source: palm/trunk/TESTS/cases/wind_turbine_model/INPUT/wind_turbine_model_p3d @ 4447

Last change on this file since 4447 was 4447, checked in by oliver.maas, 4 years ago

renamed wind_turbine_parameters namelist variables

File size: 1.7 KB
RevLine 
[4056]1 &initialization_parameters
2         nx = 63, ny = 63, nz = 64,
3   
4         dx = 15.0, dy = 15.0, dz = 15.0,
5
6         bc_lr = 'cyclic',
7         bc_ns = 'cyclic',
8
9         initializing_actions = 'set_constant_profiles',
10         ug_surface = 6.0, vg_surface = 0.0,
11
12         bc_uv_b = 'dirichlet',
13         fft_method = 'temperton-algorithm',
14         
15         constant_flux_layer = .F., /
16
17 &runtime_parameters
[4069]18         end_time = 60.0,
[4056]19         
20         create_disturbances = .T.,
21         
22         dt_run_control = 0.,
23         
[4069]24         dt_dopr = 20.0,
[4056]25         
26         data_output_pr = '#u', '#v',
27                          'u*2', 'v*2', 'w*2',
28           
[4069]29         mask_x_loop(1,:) = 200.0, 800.0, 15.0,
30         mask_y_loop(1,:) = 200.0, 800.0, 15.0,
31         mask_z_loop(1,:) = 400.0, 560.0, 30.0,
[4056]32         
33         data_output_masks(1,:) = 'u', 'v','w',
34
35         dt_domask = 20.,/
36
37 &wind_turbine_parameters
38         time_turbine_on  = 1.0,
39
[4447]40         n_turbines = 4,
41         hub_x =   300.0, 600.0, 300.0, 600.0,
42         hub_y =   300.0, 300.0, 600.0, 600.0,
43         hub_z =   480.0, 480.0, 480.0, 480.0,
44         rotor_radius  =    63.0, 63.0, 63.0, 63.0,
45         nacelle_radius =    1.5, 1.5, 1.5, 1.5,
46         tower_diameter =    4.0, 4.0, 4.0, 4.0,
[4056]47
[4447]48         rotor_speed = 0.9, 0.9, 0.9, 0.9,
49         yaw_angle = -20.0, 10.0, 0.0, 30.0,
50         tilt_angle = 0.0,
51         generator_power_rated = 5296610.0,
[4056]52         speed_control = .T.,
53         pitch_control = .T.,
[4447]54         pitch_angle = 0.0,
[4056]55         yaw_control = .T.,
56         yaw_speed = 0.01,
57   
[4447]58         tower_cd   = 1.2, 1.2, 1.2, 1.2,
[4056]59       
[4447]60         segment_length_tangential = 1.0,
61         segment_width_radial  = 0.5,
[4056]62       
[4447]63         n_airfoils = 8, /
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