCATE( u_inflow(1:nturbines) )
	570	ALLOCATE( wdir(1:nturbines) )
	571	ALLOCATE( u_inflow_l(1:nturbines) )
	572	ALLOCATE( wdir_l(1:nturbines) )
	573	ALLOCATE( phi_yaw_l(1:nturbines) )
	574
	575	!
	576	!-- Allocate 1D arrays (dimension = number of rotor segments)
	577	ALLOCATE( alpha_attack(1:nsegs_max) )
	578	ALLOCATE( chord(1:nsegs_max) )
	579	ALLOCATE( phi_rel(1:nsegs_max) )
	580	ALLOCATE( thrust_seg(1:nsegs_max) )
	581	ALLOCATE( torque_seg_y(1:nsegs_max) )
	582	ALLOCATE( torque_seg_z(1:nsegs_max) )
[1839]	583	ALLOCATE( turb_cd(1:nsegs_max) )
	584	ALLOCATE( turb_cl(1:nsegs_max) )
[1819]	585	ALLOCATE( vrel(1:nsegs_max) )
	586	ALLOCATE( vtheta(1:nsegs_max) )
	587
	588	!
	589	!-- Allocate 2D arrays (dimension = number of rotor rings and segments)
	590	ALLOCATE( rbx(1:nrings_max,1:nsegs_max) )
	591	ALLOCATE( rby(1:nrings_max,1:nsegs_max) )
	592	ALLOCATE( rbz(1:nrings_max,1:nsegs_max) )
	593	ALLOCATE( thrust_ring(1:nrings_max,1:nsegs_max) )
	594	ALLOCATE( torque_ring_y(1:nrings_max,1:nsegs_max) )
	595	ALLOCATE( torque_ring_z(1:nrings_max,1:nsegs_max) )
	596
	597	!
	598	!-- Allocate additional 2D arrays
	599	ALLOCATE( rotx(1:nturbines,1:3) )
	600	ALLOCATE( roty(1:nturbines,1:3) )
	601	ALLOCATE( rotz(1:nturbines,1:3) )
	602
	603	!
	604	!-- Allocate 3D arrays (dimension = number of grid points)
[1912]	605	ALLOCATE( nac_cd_surf(nzb:nzt+1,nysg:nyng,nxlg:nxrg) )
	606	ALLOCATE( rot_tend_x(nzb:nzt+1,nysg:nyng,nxlg:nxrg) )
	607	ALLOCATE( rot_tend_y(nzb:nzt+1,nysg:nyng,nxlg:nxrg) )
	608	ALLOCATE( rot_tend_z(nzb:nzt+1,nysg:nyng,nxlg:nxrg) )
[1819]	609	ALLOCATE( thrust(nzb:nzt+1,nysg:nyng,nxlg:nxrg) )
	610	ALLOCATE( torque_y(nzb:nzt+1,nysg:nyng,nxlg:nxrg) )
	611	ALLOCATE( torque_z(nzb:nzt+1,nysg:nyng,nxlg:nxrg) )
[1912]	612	ALLOCATE( tow_cd_surf(nzb:nzt+1,nysg:nyng,nxlg:nxrg) )
[1819]	613
	614	!
	615	!-- Allocate additional 3D arrays
	616	ALLOCATE( u_int(1:nturbines,1:nrings_max,1:nsegs_max) )
	617	ALLOCATE( u_int_1_l(1:nturbines,1:nrings_max,1:nsegs_max) )
	618	ALLOCATE( v_int(1:nturbines,1:nrings_max,1:nsegs_max) )
	619	ALLOCATE( v_int_1_l(1:nturbines,1:nrings_max,1:nsegs_max) )
	620	ALLOCATE( w_int(1:nturbines,1:nrings_max,1:nsegs_max) )
	621	ALLOCATE( w_int_1_l(1:nturbines,1:nrings_max,1:nsegs_max) )
	622
	623	!
	624	!-- All of the arrays are initialized with a value of zero:
	625	i_hub(:) = 0
	626	i_smear(:) = 0
	627	j_hub(:) = 0
	628	j_smear(:) = 0
	629	k_hub(:) = 0
	630	k_smear(:) = 0
[1912]	631
[1819]	632	torque_total(:) = 0.0_wp
[1912]	633	thrust_rotor(:) = 0.0_wp
[1819]	634
	635	omega_gen(:) = 0.0_wp
[1864]	636	omega_gen_old(:) = 0.0_wp
[1819]	637	omega_gen_f(:) = 0.0_wp
	638	omega_gen_f_old(:) = 0.0_wp
[1912]	639	pitch_add_old(:) = 0.0_wp
[1819]	640	torque_gen(:) = 0.0_wp
	641	torque_gen_old(:) = 0.0_wp
	642
	643	yawdir(:) = 0.0_wp
	644	wdir(:) = 0.0_wp
	645	u_inflow(:) = 0.0_wp
	646
	647	!
	648	!-- Allocate 1D arrays (dimension = number of rotor segments)
	649	alpha_attack(:) = 0.0_wp
	650	chord(:) = 0.0_wp
	651	phi_rel(:) = 0.0_wp
	652	thrust_seg(:) = 0.0_wp
	653	torque_seg_y(:) = 0.0_wp
	654	torque_seg_z(:) = 0.0_wp
[1864]	655	turb_cd(:) = 0.0_wp
	656	turb_cl(:) = 0.0_wp
[1819]	657	vrel(:) = 0.0_wp
	658	vtheta(:) = 0.0_wp
	659
	660	rbx(:,:) = 0.0_wp
	661	rby(:,:) = 0.0_wp
	662	rbz(:,:) = 0.0_wp
	663	thrust_ring(:,:) = 0.0_wp
	664	torque_ring_y(:,:) = 0.0_wp
	665	torque_ring_z(:,:) = 0.0_wp
	666
	667	rotx(:,:) = 0.0_wp
	668	roty(:,:) = 0.0_wp
	669	rotz(:,:) = 0.0_wp
[1864]	670	turb_cl_tab(:,:) = 0.0_wp
	671	turb_cd_tab(:,:) = 0.0_wp
[1819]	672
[1912]	673	nac_cd_surf(:,:,:) = 0.0_wp
	674	rot_tend_x(:,:,:) = 0.0_wp
	675	rot_tend_y(:,:,:) = 0.0_wp
	676	rot_tend_z(:,:,:) = 0.0_wp
[1819]	677	thrust(:,:,:) = 0.0_wp
	678	torque_y(:,:,:) = 0.0_wp
	679	torque_z(:,:,:) = 0.0_wp
[1912]	680	tow_cd_surf(:,:,:) = 0.0_wp
[1819]	681
	682	u_int(:,:,:) = 0.0_wp
	683	u_int_1_l(:,:,:) = 0.0_wp
	684	v_int(:,:,:) = 0.0_wp
	685	v_int_1_l(:,:,:) = 0.0_wp
	686	w_int(:,:,:) = 0.0_wp
	687	w_int_1_l(:,:,:) = 0.0_wp
	688
	689
[1839]	690	END SUBROUTINE wtm_init_arrays
[1819]	691
	692
	693	!------------------------------------------------------------------------------!
	694	! Description:
	695	! ------------
[1839]	696	!> Initialization of the wind turbine model
[1819]	697	!------------------------------------------------------------------------------!
[1839]	698	SUBROUTINE wtm_init
[1819]	699
[1839]	700
[1819]	701	IMPLICIT NONE
	702
	703	INTEGER(iwp) :: i !< running index
	704	INTEGER(iwp) :: j !< running index
	705	INTEGER(iwp) :: k !< running index
[1864]	706
[1819]	707	!
[1864]	708	!-- Help variables for the smearing function
	709	REAL(wp) :: eps_kernel !<
	710
[1839]	711	!
[1864]	712	!-- Help variables for calculation of the tower drag
	713	INTEGER(iwp) :: tower_n !<
	714	INTEGER(iwp) :: tower_s !<
[1839]	715	!
[1864]	716	!-- Help variables for the calulaction of the nacelle drag
	717	INTEGER(iwp) :: i_ip !<
	718	INTEGER(iwp) :: i_ipg !<
	719
	720	REAL(wp) :: yvalue
	721	REAL(wp) :: dy_int !<
	722	REAL(wp) :: dz_int !<
	723
	724	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: circle_points !<
	725
	726	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: index_nacb !<
	727	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: index_nacl !<
	728	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: index_nacr !<
	729	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: index_nact !<
	730
	731	ALLOCATE( index_nacb(1:nturbines) )
	732	ALLOCATE( index_nacl(1:nturbines) )
	733	ALLOCATE( index_nacr(1:nturbines) )
	734	ALLOCATE( index_nact(1:nturbines) )
[1819]	735
	736
[1864]	737	IF ( speed_control) THEN
	738
	739	CALL wtm_speed_control
	740
	741	ENDIF
	742
[1839]	743	!
[1819]	744	!------------------------------------------------------------------------------!
[1839]	745	!-- Calculation of parameters for the regularization kernel
	746	!-- (smearing of the forces)
[1819]	747	!------------------------------------------------------------------------------!
	748	!
[1839]	749	!-- In the following, some of the required parameters for the smearing will
	750	!-- be calculated:
[1819]	751
[1839]	752	!-- The kernel is set equal to twice the grid spacing which has turned out to
	753	!-- be a reasonable value (see e.g. Troldborg et al. (2013), Wind Energy,
[1819]	754	!-- DOI: 10.1002/we.1608):
	755	eps_kernel = 2.0_wp * dx
	756	!
[1839]	757	!-- The zero point (eps_min) of the polynomial function must be the following
	758	!-- if the integral of the polynomial function (for values < eps_min) shall
	759	!-- be equal to the integral of the Gaussian function used before:
	760	eps_min = ( 105.0_wp / 32.0_wp )*( 1.0_wp / 3.0_wp ) &
	761	pi*( 1.0_wp / 6.0_wp ) eps_kernel
[1819]	762	!
	763	!-- Square of eps_min:
	764	eps_min2 = eps_min**2
	765	!
	766	!-- Parameters in the polynomial function:
[1864]	767	pol_a = 1.0_wp / eps_min**4
	768	pol_b = 2.0_wp / eps_min**2
[1819]	769	!
[1839]	770	!-- Normalization factor which is the inverse of the integral of the smearing
	771	!-- function:
	772	eps_factor = 105.0_wp / ( 32.0_wp * pi * eps_min**3 )
	773
[1864]	774	!-- Change tilt angle to rad:
	775	tilt = tilt * pi / 180.0_wp
	776
[1819]	777	!
[1864]	778	!-- Change yaw angle to rad:
	779	phi_yaw(:) = phi_yaw(:) * pi / 180.0_wp
[1819]	780
[1864]	781
[1819]	782	DO inot = 1, nturbines
	783	!
[1864]	784	!-- Rotate the rotor coordinates in case yaw and tilt are defined
	785	CALL wtm_rotate_rotor( inot )
[1819]	786
	787	!
	788	!-- Determine the indices of the hub height
	789	i_hub(inot) = INT( rcx(inot) / dx )
	790	j_hub(inot) = INT( ( rcy(inot) + 0.5_wp * dy ) / dy )
	791	k_hub(inot) = INT( ( rcz(inot) + 0.5_wp * dz ) / dz )
	792
	793	!
	794	!-- Determining the area to which the smearing of the forces is applied.
[1839]	795	!-- As smearing now is effectively applied only for distances smaller than
	796	!-- eps_min, the smearing area can be further limited and regarded as a
	797	!-- function of eps_min:
[1819]	798	i_smear(inot) = CEILING( ( rr(inot) + eps_min ) / dx )
	799	j_smear(inot) = CEILING( ( rr(inot) + eps_min ) / dy )
	800	k_smear(inot) = CEILING( ( rr(inot) + eps_min ) / dz )
[1864]	801
[1819]	802	ENDDO
	803
	804	!
	805	!------------------------------------------------------------------------------!
[1839]	806	!-- Determine the area within each grid cell that overlaps with the area
	807	!-- of the nacelle and the tower (needed for calculation of the forces)
[1819]	808	!------------------------------------------------------------------------------!
	809	!
	810	!-- Note: so far this is only a 2D version, in that the mean flow is
	811	!-- perpendicular to the rotor area.
	812
	813	!
	814	!-- Allocation of the array containing information on the intersection points
	815	!-- between rotor disk and the numerical grid:
	816	upper_end = ( ny + 1 ) * 10000
	817
	818	ALLOCATE( circle_points(1:2,1:upper_end) )
[1839]	819
	820	circle_points(:,:) = 0.0_wp
[1819]	821
[1839]	822
	823	DO inot = 1, nturbines ! loop over number of turbines
[1819]	824	!
[1839]	825	!-- Determine the grid index (u-grid) that corresponds to the location of
	826	!-- the rotor center (reduces the amount of calculations in the case that
	827	!-- the mean flow is perpendicular to the rotor area):
[1819]	828	i = i_hub(inot)
	829
	830	!
[1839]	831	!-- Determine the left and the right edge of the nacelle (corresponding
	832	!-- grid point indices):
[1819]	833	index_nacl(inot) = INT( ( rcy(inot) - rnac(inot) + 0.5_wp * dy ) / dy )
	834	index_nacr(inot) = INT( ( rcy(inot) + rnac(inot) + 0.5_wp * dy ) / dy )
	835	!
[1839]	836	!-- Determine the bottom and the top edge of the nacelle (corresponding
	837	!-- grid point indices).The grid point index has to be increased by 1, as
	838	!-- the first level for the u-component (index 0) is situated below the
	839	!-- surface. All points between z=0 and z=dz/s would already be contained
	840	!-- in grid box 1.
[1819]	841	index_nacb(inot) = INT( ( rcz(inot) - rnac(inot) ) / dz ) + 1
	842	index_nact(inot) = INT( ( rcz(inot) + rnac(inot) ) / dz ) + 1
	843
	844	!
	845	!-- Determine the indices of the grid boxes containing the left and
[1864]	846	!-- the right boundaries of the tower:
[1819]	847	tower_n = ( rcy(inot) + 0.5_wp * dtow(inot) - 0.5_wp * dy ) / dy
	848	tower_s = ( rcy(inot) - 0.5_wp * dtow(inot) - 0.5_wp * dy ) / dy
	849
	850	!
	851	!-- Determine the fraction of the grid box area overlapping with the tower
[1864]	852	!-- area and multiply it with the drag of the tower:
[1839]	853	IF ( ( nxlg <= i ) .AND. ( nxrg >= i ) ) THEN
[1819]	854
	855	DO j = nys, nyn
	856	!
[1839]	857	!-- Loop from south to north boundary of tower
	858	IF ( ( j >= tower_s ) .AND. ( j <= tower_n ) ) THEN
	859
[1819]	860	DO k = nzb, nzt
	861
	862	IF ( k == k_hub(inot) ) THEN
	863	IF ( tower_n - tower_s >= 1 ) THEN
[1839]	864	!
[1819]	865	!-- leftmost and rightmost grid box:
	866	IF ( j == tower_s ) THEN
[1912]	867	tow_cd_surf(k,j,i) = ( rcz(inot) - &
	868	( k_hub(inot) * dz - 0.5_wp * dz ) ) * & ! extension in z-direction
	869	( ( tower_s + 1.0_wp + 0.5_wp ) * dy - &
	870	( rcy(inot) - 0.5_wp * dtow(inot) ) ) * & ! extension in y-direction
	871	turb_cd_tower(inot)
[1819]	872	ELSEIF ( j == tower_n ) THEN
[1912]	873	tow_cd_surf(k,j,i) = ( rcz(inot) - &
	874	( k_hub(inot) * dz - 0.5_wp * dz ) ) * & ! extension in z-direction
	875	( ( rcy(inot) + 0.5_wp * dtow(inot) ) - &
	876	( tower_n + 0.5_wp ) * dy ) * & ! extension in y-direction
	877	turb_cd_tower(inot)
[1819]	878	!
	879	!-- grid boxes inbetween
[1912]	880	!-- (where tow_cd_surf = grid box area):
[1819]	881	ELSE
[1912]	882	tow_cd_surf(k,j,i) = ( rcz(inot) - &
	883	( k_hub(inot) * dz - 0.5_wp * dz ) ) * &
	884	dy * turb_cd_tower(inot)
[1819]	885	ENDIF
	886	!
	887	!-- tower lies completely within one grid box:
	888	ELSE
[1912]	889	tow_cd_surf(k,j,i) = ( rcz(inot) - &
[1839]	890	( k_hub(inot) * dz - 0.5_wp * dz ) ) * &
[1912]	891	dtow(inot) * turb_cd_tower(inot)
[1819]	892	ENDIF
[1839]	893	!
	894	!-- In case that k is smaller than k_hub the following actions
	895	!-- are carried out:
[1819]	896	ELSEIF ( k < k_hub(inot) ) THEN
	897
[1839]	898	IF ( ( tower_n - tower_s ) >= 1 ) THEN
	899	!
[1819]	900	!-- leftmost and rightmost grid box:
	901	IF ( j == tower_s ) THEN
[1912]	902	tow_cd_surf(k,j,i) = dz * ( &
[1839]	903	( tower_s + 1 + 0.5_wp ) * dy - &
	904	( rcy(inot) - 0.5_wp * dtow(inot) ) &
[1912]	905	) * turb_cd_tower(inot)
[1819]	906	ELSEIF ( j == tower_n ) THEN
[1912]	907	tow_cd_surf(k,j,i) = dz * ( &
[1839]	908	( rcy(inot) + 0.5_wp * dtow(inot) ) - &
	909	( tower_n + 0.5_wp ) * dy &
[1912]	910	) * turb_cd_tower(inot)
[1839]	911	!
	912	!-- grid boxes inbetween
[1912]	913	!-- (where tow_cd_surf = grid box area):
[1819]	914	ELSE
[1912]	915	tow_cd_surf(k,j,i) = dz * dy * turb_cd_tower(inot)
[1819]	916	ENDIF
[1839]	917	!
[1819]	918	!-- tower lies completely within one grid box:
	919	ELSE
[1912]	920	tow_cd_surf(k,j,i) = dz * dtow(inot) * &
	921	turb_cd_tower(inot)
[1839]	922	ENDIF ! end if larger than grid box
	923
	924	ENDIF ! end if k == k_hub
	925
	926	ENDDO ! end loop over k
	927
	928	ENDIF ! end if inside north and south boundary of tower
	929
	930	ENDDO ! end loop over j
	931
	932	ENDIF ! end if hub inside domain + ghostpoints
[1819]	933
[1839]	934
[1912]	935	CALL exchange_horiz( tow_cd_surf, nbgp )
[1819]	936
[1839]	937	!
[1864]	938	!-- Calculation of the nacelle area
	939	!-- CAUTION: Currently disabled due to segmentation faults on the FLOW HPC
	940	!-- cluster (Oldenburg)
	941	!!
	942	!!-- Tabulate the points on the circle that are required in the following for
	943	!!-- the calculation of the Riemann integral (node points; they are called
	944	!!-- circle_points in the following):
	945	!
	946	! dy_int = dy / 10000.0_wp
	947	!
	948	! DO i_ip = 1, upper_end
	949	! yvalue = dy_int * ( i_ip - 0.5_wp ) + 0.5_wp * dy !<--- segmentation fault
	950	! sqrt_arg = rnac(inot)2 - ( yvalue - rcy(inot) )2 !<--- segmentation fault
	951	! IF ( sqrt_arg >= 0.0_wp ) THEN
	952	!!
	953	!!-- bottom intersection point
	954	! circle_points(1,i_ip) = rcz(inot) - SQRT( sqrt_arg )
	955	!!
	956	!!-- top intersection point
	957	! circle_points(2,i_ip) = rcz(inot) + SQRT( sqrt_arg ) !<--- segmentation fault
	958	! ELSE
	959	! circle_points(:,i_ip) = -111111 !<--- segmentation fault
	960	! ENDIF
	961	! ENDDO
	962	!
	963	!
	964	! DO j = nys, nyn
	965	!!
	966	!!-- In case that the grid box is located completely outside the nacelle
	967	!!-- (y) it can automatically be stated that there is no overlap between
	968	!!-- the grid box and the nacelle and consequently we can set
[1912]	969	!!-- nac_cd_surf(:,j,i) = 0.0:
[1864]	970	! IF ( ( j >= index_nacl(inot) ) .AND. ( j <= index_nacr(inot) ) ) THEN
	971	! DO k = nzb+1, nzt
	972	!!
	973	!!-- In case that the grid box is located completely outside the
	974	!!-- nacelle (z) it can automatically be stated that there is no
	975	!!-- overlap between the grid box and the nacelle and consequently
[1912]	976	!!-- we can set nac_cd_surf(k,j,i) = 0.0:
[1864]	977	! IF ( ( k >= index_nacb(inot) ) .OR. &
	978	! ( k <= index_nact(inot) ) ) THEN
	979	!!
	980	!!-- For all other cases Riemann integrals are calculated.
	981	!!-- Here, the points on the circle that have been determined
	982	!!-- above are used in order to calculate the overlap between the
	983	!!-- gridbox and the nacelle area (area approached by 10000
	984	!!-- rectangulars dz_int * dy_int):
	985	! DO i_ipg = 1, 10000
	986	! dz_int = dz
	987	! i_ip = j * 10000 + i_ipg
	988	!!
	989	!!-- Determine the vertical extension dz_int of the circle
	990	!!-- within the current grid box:
	991	! IF ( ( circle_points(2,i_ip) < zw(k) ) .AND. & !<--- segmentation fault
	992	! ( circle_points(2,i_ip) >= zw(k-1) ) ) THEN
	993	! dz_int = dz_int - & !<--- segmentation fault
	994	! ( zw(k) - circle_points(2,i_ip) )
	995	! ENDIF
	996	! IF ( ( circle_points(1,i_ip) <= zw(k) ) .AND. & !<--- segmentation fault
	997	! ( circle_points(1,i_ip) > zw(k-1) ) ) THEN
	998	! dz_int = dz_int - &
	999	! ( circle_points(1,i_ip) - zw(k-1) )
	1000	! ENDIF
	1001	! IF ( zw(k-1) > circle_points(2,i_ip) ) THEN
	1002	! dz_int = 0.0_wp
	1003	! ENDIF
	1004	! IF ( zw(k) < circle_points(1,i_ip) ) THEN
	1005	! dz_int = 0.0_wp
	1006	! ENDIF
	1007	! IF ( ( nxlg <= i ) .AND. ( nxrg >= i ) ) THEN
[1912]	1008	! nac_cd_surf(k,j,i) = nac_cd_surf(k,j,i) + & !<--- segmentation fault
	1009	! dy_int * dz_int * turb_cd_nacelle(inot)
[1864]	1010	! ENDIF
	1011	! ENDDO
	1012	! ENDIF
	1013	! ENDDO
	1014	! ENDIF
[1819]	1015	!
[1864]	1016	! ENDDO
[1819]	1017	!
[1912]	1018	! CALL exchange_horiz( nac_cd_surf, nbgp ) !<--- segmentation fault
[1819]	1019
[1864]	1020	ENDDO ! end of loop over turbines
[1819]	1021
[1912]	1022	tow_cd_surf = tow_cd_surf / ( dx * dy * dz ) ! Normalize tower drag
	1023	nac_cd_surf = nac_cd_surf / ( dx * dy * dz ) ! Normalize nacelle drag
[1819]	1024
[1912]	1025	CALL wtm_read_blade_tables
[1839]	1026
[1864]	1027	END SUBROUTINE wtm_init
	1028
	1029
[1819]	1030	!------------------------------------------------------------------------------!
[1864]	1031	! Description:
	1032	! ------------
	1033	!> Read in layout of the rotor blade , the lift and drag tables
	1034	!> and the distribution of lift and drag tables along the blade
[1819]	1035	!------------------------------------------------------------------------------!
[1912]	1036	!
	1037	SUBROUTINE wtm_read_blade_tables
[1819]	1038
[1839]	1039
[1864]	1040	IMPLICIT NONE
	1041
	1042	INTEGER(iwp) :: ii !< running index
	1043	INTEGER(iwp) :: jj !< running index
[1843]	1044
[1864]	1045	INTEGER(iwp) :: ierrn !<
	1046
	1047	CHARACTER(200) :: chmess !< Read in string
[1839]	1048
[1864]	1049	INTEGER(iwp) :: dlen !< no. rows of local table
	1050	INTEGER(iwp) :: dlenbl !< no. rows of cd, cl table
	1051	INTEGER(iwp) :: ialpha !< table position of current alpha value
	1052	INTEGER(iwp) :: iialpha !<
	1053	INTEGER(iwp) :: iir !<
	1054	INTEGER(iwp) :: radres !< radial resolution
	1055	INTEGER(iwp) :: t1 !< no. of airfoil
	1056	INTEGER(iwp) :: t2 !< no. of airfoil
	1057	INTEGER(iwp) :: trow !<
	1058	INTEGER(iwp) :: dlenbl_int !< no. rows of interpolated cd, cl tables
[1839]	1059
[1864]	1060	REAL(wp) :: alpha_attack_i !<
	1061	REAL(wp) :: weight_a !<
	1062	REAL(wp) :: weight_b !<
[1839]	1063
[1864]	1064	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: ttoint1 !<
	1065	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: ttoint2 !<
[1839]	1066
[1864]	1067	REAL(wp), DIMENSION(:), ALLOCATABLE :: turb_cd_sel1 !<
	1068	REAL(wp), DIMENSION(:), ALLOCATABLE :: turb_cd_sel2 !<
	1069	REAL(wp), DIMENSION(:), ALLOCATABLE :: turb_cl_sel1 !<
	1070	REAL(wp), DIMENSION(:), ALLOCATABLE :: turb_cl_sel2 !<
	1071	REAL(wp), DIMENSION(:), ALLOCATABLE :: read_cl_cd !< read in var array
[1839]	1072
[1864]	1073	REAL(wp), DIMENSION(:), ALLOCATABLE :: alpha_attack_tab !<
	1074	REAL(wp), DIMENSION(:), ALLOCATABLE :: trad1 !<
	1075	REAL(wp), DIMENSION(:), ALLOCATABLE :: trad2 !<
	1076	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: turb_cd_table !<
	1077	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: turb_cl_table !<
[1839]	1078
[1864]	1079	ALLOCATE ( read_cl_cd(1:2*nairfoils+1) )
[1839]	1080
[1864]	1081	!
	1082	!-- Read in the distribution of lift and drag tables along the blade, the
	1083	!-- layout of the rotor blade and the lift and drag tables:
	1084
	1085	OPEN ( 201, FILE='WTM_DATA', STATUS='OLD', FORM='FORMATTED', IOSTAT=ierrn )
	1086
	1087	IF ( ierrn /= 0 ) THEN
	1088	message_string = 'file WTM_DATA does not exist'
	1089	CALL message( 'wtm_init', 'PA0???', 1, 2, 0, 6, 0 )
	1090	ENDIF
	1091	!
	1092	!-- Read distribution table:
	1093
	1094	dlen = 0
	1095
	1096	READ ( 201, '(3/)' )
	1097
	1098	rloop3: DO
	1099	READ ( 201, *, IOSTAT=ierrn ) chmess
	1100	IF ( ierrn < 0 .OR. chmess == '#' .OR. chmess == '') EXIT rloop3
	1101	dlen = dlen + 1
	1102	ENDDO rloop3
	1103
	1104	ALLOCATE( trad1(1:dlen), trad2(1:dlen), ttoint1(1:dlen), ttoint2(1:dlen))
	1105
	1106	DO jj = 1,dlen+1
	1107	BACKSPACE ( 201, IOSTAT=ierrn )
	1108	ENDDO
	1109
	1110	DO jj = 1,dlen
	1111	READ ( 201, * ) trad1(jj), trad2(jj), ttoint1(jj), ttoint2(jj)
	1112	ENDDO
	1113
	1114	!
	1115	!-- Read layout table:
	1116
[1839]	1117	dlen = 0
[1864]	1118
[1839]	1119	READ ( 201, '(3/)')
[1864]	1120
[1843]	1121	rloop1: DO
[1864]	1122	READ ( 201, *, IOSTAT=ierrn ) chmess
	1123	IF ( ierrn < 0 .OR. chmess == '#' .OR. chmess == '') EXIT rloop1
	1124	dlen = dlen + 1
[1843]	1125	ENDDO rloop1
[1864]	1126
[1839]	1127	ALLOCATE( lrd(1:dlen), ard(1:dlen), crd(1:dlen) )
[1864]	1128	DO jj = 1, dlen+1
	1129	BACKSPACE ( 201, IOSTAT=ierrn )
	1130	ENDDO
	1131	DO jj = 1, dlen
	1132	READ ( 201, * ) lrd(jj), ard(jj), crd(jj)
[1839]	1133	ENDDO
[1819]	1134
[1864]	1135	!
	1136	!-- Read tables (turb_cl(alpha),turb_cd(alpha) for the different profiles:
[1819]	1137
[1864]	1138	dlen = 0
	1139
[1839]	1140	READ ( 201, '(3/)' )
[1864]	1141
[1843]	1142	rloop2: DO
[1864]	1143	READ ( 201, *, IOSTAT=ierrn ) chmess
	1144	IF ( ierrn < 0 .OR. chmess == '#' .OR. chmess == '') EXIT rloop2
	1145	dlen = dlen + 1
	1146	ENDDO rloop2
	1147
[1912]	1148	ALLOCATE( alpha_attack_tab(1:dlen), turb_cl_table(1:dlen,1:nairfoils), &
[1864]	1149	turb_cd_table(1:dlen,1:nairfoils) )
	1150
	1151	DO jj = 1,dlen+1
	1152	BACKSPACE ( 201, IOSTAT=ierrn )
	1153	ENDDO
	1154
[1839]	1155	DO jj = 1,dlen
[1864]	1156	READ ( 201, * ) read_cl_cd
	1157	alpha_attack_tab(jj) = read_cl_cd(1)
	1158	DO ii= 1, nairfoils
	1159	turb_cl_table(jj,ii) = read_cl_cd(ii*2)
	1160	turb_cd_table(jj,ii) = read_cl_cd(ii*2+1)
[1819]	1161	ENDDO
[1864]	1162
[1839]	1163	ENDDO
[1864]	1164
	1165	dlenbl = dlen
	1166
[1839]	1167	CLOSE ( 201 )
[1819]	1168
[1864]	1169	!
	1170	!-- For each possible radial position (resolution: 0.1 m --> 630 values) and
	1171	!-- each possible angle of attack (resolution: 0.01 degrees --> 36000 values!)
	1172	!-- determine the lift and drag coefficient by interpolating between the
	1173	!-- tabulated values of each table (interpolate to current angle of attack)
	1174	!-- and between the tables (interpolate to current radial position):
[1839]	1175
[1864]	1176	ALLOCATE( turb_cl_sel1(0:dlenbl) )
	1177	ALLOCATE( turb_cl_sel2(0:dlenbl) )
	1178	ALLOCATE( turb_cd_sel1(0:dlenbl) )
	1179	ALLOCATE( turb_cd_sel2(0:dlenbl) )
[1819]	1180
[1864]	1181	radres = INT( rr(1) * 10.0_wp ) + 1_iwp
	1182	dlenbl_int = INT( 360.0_wp / accu_cl_cd_tab ) + 1_iwp
[1839]	1183
[1864]	1184
	1185	ALLOCATE( turb_cl_tab(0:dlenbl_int,1:radres) )
	1186	ALLOCATE( turb_cd_tab(0:dlenbl_int,1:radres) )
	1187
	1188
	1189	DO iir = 1, radres ! loop over radius
	1190
	1191	DO iialpha = 1, dlenbl_int ! loop over angles
	1192
	1193	cur_r = ( iir - 1_iwp ) * 0.1_wp
	1194	alpha_attack_i = -180.0_wp + REAL( iialpha-1 ) * accu_cl_cd_tab
	1195	ialpha = 1
	1196
	1197	DO WHILE ( alpha_attack_i > alpha_attack_tab(ialpha) )
	1198	ialpha = ialpha + 1
	1199	ENDDO
[1819]	1200	!
[1864]	1201	!-- Find position in table
	1202	lct = MINLOC( ABS( trad1 - cur_r ) )
	1203	! lct(1) = lct(1)
[1819]	1204
[1864]	1205	IF ( ( trad1(lct(1)) - cur_r ) .GT. 0.0 ) THEN
	1206	lct(1) = lct(1) - 1
	1207	ENDIF
[1819]	1208
[1864]	1209	trow = lct(1)
	1210	!
	1211	!-- Calculate weights for interpolation
	1212	weight_a = ( trad2(trow) - cur_r ) / ( trad2(trow) - trad1(trow) )
	1213	weight_b = ( cur_r - trad1(trow) ) / ( trad2(trow) - trad1(trow) )
	1214	t1 = ttoint1(trow)
	1215	t2 = ttoint2(trow)
[1819]	1216
[1912]	1217	IF ( t1 .EQ. t2 ) THEN ! if both are the same, the weights are NaN
	1218	weight_a = 0.5_wp ! then do interpolate in between same twice
	1219	weight_b = 0.5_wp ! using 0.5 as weight
[1864]	1220	ENDIF
[1819]	1221
[1864]	1222	IF ( t1 == 0 .AND. t2 == 0 ) THEN
	1223	turb_cd_sel1 = 0.0_wp
	1224	turb_cd_sel2 = 0.0_wp
	1225	turb_cl_sel1 = 0.0_wp
	1226	turb_cl_sel2 = 0.0_wp
	1227	ELSE
	1228	turb_cd_sel1 = turb_cd_table(:,t1)
	1229	turb_cd_sel2 = turb_cd_table(:,t2)
	1230	turb_cl_sel1 = turb_cl_table(:,t1)
	1231	turb_cl_sel2 = turb_cl_table(:,t2)
	1232	ENDIF
	1233
[1912]	1234	!
	1235	!-- Interpolation of lift and drag coefficiencts on fine grid of radius
	1236	!-- segments and angles of attack
	1237
	1238	turb_cl_tab(iialpha,iir) = ( alpha_attack_tab(ialpha) - &
	1239	alpha_attack_i ) / &
[1864]	1240	( alpha_attack_tab(ialpha) - &
	1241	alpha_attack_tab(ialpha-1) ) * &
	1242	( weight_a * turb_cl_sel1(ialpha-1) + &
	1243	weight_b * turb_cl_sel2(ialpha-1) ) +&
	1244	( alpha_attack_i - &
	1245	alpha_attack_tab(ialpha-1) ) / &
	1246	( alpha_attack_tab(ialpha) - &
	1247	alpha_attack_tab(ialpha-1) ) * &
	1248	( weight_a * turb_cl_sel1(ialpha) + &
	1249	weight_b * turb_cl_sel2(ialpha) )
[1912]	1250	turb_cd_tab(iialpha,iir) = ( alpha_attack_tab(ialpha) - &
	1251	alpha_attack_i ) / &
[1864]	1252	( alpha_attack_tab(ialpha) - &
	1253	alpha_attack_tab(ialpha-1) ) * &
	1254	( weight_a * turb_cd_sel1(ialpha-1) + &
	1255	weight_b * turb_cd_sel2(ialpha-1) ) +&
	1256	( alpha_attack_i - &
	1257	alpha_attack_tab(ialpha-1) ) / &
	1258	( alpha_attack_tab(ialpha) - &
	1259	alpha_attack_tab(ialpha-1) ) * &
	1260	( weight_a * turb_cd_sel1(ialpha) + &
	1261	weight_b * turb_cd_sel2(ialpha) )
[1819]	1262
[1912]	1263	ENDDO ! end loop over angles of attack
[1819]	1264
[1864]	1265	ENDDO ! end loop over radius
	1266
[1912]	1267	END SUBROUTINE wtm_read_blade_tables
[1819]	1268
	1269
[1864]	1270	!------------------------------------------------------------------------------!
	1271	! Description:
	1272	! ------------
	1273	!> The projection matrix for the coordinate system of therotor disc in respect
	1274	!> to the yaw and tilt angle of the rotor is calculated
	1275	!------------------------------------------------------------------------------!
	1276	SUBROUTINE wtm_rotate_rotor( inot )
[1819]	1277
[1864]	1278
	1279	IMPLICIT NONE
	1280
	1281	INTEGER(iwp) :: inot
	1282	!
	1283	!-- Calculation of the rotation matrix for the application of the tilt to
	1284	!-- the rotors
	1285	rot_eigen_rad(1) = SIN( phi_yaw(inot) ) ! x-component of the radial eigenvector
	1286	rot_eigen_rad(2) = COS( phi_yaw(inot) ) ! y-component of the radial eigenvector
	1287	rot_eigen_rad(3) = 0.0_wp ! z-component of the radial eigenvector
	1288
	1289	rot_eigen_azi(1) = 0.0_wp ! x-component of the azimuth eigenvector
	1290	rot_eigen_azi(2) = 0.0_wp ! y-component of the azimuth eigenvector
	1291	rot_eigen_azi(3) = 1.0_wp ! z-component of the azimuth eigenvector
	1292
	1293	rot_eigen_nor(1) = COS( phi_yaw(inot) ) ! x-component of the normal eigenvector
	1294	rot_eigen_nor(2) = -SIN( phi_yaw(inot) ) ! y-component of the normal eigenvector
	1295	rot_eigen_nor(3) = 0.0_wp ! z-component of the normal eigenvector
[1839]	1296
[1864]	1297	!
	1298	!-- Calculation of the coordinate transformation matrix to apply a tilt to
	1299	!-- the rotor. If tilt = 0, rot_coord_trans is a unit matrix.
[1819]	1300
[1912]	1301	rot_coord_trans(inot,1,1) = rot_eigen_rad(1)*2 &
[1864]	1302	( 1.0_wp - COS( tilt ) ) + COS( tilt )
[1912]	1303	rot_coord_trans(inot,1,2) = rot_eigen_rad(1) * rot_eigen_rad(2) * &
	1304	( 1.0_wp - COS( tilt ) ) - &
[1864]	1305	rot_eigen_rad(3) * SIN( tilt )
[1912]	1306	rot_coord_trans(inot,1,3) = rot_eigen_rad(1) * rot_eigen_rad(3) * &
	1307	( 1.0_wp - COS( tilt ) ) + &
[1864]	1308	rot_eigen_rad(2) * SIN( tilt )
[1912]	1309	rot_coord_trans(inot,2,1) = rot_eigen_rad(2) * rot_eigen_rad(1) * &
	1310	( 1.0_wp - COS( tilt ) ) + &
[1864]	1311	rot_eigen_rad(3) * SIN( tilt )
[1912]	1312	rot_coord_trans(inot,2,2) = rot_eigen_rad(2)*2 &
[1864]	1313	( 1.0_wp - COS( tilt ) ) + COS( tilt )
[1912]	1314	rot_coord_trans(inot,2,3) = rot_eigen_rad(2) * rot_eigen_rad(3) * &
	1315	( 1.0_wp - COS( tilt ) ) - &
[1864]	1316	rot_eigen_rad(1) * SIN( tilt )
[1912]	1317	rot_coord_trans(inot,3,1) = rot_eigen_rad(3) * rot_eigen_rad(1) * &
	1318	( 1.0_wp - COS( tilt ) ) - &
[1864]	1319	rot_eigen_rad(2) * SIN( tilt )
[1912]	1320	rot_coord_trans(inot,3,2) = rot_eigen_rad(3) * rot_eigen_rad(2) * &
	1321	( 1.0_wp - COS( tilt ) ) + &
[1864]	1322	rot_eigen_rad(1) * SIN( tilt )
[1912]	1323	rot_coord_trans(inot,3,3) = rot_eigen_rad(3)*2 &
[1864]	1324	( 1.0_wp - COS( tilt ) ) + COS( tilt )
[1839]	1325
[1864]	1326	!
	1327	!-- Vectors for the Transformation of forces from the rotor's spheric
	1328	!-- coordinate system to the cartesian coordinate system
	1329	rotx(inot,:) = MATMUL( rot_coord_trans(inot,:,:), rot_eigen_nor )
	1330	roty(inot,:) = MATMUL( rot_coord_trans(inot,:,:), rot_eigen_rad )
	1331	rotz(inot,:) = MATMUL( rot_coord_trans(inot,:,:), rot_eigen_azi )
	1332
	1333	END SUBROUTINE wtm_rotate_rotor
[1839]	1334
	1335
[1819]	1336	!------------------------------------------------------------------------------!
	1337	! Description:
	1338	! ------------
[1839]	1339	!> Calculation of the forces generated by the wind turbine
[1819]	1340	!------------------------------------------------------------------------------!
	1341	SUBROUTINE wtm_forces
	1342
[1864]	1343
[1819]	1344	IMPLICIT NONE
	1345
	1346	CHARACTER (LEN=2) :: turbine_id
	1347
[1839]	1348	INTEGER(iwp) :: i, j, k !< loop indices
	1349	INTEGER(iwp) :: inot !< turbine loop index (turbine id)
	1350	INTEGER(iwp) :: iialpha, iir !<
	1351	INTEGER(iwp) :: rseg, rseg_int !<
	1352	INTEGER(iwp) :: ring, ring_int !<
	1353	INTEGER(iwp) :: ii, jj, kk !<
[1912]	1354
[1839]	1355	REAL(wp) :: sin_rot, cos_rot !<
	1356	REAL(wp) :: sin_yaw, cos_yaw !<
[1912]	1357
	1358	REAL(wp) :: aa, bb, cc, dd !< interpolation distances
	1359	REAL(wp) :: gg !< interpolation volume var
	1360
	1361	REAL(wp) :: dist_u_3d, dist_v_3d, dist_w_3d !< smearing distances
	1362
	1363
[1839]	1364	!
[1819]	1365	! Variables for pitch control
	1366	REAL(wp) :: torque_max=0.0_wp
[1839]	1367	LOGICAL :: pitch_sw=.FALSE.
	1368
[1819]	1369	INTEGER(iwp), DIMENSION(1) :: lct=0
[1839]	1370	REAL(wp), DIMENSION(1) :: rad_d=0.0_wp
[1819]	1371
	1372
[1864]	1373	CALL cpu_log( log_point_s(61), 'wtm_forces', 'start' )
[1819]	1374
	1375
	1376	IF ( simulated_time >= time_turbine_on ) THEN
	1377
[1864]	1378	!
[1819]	1379	!-- Set forces to zero for each new time step:
	1380	thrust(:,:,:) = 0.0_wp
	1381	torque_y(:,:,:) = 0.0_wp
	1382	torque_z(:,:,:) = 0.0_wp
	1383	torque_total(:) = 0.0_wp
[1912]	1384	rot_tend_x(:,:,:) = 0.0_wp
	1385	rot_tend_y(:,:,:) = 0.0_wp
	1386	rot_tend_z(:,:,:) = 0.0_wp
	1387	thrust_rotor(:) = 0.0_wp
[1819]	1388	!
	1389	!-- Loop over number of turbines:
	1390	DO inot = 1, nturbines
	1391
	1392	cos_yaw = COS(phi_yaw(inot))
	1393	sin_yaw = SIN(phi_yaw(inot))
	1394	!
[1839]	1395	!-- Loop over rings of each turbine:
[1819]	1396	DO ring = 1, nrings(inot)
	1397
	1398	thrust_seg(:) = 0.0_wp
	1399	torque_seg_y(:) = 0.0_wp
	1400	torque_seg_z(:) = 0.0_wp
	1401	!
	1402	!-- Determine distance between each ring (center) and the hub:
	1403	cur_r = (ring - 0.5_wp) * delta_r(inot)
	1404
	1405	!
[1839]	1406	!-- Loop over segments of each ring of each turbine:
[1819]	1407	DO rseg = 1, nsegs(ring,inot)
	1408	!
[1864]	1409	!-- !-----------------------------------------------------------!
	1410	!-- !-- Determine coordinates of the ring segments --!
	1411	!-- !-----------------------------------------------------------!
[1819]	1412	!
[1864]	1413	!-- Determine angle of ring segment towards zero degree angle of
	1414	!-- rotor system (at zero degree rotor direction vectors aligned
	1415	!-- with y-axis):
[1819]	1416	phi_rotor = rseg * 2.0_wp * pi / nsegs(ring,inot)
	1417	cos_rot = COS( phi_rotor )
	1418	sin_rot = SIN( phi_rotor )
	1419
[1864]	1420	!-- Now the direction vectors can be determined with respect to
	1421	!-- the yaw and tilt angle:
[1819]	1422	re(1) = cos_rot * sin_yaw
[1839]	1423	re(2) = cos_rot * cos_yaw
[1819]	1424	re(3) = sin_rot
	1425
	1426	rote = MATMUL( rot_coord_trans(inot,:,:), re )
	1427	!
	1428	!-- Coordinates of the single segments (center points):
	1429	rbx(ring,rseg) = rcx(inot) + cur_r * rote(1)
	1430	rby(ring,rseg) = rcy(inot) + cur_r * rote(2)
	1431	rbz(ring,rseg) = rcz(inot) + cur_r * rote(3)
	1432
[1864]	1433	!-- !-----------------------------------------------------------!
	1434	!-- !-- Interpolation of the velocity components from the --!
	1435	!-- !-- cartesian grid point to the coordinates of each ring --!
	1436	!-- !-- segment (follows a method used in the particle model) --!
	1437	!-- !-----------------------------------------------------------!
[1819]	1438
	1439	u_int(inot,ring,rseg) = 0.0_wp
	1440	u_int_1_l(inot,ring,rseg) = 0.0_wp
	1441
	1442	v_int(inot,ring,rseg) = 0.0_wp
	1443	v_int_1_l(inot,ring,rseg) = 0.0_wp
	1444
	1445	w_int(inot,ring,rseg) = 0.0_wp
	1446	w_int_1_l(inot,ring,rseg) = 0.0_wp
	1447
	1448	!
	1449	!-- Interpolation of the u-component:
	1450
	1451	ii = rbx(ring,rseg) * ddx
	1452	jj = ( rby(ring,rseg) - 0.5_wp * dy ) * ddy
	1453	kk = ( rbz(ring,rseg) - 0.5_wp * dz ) / dz
	1454	!
[1864]	1455	!-- Interpolate only if all required information is available on
	1456	!-- the current PE:
[1839]	1457	IF ( ( ii >= nxl ) .AND. ( ii <= nxr ) ) THEN
	1458	IF ( ( jj >= nys ) .AND. ( jj <= nyn ) ) THEN
[1819]	1459
[1839]	1460	aa = ( ( ii + 1 ) * dx - rbx(ring,rseg) ) * &
	1461	( ( jj + 1 + 0.5_wp ) * dy - rby(ring,rseg) )
	1462	bb = ( rbx(ring,rseg) - ii * dx ) * &
	1463	( ( jj + 1 + 0.5_wp ) * dy - rby(ring,rseg) )
	1464	cc = ( ( ii+1 ) * dx - rbx(ring,rseg) ) * &
	1465	( rby(ring,rseg) - ( jj + 0.5_wp ) * dy )
	1466	dd = ( rbx(ring,rseg) - ii * dx ) * &
	1467	( rby(ring,rseg) - ( jj + 0.5_wp ) * dy )
[1819]	1468	gg = dx * dy
	1469
[1864]	1470	u_int_l = ( aa * u(kk,jj,ii) + &
	1471	bb * u(kk,jj,ii+1) + &
	1472	cc * u(kk,jj+1,ii) + &
	1473	dd * u(kk,jj+1,ii+1) &
[1819]	1474	) / gg
	1475
[1864]	1476	u_int_u = ( aa * u(kk+1,jj,ii) + &
	1477	bb * u(kk+1,jj,ii+1) + &
	1478	cc * u(kk+1,jj+1,ii) + &
	1479	dd * u(kk+1,jj+1,ii+1) &
[1819]	1480	) / gg
	1481
[1864]	1482	u_int_1_l(inot,ring,rseg) = u_int_l + &
	1483	( rbz(ring,rseg) - zu(kk) ) / dz * &
[1819]	1484	( u_int_u - u_int_l )
	1485
	1486	ELSE
	1487	u_int_1_l(inot,ring,rseg) = 0.0_wp
	1488	ENDIF
	1489	ELSE
	1490	u_int_1_l(inot,ring,rseg) = 0.0_wp
	1491	ENDIF
	1492
	1493
	1494	!
	1495	!-- Interpolation of the v-component:
	1496	ii = ( rbx(ring,rseg) - 0.5_wp * dx ) * ddx
[1839]	1497	jj = rby(ring,rseg) * ddy
[1819]	1498	kk = ( rbz(ring,rseg) + 0.5_wp * dz ) / dz
	1499	!
[1864]	1500	!-- Interpolate only if all required information is available on
	1501	!-- the current PE:
[1839]	1502	IF ( ( ii >= nxl ) .AND. ( ii <= nxr ) ) THEN
	1503	IF ( ( jj >= nys ) .AND. ( jj <= nyn ) ) THEN
[1819]	1504
[1839]	1505	aa = ( ( ii + 1 + 0.5_wp ) * dx - rbx(ring,rseg) ) * &
	1506	( ( jj + 1 ) * dy - rby(ring,rseg) )
	1507	bb = ( rbx(ring,rseg) - ( ii + 0.5_wp ) * dx ) * &
	1508	( ( jj + 1 ) * dy - rby(ring,rseg) )
	1509	cc = ( ( ii + 1 + 0.5_wp ) * dx - rbx(ring,rseg) ) * &
	1510	( rby(ring,rseg) - jj * dy )
	1511	dd = ( rbx(ring,rseg) - ( ii + 0.5_wp ) * dx ) * &
	1512	( rby(ring,rseg) - jj * dy )
[1819]	1513	gg = dx * dy
	1514
[1864]	1515	v_int_l = ( aa * v(kk,jj,ii) + &
	1516	bb * v(kk,jj,ii+1) + &
	1517	cc * v(kk,jj+1,ii) + &
	1518	dd * v(kk,jj+1,ii+1) &
[1819]	1519	) / gg
	1520
[1864]	1521	v_int_u = ( aa * v(kk+1,jj,ii) + &
	1522	bb * v(kk+1,jj,ii+1) + &
	1523	cc * v(kk+1,jj+1,ii) + &
	1524	dd * v(kk+1,jj+1,ii+1) &
[1819]	1525	) / gg
	1526
[1864]	1527	v_int_1_l(inot,ring,rseg) = v_int_l + &
	1528	( rbz(ring,rseg) - zu(kk) ) / dz * &
[1819]	1529	( v_int_u - v_int_l )
	1530
	1531	ELSE
	1532	v_int_1_l(inot,ring,rseg) = 0.0_wp
	1533	ENDIF
	1534	ELSE
	1535	v_int_1_l(inot,ring,rseg) = 0.0_wp
	1536	ENDIF
	1537
	1538
	1539	!
	1540	!-- Interpolation of the w-component:
	1541	ii = ( rbx(ring,rseg) - 0.5_wp * dx ) * ddx
	1542	jj = ( rby(ring,rseg) - 0.5_wp * dy ) * ddy
[1839]	1543	kk = rbz(ring,rseg) / dz
[1819]	1544	!
[1864]	1545	!-- Interpolate only if all required information is available on
	1546	!-- the current PE:
[1839]	1547	IF ( ( ii >= nxl ) .AND. ( ii <= nxr ) ) THEN
	1548	IF ( ( jj >= nys ) .AND. ( jj <= nyn ) ) THEN
[1819]	1549
[1839]	1550	aa = ( ( ii + 1 + 0.5_wp ) * dx - rbx(ring,rseg) ) * &
	1551	( ( jj + 1 + 0.5_wp ) * dy - rby(ring,rseg) )
	1552	bb = ( rbx(ring,rseg) - ( ii + 0.5_wp ) * dx ) * &
	1553	( ( jj + 1 + 0.5_wp ) * dy - rby(ring,rseg) )
	1554	cc = ( ( ii + 1 + 0.5_wp ) * dx - rbx(ring,rseg) ) * &
	1555	( rby(ring,rseg) - ( jj + 0.5_wp ) * dy )
	1556	dd = ( rbx(ring,rseg) - ( ii + 0.5_wp ) * dx ) * &
	1557	( rby(ring,rseg) - ( jj + 0.5_wp ) * dy )
[1819]	1558	gg = dx * dy
	1559
[1864]	1560	w_int_l = ( aa * w(kk,jj,ii) + &
	1561	bb * w(kk,jj,ii+1) + &
	1562	cc * w(kk,jj+1,ii) + &
	1563	dd * w(kk,jj+1,ii+1) &
[1819]	1564	) / gg
	1565
[1864]	1566	w_int_u = ( aa * w(kk+1,jj,ii) + &
	1567	bb * w(kk+1,jj,ii+1) + &
	1568	cc * w(kk+1,jj+1,ii) + &
	1569	dd * w(kk+1,jj+1,ii+1) &
[1819]	1570	) / gg
	1571
[1864]	1572	w_int_1_l(inot,ring,rseg) = w_int_l + &
	1573	( rbz(ring,rseg) - zw(kk) ) / dz * &
[1819]	1574	( w_int_u - w_int_l )
	1575	ELSE
	1576	w_int_1_l(inot,ring,rseg) = 0.0_wp
	1577	ENDIF
	1578	ELSE
	1579	w_int_1_l(inot,ring,rseg) = 0.0_wp
	1580	ENDIF
	1581
	1582	ENDDO
	1583	ENDDO
	1584
	1585	ENDDO
	1586
	1587	!
	1588	!-- Exchange between PEs (information required on each PE):
	1589	#if defined( __parallel )
[1839]	1590	CALL MPI_ALLREDUCE( u_int_1_l, u_int, nturbines * MAXVAL(nrings) * &
	1591	MAXVAL(nsegs), MPI_REAL, MPI_SUM, comm2d, ierr )
	1592	CALL MPI_ALLREDUCE( v_int_1_l, v_int, nturbines * MAXVAL(nrings) * &
	1593	MAXVAL(nsegs), MPI_REAL, MPI_SUM, comm2d, ierr )
	1594	CALL MPI_ALLREDUCE( w_int_1_l, w_int, nturbines * MAXVAL(nrings) * &
	1595	MAXVAL(nsegs), MPI_REAL, MPI_SUM, comm2d, ierr )
[1819]	1596	#else
	1597	u_int = u_int_1_l
	1598	v_int = v_int_1_l
	1599	w_int = w_int_1_l
	1600	#endif
	1601
	1602
	1603	!
	1604	!-- Loop over number of turbines:
[1912]	1605
[1819]	1606	DO inot = 1, nturbines
[1912]	1607	pit_loop: DO
[1819]	1608
[1912]	1609	IF ( pitch_sw ) THEN
[1839]	1610	torque_total(inot) = 0.0_wp
[1912]	1611	thrust_rotor(inot) = 0.0_wp
	1612	pitch_add(inot) = pitch_add(inot) + 0.25_wp
	1613	! IF ( myid == 0 ) PRINT*, 'Pitch', inot, pitch_add(inot)
	1614	ELSE
	1615	cos_yaw = COS(phi_yaw(inot))
	1616	sin_yaw = SIN(phi_yaw(inot))
	1617	IF ( pitch_control ) THEN
	1618	pitch_add(inot) = MAX(pitch_add_old(inot) - pitch_rate * &
	1619	dt_3d , 0.0_wp )
	1620	ENDIF
[1819]	1621	ENDIF
	1622
[1839]	1623	!
	1624	!-- Loop over rings of each turbine:
[1819]	1625	DO ring = 1, nrings(inot)
	1626	!
	1627	!-- Determine distance between each ring (center) and the hub:
	1628	cur_r = (ring - 0.5_wp) * delta_r(inot)
[1839]	1629	!
	1630	!-- Loop over segments of each ring of each turbine:
[1819]	1631	DO rseg = 1, nsegs(ring,inot)
	1632	!
[1839]	1633	!-- Determine angle of ring segment towards zero degree angle of
	1634	!-- rotor system (at zero degree rotor direction vectors aligned
	1635	!-- with y-axis):
[1819]	1636	phi_rotor = rseg * 2.0_wp * pi / nsegs(ring,inot)
	1637	cos_rot = COS(phi_rotor)
	1638	sin_rot = SIN(phi_rotor)
	1639	!
[1839]	1640	!-- Now the direction vectors can be determined with respect to
	1641	!-- the yaw and tilt angle:
[1819]	1642	re(1) = cos_rot * sin_yaw
	1643	re(2) = cos_rot * cos_yaw
	1644	re(3) = sin_rot
	1645
[1864]	1646	! The current unit vector in azimuthal direction:
[1819]	1647	rea(1) = - sin_rot * sin_yaw
	1648	rea(2) = - sin_rot * cos_yaw
	1649	rea(3) = cos_rot
	1650
	1651	!
[1864]	1652	!-- To respect the yawing angle for the calculations of
	1653	!-- velocities and forces the unit vectors perpendicular to the
	1654	!-- rotor area in direction of the positive yaw angle are defined:
[1819]	1655	ren(1) = cos_yaw
	1656	ren(2) = - sin_yaw
	1657	ren(3) = 0.0_wp
	1658	!
	1659	!-- Multiplication with the coordinate transformation matrix
[1864]	1660	!-- gives the final unit vector with consideration of the rotor
	1661	!-- tilt:
[1819]	1662	rote = MATMUL( rot_coord_trans(inot,:,:), re )
	1663	rota = MATMUL( rot_coord_trans(inot,:,:), rea )
	1664	rotn = MATMUL( rot_coord_trans(inot,:,:), ren )
	1665	!
	1666	!-- Coordinates of the single segments (center points):
	1667	rbx(ring,rseg) = rcx(inot) + cur_r * rote(1)
	1668
	1669	rby(ring,rseg) = rcy(inot) + cur_r * rote(2)
	1670
	1671	rbz(ring,rseg) = rcz(inot) + cur_r * rote(3)
	1672
	1673	!
[1864]	1674	!-- !-----------------------------------------------------------!
	1675	!-- !-- Calculation of various angles and relative velocities --!
	1676	!-- !-----------------------------------------------------------!
[1819]	1677	!
[1864]	1678	!-- In the following the 3D-velocity field is projected its
[1819]	1679	!-- components perpedicular and parallel to the rotor area
	1680	!-- The calculation of forces will be done in the rotor-
	1681	!-- coordinates y' and z.
	1682	!-- The yaw angle will be reintroduced when the force is applied
	1683	!-- on the hydrodynamic equations
[1864]	1684	!
	1685	!-- Projection of the xy-velocities relative to the rotor area
	1686	!
[1819]	1687	!-- Velocity perpendicular to the rotor area:
[1864]	1688	u_rot = u_int(inot,ring,rseg)*rotn(1) + &
	1689	v_int(inot,ring,rseg)*rotn(2) + &
[1819]	1690	w_int(inot,ring,rseg)*rotn(3)
	1691	!
[1864]	1692	!-- Projection of the 3D-velocity vector in the azimuthal
	1693	!-- direction:
	1694	vtheta(rseg) = rota(1) * u_int(inot,ring,rseg) + &
	1695	rota(2) * v_int(inot,ring,rseg) + &
[1819]	1696	rota(3) * w_int(inot,ring,rseg)
	1697	!
[1864]	1698	!-- Determination of the angle phi_rel between the rotor plane
	1699	!-- and the direction of the flow relative to the rotor:
[1819]	1700
[1864]	1701	phi_rel(rseg) = ATAN( u_rot / &
	1702	( omega_rot(inot) * cur_r - &
[1819]	1703	vtheta(rseg) ) )
	1704
	1705	!
[1864]	1706	!-- Interpolation of the local pitch angle from tabulated values
	1707	!-- to the current radial position:
[1819]	1708
	1709	lct=minloc(ABS(cur_r-lrd))
	1710	rad_d=cur_r-lrd(lct)
	1711
	1712	IF (cur_r == 0.0_wp) THEN
	1713	alpha_attack(rseg) = 0.0_wp
	1714	ELSE IF (cur_r >= lrd(size(ard))) THEN
[1864]	1715	alpha_attack(rseg) = ( ard(size(ard)) + &
	1716	ard(size(ard)-1) ) / 2.0_wp
[1819]	1717	ELSE
[1864]	1718	alpha_attack(rseg) = ( ard(lct(1)) * &
	1719	( ( lrd(lct(1)+1) - cur_r ) / &
	1720	( lrd(lct(1)+1) - lrd(lct(1)) ) &
	1721	) ) + ( ard(lct(1)+1) * &
	1722	( ( cur_r - lrd(lct(1)) ) / &
	1723	( lrd(lct(1)+1) - lrd(lct(1)) ) ) )
[1819]	1724	ENDIF
	1725
	1726	!
[1864]	1727	!-- In Fortran radian instead of degree is used as unit for all
	1728	!-- angles. Therefore, a transformation from angles given in
	1729	!-- degree to angles given in radian is necessary here:
	1730	alpha_attack(rseg) = alpha_attack(rseg) * &
[1819]	1731	( (2.0_wp*pi) / 360.0_wp )
	1732	!
[1864]	1733	!-- Substraction of the local pitch angle to obtain the local
	1734	!-- angle of attack:
[1819]	1735	alpha_attack(rseg) = phi_rel(rseg) - alpha_attack(rseg)
	1736	!
[1864]	1737	!-- Preliminary transformation back from angles given in radian
	1738	!-- to angles given in degree:
	1739	alpha_attack(rseg) = alpha_attack(rseg) * &
[1819]	1740	( 360.0_wp / (2.0_wp*pi) )
	1741	!
[1864]	1742	!-- Correct with collective pitch angle:
[2015]	1743	alpha_attack = alpha_attack - pitch_add(inot)
[1819]	1744
	1745	!
[1864]	1746	!-- Determination of the magnitude of the flow velocity relative
	1747	!-- to the rotor:
[1912]	1748	vrel(rseg) = SQRT( u_rot**2 + &
	1749	( omega_rot(inot) * cur_r - &
[1819]	1750	vtheta(rseg) )**2 )
	1751
	1752	!
[1864]	1753	!-- !-----------------------------------------------------------!
	1754	!-- !-- Interpolation of chord as well as lift and drag --!
	1755	!-- !-- coefficients from tabulated values --!
	1756	!-- !-----------------------------------------------------------!
[1819]	1757
	1758	!
[1864]	1759	!-- Interpolation of the chord_length from tabulated values to
	1760	!-- the current radial position:
[1819]	1761
	1762	IF (cur_r == 0.0_wp) THEN
	1763	chord(rseg) = 0.0_wp
	1764	ELSE IF (cur_r >= lrd(size(crd))) THEN
[1864]	1765	chord(rseg) = (crd(size(crd)) + ard(size(crd)-1)) / 2.0_wp
[1819]	1766	ELSE
[1864]	1767	chord(rseg) = ( crd(lct(1)) * &
	1768	( ( lrd(lct(1)+1) - cur_r ) / &
	1769	( lrd(lct(1)+1) - lrd(lct(1)) ) ) ) + &
	1770	( crd(lct(1)+1) * &
	1771	( ( cur_r-lrd(lct(1)) ) / &
	1772	( lrd(lct(1)+1) - lrd(lct(1)) ) ) )
[1819]	1773	ENDIF
	1774
	1775	!
	1776	!-- Determine index of current angle of attack, needed for
[1864]	1777	!-- finding the appropriate interpolated values of the lift and
	1778	!-- drag coefficients (-180.0 degrees = 0, +180.0 degrees = 36000,
	1779	!-- so one index every 0.01 degrees):
	1780	iialpha = CEILING( ( alpha_attack(rseg) + 180.0_wp ) &
[1839]	1781	* ( 1.0_wp / accu_cl_cd_tab ) )
[1819]	1782	!
	1783	!-- Determine index of current radial position, needed for
[1864]	1784	!-- finding the appropriate interpolated values of the lift and
	1785	!-- drag coefficients (one index every 0.1 m):
[1819]	1786	iir = CEILING( cur_r * 10.0_wp )
	1787	!
[1864]	1788	!-- Read in interpolated values of the lift and drag coefficients
	1789	!-- for the current radial position and angle of attack:
[1839]	1790	turb_cl(rseg) = turb_cl_tab(iialpha,iir)
	1791	turb_cd(rseg) = turb_cd_tab(iialpha,iir)
[1819]	1792
	1793	!
[1864]	1794	!-- Final transformation back from angles given in degree to
	1795	!-- angles given in radian:
	1796	alpha_attack(rseg) = alpha_attack(rseg) * &
[1819]	1797	( (2.0_wp*pi) / 360.0_wp )
	1798
	1799	!
	1800	!-- !-----------------------------------------------------!
	1801	!-- !-- Calculation of the forces --!
	1802	!-- !-----------------------------------------------------!
	1803
	1804	!
[1864]	1805	!-- Calculate the pre_factor for the thrust and torque forces:
[1819]	1806
	1807	pre_factor = 0.5_wp * (vrel(rseg)*2) 3.0_wp * &
	1808	chord(rseg) * delta_r(inot) / nsegs(ring,inot)
	1809
	1810	!
[1864]	1811	!-- Calculate the thrust force (x-component of the total force)
	1812	!-- for each ring segment:
	1813	thrust_seg(rseg) = pre_factor * &
	1814	( turb_cl(rseg) * COS(phi_rel(rseg)) + &
	1815	turb_cd(rseg) * SIN(phi_rel(rseg)) )
[1819]	1816
	1817	!
[1864]	1818	!-- Determination of the second of the additional forces acting
	1819	!-- on the flow in the azimuthal direction: force vector as basis
	1820	!-- for torque (torque itself would be the vector product of the
	1821	!-- radius vector and the force vector):
	1822	torque_seg = pre_factor * &
	1823	( turb_cl(rseg) * SIN(phi_rel(rseg)) - &
[1839]	1824	turb_cd(rseg) * COS(phi_rel(rseg)) )
[1819]	1825	!
	1826	!-- Decomposition of the force vector into two parts:
[1864]	1827	!-- One acting along the y-direction and one acting along the
	1828	!-- z-direction of the rotor coordinate system:
[1819]	1829
	1830	torque_seg_y(rseg) = -torque_seg * sin_rot
	1831	torque_seg_z(rseg) = torque_seg * cos_rot
	1832
[1912]	1833	!
	1834	!-- Add the segment thrust to the thrust of the whole rotor
	1835	thrust_rotor(inot) = thrust_rotor(inot) + &
	1836	thrust_seg(rseg)
	1837
	1838
[1819]	1839	torque_total(inot) = torque_total(inot) + (torque_seg * cur_r)
	1840
[1864]	1841	ENDDO !-- end of loop over ring segments
[1819]	1842
	1843	!
[1864]	1844	!-- Restore the forces into arrays containing all the segments of
	1845	!-- each ring:
[1819]	1846	thrust_ring(ring,:) = thrust_seg(:)
	1847	torque_ring_y(ring,:) = torque_seg_y(:)
	1848	torque_ring_z(ring,:) = torque_seg_z(:)
	1849
	1850
[1864]	1851	ENDDO !-- end of loop over rings
[1819]	1852
	1853
[1864]	1854	CALL cpu_log( log_point_s(62), 'wtm_controller', 'start' )
[1819]	1855
[1912]	1856
	1857	IF ( speed_control ) THEN
	1858	!
	1859	!-- Calculation of the current generator speed for rotor speed control
	1860
	1861	!
	1862	!-- The acceleration of the rotor speed is calculated from
	1863	!-- the force balance of the accelerating torque
	1864	!-- and the torque of the rotating rotor and generator
	1865	om_rate = ( torque_total(inot) * air_dens * gear_eff - &
	1866	gear_ratio * torque_gen_old(inot) ) / &
	1867	( inertia_rot + &
	1868	gear_ratio * gear_ratio * inertia_gen ) * dt_3d
[1819]	1869
[1912]	1870	!
	1871	!-- The generator speed is given by the product of gear gear_ratio
	1872	!-- and rotor speed
	1873	omega_gen(inot) = gear_ratio * ( omega_rot(inot) + om_rate )
	1874
	1875	ENDIF
	1876
[1864]	1877	IF ( pitch_control ) THEN
[1819]	1878
[1912]	1879	!
	1880	!-- If the current generator speed is above rated, the pitch is not
	1881	!-- saturated and the change from the last time step is within the
	1882	!-- maximum pitch rate, then the pitch loop is repeated with a pitch
	1883	!-- gain
	1884	IF ( ( omega_gen(inot) > rated_genspeed ) .AND. &
	1885	( pitch_add(inot) < 25.0_wp ) .AND. &
	1886	( pitch_add(inot) < pitch_add_old(inot) + &
	1887	pitch_rate * dt_3d ) ) THEN
[1864]	1888	pitch_sw = .TRUE.
[1912]	1889	!
	1890	!-- Go back to beginning of pit_loop
	1891	CYCLE pit_loop
[1819]	1892	ENDIF
[1912]	1893
	1894	!
	1895	!-- The current pitch is saved for the next time step
	1896	pitch_add_old(inot) = pitch_add(inot)
[1864]	1897	pitch_sw = .FALSE.
[1819]	1898	ENDIF
[1912]	1899	EXIT pit_loop
	1900	ENDDO pit_loop ! Recursive pitch control loop
[1819]	1901
[1864]	1902
[1819]	1903	!
[1864]	1904	!-- Call the rotor speed controller
	1905
[1819]	1906	IF ( speed_control ) THEN
	1907	!
[1864]	1908	!-- Find processor at i_hub, j_hub
[1912]	1909	IF ( ( nxl <= i_hub(inot) ) .AND. ( nxr >= i_hub(inot) ) ) &
	1910	THEN
	1911	IF ( ( nys <= j_hub(inot) ) .AND. ( nyn >= j_hub(inot) ) )&
	1912	THEN
[1864]	1913	CALL wtm_speed_control( inot )
	1914	ENDIF
[1912]	1915	ENDIF
[1864]	1916
[1819]	1917	ENDIF
	1918
	1919
[1864]	1920	CALL cpu_log( log_point_s(62), 'wtm_controller', 'stop' )
[1819]	1921
[1864]	1922	CALL cpu_log( log_point_s(63), 'wtm_smearing', 'start' )
[1819]	1923
	1924
[1864]	1925	!-- !-----------------------------------------------------------------!
	1926	!-- !-- Regularization kernel --!
	1927	!-- !-- Smearing of the forces and interpolation to cartesian grid --!
	1928	!-- !-----------------------------------------------------------------!
[1819]	1929	!
[1864]	1930	!-- The aerodynamic blade forces need to be distributed smoothly on
	1931	!-- several mesh points in order to avoid singular behaviour
[1819]	1932	!
	1933	!-- Summation over sum of weighted forces. The weighting factor
[1864]	1934	!-- (calculated in user_init) includes information on the distance
	1935	!-- between the center of the grid cell and the rotor segment under
	1936	!-- consideration
[1819]	1937	!
[1864]	1938	!-- To save computing time, apply smearing only for the relevant part
	1939	!-- of the model domain:
[1819]	1940	!
	1941	!--
	1942	!-- Calculation of the boundaries:
[1864]	1943	i_smear(inot) = CEILING( ( rr(inot) * ABS( roty(inot,1) ) + &
	1944	eps_min ) / dx )
	1945	j_smear(inot) = CEILING( ( rr(inot) * ABS( roty(inot,2) ) + &
	1946	eps_min ) / dy )
[1819]	1947
[1864]	1948	DO i = MAX( nxl, i_hub(inot) - i_smear(inot) ), &
[1819]	1949	MIN( nxr, i_hub(inot) + i_smear(inot) )
[1864]	1950	DO j = MAX( nys, j_hub(inot) - j_smear(inot) ), &
[1819]	1951	MIN( nyn, j_hub(inot) + j_smear(inot) )
	1952	DO k = MAX( nzb_u_inner(j,i)+1, k_hub(inot) - k_smear(inot) ), &
	1953	k_hub(inot) + k_smear(inot)
	1954	DO ring = 1, nrings(inot)
	1955	DO rseg = 1, nsegs(ring,inot)
	1956	!
	1957	!-- Determine the square of the distance between the
	1958	!-- current grid point and each rotor area segment:
[1864]	1959	dist_u_3d = ( i * dx - rbx(ring,rseg) )**2 + &
	1960	( j * dy + 0.5_wp * dy - rby(ring,rseg) )**2 + &
	1961	( k * dz - 0.5_wp * dz - rbz(ring,rseg) )**2
	1962	dist_v_3d = ( i * dx + 0.5_wp * dx - rbx(ring,rseg) )**2 + &
	1963	( j * dy - rby(ring,rseg) )**2 + &
	1964	( k * dz - 0.5_wp * dz - rbz(ring,rseg) )**2
	1965	dist_w_3d = ( i * dx + 0.5_wp * dx - rbx(ring,rseg) )**2 + &
	1966	( j * dy + 0.5_wp * dy - rby(ring,rseg) )**2 + &
	1967	( k * dz - rbz(ring,rseg) )**2
[1819]	1968
	1969	!
	1970	!-- 3D-smearing of the forces with a polynomial function
	1971	!-- (much faster than the old Gaussian function), using
	1972	!-- some parameters that have been calculated in user_init.
	1973	!-- The function is only similar to Gaussian function for
	1974	!-- squared distances <= eps_min2:
	1975	IF ( dist_u_3d <= eps_min2 ) THEN
[1864]	1976	thrust(k,j,i) = thrust(k,j,i) + &
	1977	thrust_ring(ring,rseg) * &
	1978	( ( pol_a * dist_u_3d - pol_b ) * &
	1979	dist_u_3d + 1.0_wp ) * eps_factor
[1819]	1980	ENDIF
	1981	IF ( dist_v_3d <= eps_min2 ) THEN
[1864]	1982	torque_y(k,j,i) = torque_y(k,j,i) + &
	1983	torque_ring_y(ring,rseg) * &
	1984	( ( pol_a * dist_v_3d - pol_b ) *&
	1985	dist_v_3d + 1.0_wp ) * eps_factor
[1819]	1986	ENDIF
	1987	IF ( dist_w_3d <= eps_min2 ) THEN
[1864]	1988	torque_z(k,j,i) = torque_z(k,j,i) + &
	1989	torque_ring_z(ring,rseg) * &
	1990	( ( pol_a * dist_w_3d - pol_b ) *&
	1991	dist_w_3d + 1.0_wp ) * eps_factor
[1819]	1992	ENDIF
	1993
	1994	ENDDO ! End of loop over rseg
	1995	ENDDO ! End of loop over ring
	1996
	1997	!
	1998	!-- Rotation of force components:
[1912]	1999	rot_tend_x(k,j,i) = rot_tend_x(k,j,i) + &
[1864]	2000	thrust(k,j,i)*rotx(inot,1) + &
	2001	torque_y(k,j,i)*roty(inot,1) + &
[1819]	2002	torque_z(k,j,i)*rotz(inot,1)
	2003
[1912]	2004	rot_tend_y(k,j,i) = rot_tend_y(k,j,i) + &
[1864]	2005	thrust(k,j,i)*rotx(inot,2) + &
	2006	torque_y(k,j,i)*roty(inot,2) + &
[1819]	2007	torque_z(k,j,i)*rotz(inot,2)
	2008
[1912]	2009	rot_tend_z(k,j,i) = rot_tend_z(k,j,i) + &
[1864]	2010	thrust(k,j,i)*rotx(inot,3) + &
	2011	torque_y(k,j,i)*roty(inot,3) + &
[1819]	2012	torque_z(k,j,i)*rotz(inot,3)
	2013
	2014	ENDDO ! End of loop over k
	2015	ENDDO ! End of loop over j
	2016	ENDDO ! End of loop over i
	2017
[1864]	2018	CALL cpu_log( log_point_s(63), 'wtm_smearing', 'stop' )
[1819]	2019
[1912]	2020	ENDDO !-- end of loop over turbines
[1819]	2021
	2022
	2023	IF ( yaw_control ) THEN
	2024	!
	2025	!-- Allocate arrays for yaw control at first call
	2026	!-- Can't be allocated before dt_3d is set
	2027	IF ( start_up ) THEN
[1864]	2028	WDLON = NINT( 30.0_wp / dt_3d ) ! 30s running mean array
[1819]	2029	ALLOCATE( wd30(1:nturbines,1:WDLON) )
[1912]	2030	wd30 = 999.0_wp ! Set to dummy value
[1819]	2031	ALLOCATE( wd30_l(1:WDLON) )
	2032
[1864]	2033	WDSHO = NINT( 2.0_wp / dt_3d ) ! 2s running mean array
[1819]	2034	ALLOCATE( wd2(1:nturbines,1:WDSHO) )
[1912]	2035	wd2 = 999.0_wp ! Set to dummy value
[1819]	2036	ALLOCATE( wd2_l(1:WDSHO) )
	2037	start_up = .FALSE.
	2038	ENDIF
	2039
	2040	!
	2041	!-- Calculate the inflow wind speed
	2042	!--
	2043	!-- Loop over number of turbines:
	2044	DO inot = 1, nturbines
	2045	!
	2046	!-- Find processor at i_hub, j_hub
[1912]	2047	IF ( ( nxl <= i_hub(inot) ) .AND. ( nxr >= i_hub(inot) ) ) &
	2048	THEN
	2049	IF ( ( nys <= j_hub(inot) ) .AND. ( nyn >= j_hub(inot) ) )&
	2050	THEN
[1864]	2051
[1819]	2052	u_inflow_l(inot) = u(k_hub(inot),j_hub(inot),i_hub(inot))
[1864]	2053
[1912]	2054	wdir_l(inot) = -1.0_wp * ATAN2( &
	2055	0.5_wp * ( v(k_hub(inot),j_hub(inot),i_hub(inot)+1) + &
	2056	v(k_hub(inot),j_hub(inot),i_hub(inot)) ) , &
	2057	0.5_wp * ( u(k_hub(inot),j_hub(inot)+1,i_hub(inot)) + &
	2058	u(k_hub(inot),j_hub(inot),i_hub(inot)) ) )
[1864]	2059
	2060	CALL wtm_yawcontrol( inot )
	2061
[1819]	2062	phi_yaw_l(inot) = phi_yaw(inot)
[2015]	2063
[1819]	2064	ENDIF
	2065	ENDIF
	2066
[1864]	2067	ENDDO !-- end of loop over turbines
	2068
	2069	!
[1929]	2070	!-- Transfer of information to the other cpus
	2071	#if defined( __parallel )
[1864]	2072	CALL MPI_ALLREDUCE( u_inflow_l, u_inflow, nturbines, MPI_REAL, &
	2073	MPI_SUM, comm2d, ierr )
	2074	CALL MPI_ALLREDUCE( wdir_l, wdir, nturbines, MPI_REAL, MPI_SUM, &
	2075	comm2d, ierr )
	2076	CALL MPI_ALLREDUCE( phi_yaw_l, phi_yaw, nturbines, MPI_REAL, &
	2077	MPI_SUM, comm2d, ierr )
[1929]	2078	#else
	2079	u_inflow = u_inflow_l
	2080	wdir = wdir_l
	2081	phi_yaw = phi_yaw_l
[2015]	2082
	2083
[1929]	2084	#endif
[1819]	2085	DO inot = 1, nturbines
[1864]	2086	!
	2087	!-- Update rotor orientation
	2088	CALL wtm_rotate_rotor( inot )
[1819]	2089
	2090	ENDDO ! End of loop over turbines
	2091
	2092	END IF
[1864]	2093
	2094	IF ( speed_control ) THEN
	2095	!
	2096	!-- Transfer of information to the other cpus
[1912]	2097	! CALL MPI_ALLREDUCE( omega_gen, omega_gen_old, nturbines, &
	2098	! MPI_REAL,MPI_SUM, comm2d, ierr )
[1929]	2099	#if defined( __parallel )
[1864]	2100	CALL MPI_ALLREDUCE( torque_gen, torque_gen_old, nturbines, &
	2101	MPI_REAL, MPI_SUM, comm2d, ierr )
	2102	CALL MPI_ALLREDUCE( omega_rot_l, omega_rot, nturbines, &
	2103	MPI_REAL, MPI_SUM, comm2d, ierr )
[1912]	2104	CALL MPI_ALLREDUCE( omega_gen_f, omega_gen_f_old, nturbines, &
	2105	MPI_REAL, MPI_SUM, comm2d, ierr )
[1929]	2106	#else
	2107	torque_gen_old = torque_gen
	2108	omega_rot = omega_rot_l
	2109	omega_gen_f_old = omega_gen_f
	2110	#endif
[1864]	2111
	2112	ENDIF
[1819]	2113
	2114	DO inot = 1, nturbines
	2115
	2116	IF ( myid == 0 ) THEN
	2117	IF ( openfile_turb_mod(400+inot)%opened ) THEN
	2118	WRITE ( 400+inot, 106 ) simulated_time, omega_rot(inot), &
[1912]	2119	omega_gen(inot), torque_gen_old(inot), &
[1864]	2120	torque_total(inot), pitch_add(inot), &
[1912]	2121	torque_gen_old(inot)omega_gen(inot)gen_eff, &
[1864]	2122	torque_total(inot)omega_rot(inot)air_dens, &
[1912]	2123	thrust_rotor(inot), &
[1864]	2124	wdir(inot)*180.0_wp/pi, &
	2125	(phi_yaw(inot))*180.0_wp/pi
[1912]	2126
[1819]	2127	ELSE
	2128
	2129	WRITE ( turbine_id,'(I2.2)') inot
[1864]	2130	OPEN ( 400+inot, FILE=( 'TURBINE_PARAMETERS'//turbine_id ), &
	2131	FORM='FORMATTED' )
[1819]	2132	WRITE ( 400+inot, 105 ) inot
	2133	WRITE ( 400+inot, 106 ) simulated_time, omega_rot(inot), &
[1912]	2134	omega_gen(inot), torque_gen_old(inot), &
[1864]	2135	torque_total(inot), pitch_add(inot), &
[1912]	2136	torque_gen_old(inot)omega_gen(inot)gen_eff, &
[1864]	2137	torque_total(inot)omega_rot(inot)air_dens, &
[1912]	2138	thrust_rotor(inot), &
[1864]	2139	wdir(inot)*180.0_wp/pi, &
	2140	(phi_yaw(inot))*180.0_wp/pi
[1819]	2141	ENDIF
	2142	ENDIF
	2143
[1912]	2144	!-- Set open flag
[1819]	2145	openfile_turb_mod(400+inot)%opened = .TRUE.
[1864]	2146	ENDDO !-- end of loop over turbines
[1819]	2147
	2148	ENDIF
	2149
[1864]	2150	CALL cpu_log( log_point_s(61), 'wtm_forces', 'stop' )
[1819]	2151
[1912]	2152	!
	2153	!-- Formats
[1819]	2154	105 FORMAT ('Turbine control data for turbine ',I2,1X,':'/ &
	2155	&'----------------------------------------'/ &
	2156	&' Time RSpeed GSpeed ', &
[1912]	2157	'GenTorque AeroTorque Pitch Power(Gen) Power(Rot) ', &
	2158	'RotThrust WDirection YawOrient')
[1819]	2159
[1864]	2160	106 FORMAT (F9.3,2X,F7.3,2X,F7.2,2X,F9.1,3X,F9.1,1X,F6.2,2X,F10.1,2X, &
	2161	F10.1,1X,F9.1,2X,F7.2,1X,F7.2)
[1819]	2162
	2163
	2164	END SUBROUTINE wtm_forces
	2165
	2166
[1839]	2167	!------------------------------------------------------------------------------!
	2168	! Description:
	2169	! ------------
	2170	!> Yaw controller for the wind turbine model
	2171	!------------------------------------------------------------------------------!
	2172	SUBROUTINE wtm_yawcontrol( inot )
	2173
[1819]	2174	USE constants
	2175	USE kinds
[1839]	2176
	2177	IMPLICIT NONE
[1819]	2178
	2179	INTEGER(iwp) :: inot
	2180	INTEGER(iwp) :: i_wd_30
	2181	REAL(wp) :: missal
	2182
	2183	i_wd_30 = 0_iwp
	2184
	2185	!
[1864]	2186	!-- The yaw controller computes a 30s running mean of the wind direction.
	2187	!-- If the difference between turbine alignment and wind direction exceeds
	2188	!-- 5Â°, the turbine is yawed. The mechanism stops as soon as the 2s-running
	2189	!-- mean of the missalignment is smaller than 0.5Â°.
	2190	!-- Attention: If the timestep during the simulation changes significantly
	2191	!-- the lengths of the running means change and it does not correspond to
	2192	!-- 30s/2s anymore.
	2193	!-- ! Needs to be modified for these situations !
	2194	!-- For wind from the east, the averaging of the wind direction could cause
	2195	!-- problems and the yaw controller is probably flawed. -> Routine for
	2196	!-- averaging needs to be improved!
	2197	!
	2198	!-- Check if turbine is not yawing
[1819]	2199	IF ( .NOT. doyaw(inot) ) THEN
[1843]	2200	!
[1864]	2201	!-- Write current wind direction into array
[1843]	2202	wd30_l = wd30(inot,:)
	2203	wd30_l = CSHIFT( wd30_l, SHIFT=-1 )
[1819]	2204	wd30_l(1) = wdir(inot)
[1843]	2205	!
[1864]	2206	!-- Check if array is full ( no more dummies )
[1819]	2207	IF ( .NOT. ANY( wd30_l == 999.) ) THEN
	2208
	2209	missal = SUM( wd30_l ) / SIZE( wd30_l ) - phi_yaw(inot)
	2210	!
[1864]	2211	!-- Check if turbine is missaligned by more than max_miss
[1843]	2212	IF ( ABS( missal ) > max_miss ) THEN
	2213	!
[1864]	2214	!-- Check in which direction to yaw
[1843]	2215	yawdir(inot) = SIGN( 1.0_wp, missal )
[1819]	2216	!
[1864]	2217	!-- Start yawing of turbine
[1843]	2218	phi_yaw(inot) = phi_yaw(inot) + yawdir(inot) * yaw_speed * dt_3d
[1819]	2219	doyaw(inot) = .TRUE.
[1864]	2220	wd30_l = 999. ! fill with dummies again
[1819]	2221	ENDIF
	2222	ENDIF
	2223
	2224	wd30(inot,:) = wd30_l
	2225
	2226	!
[1864]	2227	!-- If turbine is already yawing:
	2228	!-- Initialize 2 s running mean and yaw until the missalignment is smaller
	2229	!-- than min_miss
[1819]	2230
	2231	ELSE
	2232	!
	2233	!-- Initialize 2 s running mean
	2234	wd2_l = wd2(inot,:)
[1864]	2235	wd2_l = CSHIFT( wd2_l, SHIFT = -1 )
[1819]	2236	wd2_l(1) = wdir(inot)
[1843]	2237	!
[1864]	2238	!-- Check if array is full ( no more dummies )
	2239	IF ( .NOT. ANY( wd2_l == 999.0_wp ) ) THEN
	2240	!
	2241	!-- Calculate missalignment of turbine
[1819]	2242	missal = SUM( wd2_l - phi_yaw(inot) ) / SIZE( wd2_l )
[1864]	2243	!
	2244	!-- Check if missalignment is still larger than 0.5 degree and if the
	2245	!-- yaw direction is still right
	2246	IF ( ( ABS( missal ) > min_miss ) .AND. &
	2247	( yawdir(inot) == SIGN( 1.0_wp, missal ) ) ) THEN
	2248	!
	2249	!-- Continue yawing
	2250	phi_yaw(inot) = phi_yaw(inot) + yawdir(inot) * yaw_speed * dt_3d
[1819]	2251	ELSE
[1864]	2252	!
	2253	!-- Stop yawing
[1819]	2254	doyaw(inot) = .FALSE.
[1864]	2255	wd2_l = 999.0_wp ! fill with dummies again
[1819]	2256	ENDIF
	2257	ELSE
[1864]	2258	!
	2259	!-- Continue yawing
[1843]	2260	phi_yaw(inot) = phi_yaw(inot) + yawdir(inot) * yaw_speed * dt_3d
[1819]	2261	ENDIF
	2262
	2263	wd2(inot,:) = wd2_l
	2264
	2265	ENDIF
	2266
[1839]	2267	END SUBROUTINE wtm_yawcontrol
[1819]	2268
[1864]	2269
[1819]	2270	!------------------------------------------------------------------------------!
	2271	! Description:
	2272	! ------------
[1864]	2273	!> Initialization of the speed control
	2274	!------------------------------------------------------------------------------!
	2275	SUBROUTINE wtm_init_speed_control
	2276
	2277
	2278	IMPLICIT NONE
	2279
	2280	!
	2281	!-- If speed control is set, remaining variables and control_parameters for
	2282	!-- the control algorithm are calculated
	2283	!
	2284	!-- Calculate slope constant for region 15
	2285	slope15 = ( slope2 * min_reg2 * min_reg2 ) / ( min_reg2 - min_reg15 )
	2286	!
	2287	!-- Calculate upper limit of slipage region
	2288	vs_sysp = rated_genspeed / 1.1_wp
	2289	!
	2290	!-- Calculate slope of slipage region
	2291	slope25 = ( rated_power / rated_genspeed ) / &
	2292	( rated_genspeed - vs_sysp )
	2293	!
	2294	!-- Calculate lower limit of slipage region
	2295	min_reg25 = ( slope25 - SQRT( slope25 * ( slope25 - 4.0_wp * &
	2296	slope2 * vs_sysp ) ) ) / &
	2297	( 2.0_wp * slope2 )
	2298	!
	2299	!-- Frequency for the simple low pass filter
	2300	Fcorner = 0.25_wp
	2301	!
	2302	!-- At the first timestep the torque is set to its maximum to prevent
	2303	!-- an overspeeding of the rotor
	2304	torque_gen_old(:) = max_torque_gen
	2305
	2306	END SUBROUTINE wtm_init_speed_control
	2307
	2308
	2309	!------------------------------------------------------------------------------!
	2310	! Description:
	2311	! ------------
	2312	!> Simple controller for the regulation of the rotor speed
	2313	!------------------------------------------------------------------------------!
	2314	SUBROUTINE wtm_speed_control( inot )
	2315
	2316
	2317	IMPLICIT NONE
	2318
[1912]	2319	INTEGER(iwp) :: inot
	2320
	2321
[1864]	2322
	2323	!
	2324	!-- The controller is based on the fortran script from Jonkman
	2325	!-- et al. 2009 "Definition of a 5 MW Reference Wind Turbine for
	2326	!-- offshore system developement"
	2327
	2328	!
	2329	!-- The generator speed is filtered by a low pass filter
	2330	!-- for the control of the generator torque
	2331	lp_coeff = EXP( -2.0_wp * 3.14_wp * dt_3d * Fcorner )
[1912]	2332	omega_gen_f(inot) = ( 1.0_wp - lp_coeff ) * omega_gen(inot) + lp_coeff *&
[1864]	2333	omega_gen_f_old(inot)
	2334
	2335	IF ( omega_gen_f(inot) <= min_reg15 ) THEN
	2336	!
	2337	!-- Region 1: Generator torque is set to zero to accelerate the rotor:
	2338	torque_gen(inot) = 0
	2339
	2340	ELSEIF ( omega_gen_f(inot) <= min_reg2 ) THEN
	2341	!
	2342	!-- Region 1.5: Generator torque is increasing linearly with rotor speed:
	2343	torque_gen(inot) = slope15 * ( omega_gen_f(inot) - min_reg15 )
	2344
	2345	ELSEIF ( omega_gen_f(inot) <= min_reg25 ) THEN
	2346	!
	2347	!-- Region 2: Generator torque is increased by the square of the generator
	2348	!-- speed to keep the TSR optimal:
	2349	torque_gen(inot) = slope2 * omega_gen_f(inot) * omega_gen_f(inot)
	2350
	2351	ELSEIF ( omega_gen_f(inot) < rated_genspeed ) THEN
	2352	!
	2353	!-- Region 2.5: Slipage region between 2 and 3:
	2354	torque_gen(inot) = slope25 * ( omega_gen_f(inot) - vs_sysp )
	2355
	2356	ELSE
	2357	!
	2358	!-- Region 3: Generator torque is antiproportional to the rotor speed to
	2359	!-- keep the power constant:
	2360	torque_gen(inot) = rated_power / omega_gen_f(inot)
	2361
	2362	ENDIF
	2363	!
	2364	!-- Calculate torque rate and confine with a max
	2365	trq_rate = ( torque_gen(inot) - torque_gen_old(inot) ) / dt_3d
	2366	trq_rate = MIN( MAX( trq_rate, -1.0_wp * max_trq_rate ), max_trq_rate )
	2367	!
	2368	!-- Calculate new gen torque and confine with max torque
	2369	torque_gen(inot) = torque_gen_old(inot) + trq_rate * dt_3d
	2370	torque_gen(inot) = MIN( torque_gen(inot), max_torque_gen )
	2371	!
	2372	!-- Overwrite values for next timestep
[1912]	2373	omega_rot_l(inot) = omega_gen(inot) / gear_ratio
[1864]	2374
	2375
	2376	END SUBROUTINE wtm_speed_control
	2377
	2378
	2379	!------------------------------------------------------------------------------!
	2380	! Description:
	2381	! ------------
[1839]	2382	!> Application of the additional forces generated by the wind turbine on the
	2383	!> flow components (tendency terms)
	2384	!> Call for all grid points
[1819]	2385	!------------------------------------------------------------------------------!
	2386	SUBROUTINE wtm_tendencies( component )
	2387
[1839]	2388
[1819]	2389	IMPLICIT NONE
	2390
[1839]	2391	INTEGER(iwp) :: component !< prognostic variable (u,v,w)
	2392	INTEGER(iwp) :: i !< running index
	2393	INTEGER(iwp) :: j !< running index
	2394	INTEGER(iwp) :: k !< running index
[1819]	2395
	2396
	2397	SELECT CASE ( component )
	2398
	2399	CASE ( 1 )
	2400	!
	2401	!-- Apply the x-component of the force to the u-component of the flow:
[1864]	2402	IF ( simulated_time >= time_turbine_on ) THEN
[1819]	2403	DO i = nxlg, nxrg
	2404	DO j = nysg, nyng
	2405	DO k = nzb_u_inner(j,i)+1, k_hub(1) + k_smear(1)
	2406	!
[1864]	2407	!-- Calculate the thrust generated by the nacelle and the tower
[1912]	2408	tend_nac_x = 0.5_wp * nac_cd_surf(k,j,i) * &
[1819]	2409	SIGN( u(k,j,i)**2 , u(k,j,i) )
[1912]	2410	tend_tow_x = 0.5_wp * tow_cd_surf(k,j,i) * &
[1819]	2411	SIGN( u(k,j,i)**2 , u(k,j,i) )
	2412
[1912]	2413	tend(k,j,i) = tend(k,j,i) - rot_tend_x(k,j,i) &
	2414	- tend_nac_x - tend_tow_x
[1819]	2415	ENDDO
	2416	ENDDO
	2417	ENDDO
	2418	ENDIF
	2419
	2420	CASE ( 2 )
	2421	!
	2422	!-- Apply the y-component of the force to the v-component of the flow:
[1864]	2423	IF ( simulated_time >= time_turbine_on ) THEN
[1819]	2424	DO i = nxlg, nxrg
	2425	DO j = nysg, nyng
	2426	DO k = nzb_v_inner(j,i)+1, k_hub(1) + k_smear(1)
[1912]	2427	tend_nac_y = 0.5_wp * nac_cd_surf(k,j,i) * &
[1819]	2428	SIGN( v(k,j,i)**2 , v(k,j,i) )
[1912]	2429	tend_tow_y = 0.5_wp * tow_cd_surf(k,j,i) * &
[1819]	2430	SIGN( v(k,j,i)**2 , v(k,j,i) )
[1912]	2431	tend(k,j,i) = tend(k,j,i) - rot_tend_y(k,j,i) &
	2432	- tend_nac_y - tend_tow_y
[1819]	2433	ENDDO
	2434	ENDDO
	2435	ENDDO
	2436	ENDIF
	2437
	2438	CASE ( 3 )
	2439	!
	2440	!-- Apply the z-component of the force to the w-component of the flow:
[1864]	2441	IF ( simulated_time >= time_turbine_on ) THEN
[1819]	2442	DO i = nxlg, nxrg
	2443	DO j = nysg, nyng
	2444	DO k = nzb_w_inner(j,i)+1, k_hub(1) + k_smear(1)
[1912]	2445	tend(k,j,i) = tend(k,j,i) - rot_tend_z(k,j,i)
[1819]	2446	ENDDO
	2447	ENDDO
	2448	ENDDO
	2449	ENDIF
	2450
	2451
	2452	CASE DEFAULT
	2453
	2454	WRITE( message_string, * ) 'unknown prognostic variable: ', component
	2455	CALL message( 'wtm_tendencies', 'PA04??', 1, 2, 0, 6, 0 )
	2456
	2457	END SELECT
	2458
	2459
	2460	END SUBROUTINE wtm_tendencies
	2461
	2462
	2463	!------------------------------------------------------------------------------!
	2464	! Description:
	2465	! ------------
[1839]	2466	!> Application of the additional forces generated by the wind turbine on the
	2467	!> flow components (tendency terms)
	2468	!> Call for grid point i,j
[1819]	2469	!------------------------------------------------------------------------------!
	2470	SUBROUTINE wtm_tendencies_ij( i, j, component )
	2471
	2472
	2473	IMPLICIT NONE
	2474
[1839]	2475	INTEGER(iwp) :: component !< prognostic variable (u,v,w)
	2476	INTEGER(iwp) :: i !< running index
	2477	INTEGER(iwp) :: j !< running index
	2478	INTEGER(iwp) :: k !< running index
[1819]	2479
	2480	SELECT CASE ( component )
	2481
	2482	CASE ( 1 )
	2483	!
	2484	!-- Apply the x-component of the force to the u-component of the flow:
[1839]	2485	IF ( simulated_time >= time_turbine_on ) THEN
[1819]	2486
	2487	DO k = nzb_u_inner(j,i)+1, k_hub(1) + k_smear(1)
	2488	!
[1839]	2489	!-- Calculate the thrust generated by the nacelle and the tower
[1912]	2490	tend_nac_x = 0.5_wp * nac_cd_surf(k,j,i) * &
[1819]	2491	SIGN( u(k,j,i)**2 , u(k,j,i) )
[1912]	2492	tend_tow_x = 0.5_wp * tow_cd_surf(k,j,i) * &
[1819]	2493	SIGN( u(k,j,i)**2 , u(k,j,i) )
[1912]	2494	tend(k,j,i) = tend(k,j,i) - rot_tend_x(k,j,i) &
	2495	- tend_nac_x - tend_tow_x
[1819]	2496	ENDDO
	2497	ENDIF
	2498
	2499	CASE ( 2 )
	2500	!
	2501	!-- Apply the y-component of the force to the v-component of the flow:
[1839]	2502	IF ( simulated_time >= time_turbine_on ) THEN
[1819]	2503	DO k = nzb_v_inner(j,i)+1, k_hub(1) + k_smear(1)
[1912]	2504	tend_nac_y = 0.5_wp * nac_cd_surf(k,j,i) * &
[1819]	2505	SIGN( v(k,j,i)**2 , v(k,j,i) )
[1912]	2506	tend_tow_y = 0.5_wp * tow_cd_surf(k,j,i) * &
[1819]	2507	SIGN( v(k,j,i)**2 , v(k,j,i) )
[1912]	2508	tend(k,j,i) = tend(k,j,i) - rot_tend_y(k,j,i) &
	2509	- tend_nac_y - tend_tow_y
[1819]	2510	ENDDO
	2511	ENDIF
	2512
	2513	CASE ( 3 )
	2514	!
	2515	!-- Apply the z-component of the force to the w-component of the flow:
[1839]	2516	IF ( simulated_time >= time_turbine_on ) THEN
[1819]	2517	DO k = nzb_w_inner(j,i)+1, k_hub(1) + k_smear(1)
[1912]	2518	tend(k,j,i) = tend(k,j,i) - rot_tend_z(k,j,i)
[1819]	2519	ENDDO
	2520	ENDIF
	2521
	2522
	2523	CASE DEFAULT
	2524
	2525	WRITE( message_string, * ) 'unknown prognostic variable: ', component
	2526	CALL message( 'wtm_tendencies', 'PA04??', 1, 2, 0, 6, 0 )
	2527
	2528	END SELECT
	2529
	2530
	2531	END SUBROUTINE wtm_tendencies_ij
	2532
	2533	END MODULE wind_turbine_model_mod

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