Create a Disk Model
After creating an actuator disk, you'll need to set the physical model so that it has an effect on the flow field.
Select the disk from the Geometry > Surfaces section.
In the properties panel, scroll down to the Physical Model section and click Add.
Select + Disk Model to create a new model, or select an existing disk model from the list. If creating a new model, this will create a Disk Model entity under the Physical Models section of the control panel and open the disk model settings in the properties panel.
Select the type of disk model you wish to use. Each one is explained in detail below.
Click in the Disks box at the bottom of the properties panel to select which disks to apply this behavior to. You can click on disks in the 3D Viewer or select them from Geometry > Surfaces.
Uniform Thrust
The Uniform Thrust model allows you to set a Thrust force that is equally distributed across an actuator disk in the direction of its normal vector.
When you select this model, you will need to specify a Disk Thrust value.
Radial Distribution
The Radial Distribution model allows you to set radially varying profiles for thrust, torque, and radial force across an actuator disk by uploading an Aero File.
When you select this model, you will need to do the following:
Click Upload File to upload an Aero File containing the non-dimensional profiles of forces and moments across the disk. If you have previously uploaded a file, you can also select that existing file here.
Set the Disk Thrust, Disk Torque, and Radial Force for the entire disk. The actual profiles of these quantities across the disk will then be calculated by re-scaling the numbers in the aero file to match these integrated totals. This functionality allows you re-use the same profiles with different totals, or to remove certain forces by setting their totals to zero.
Note:
Because the profiles in your aero file are non-dimensional, they will be re-scaled according to the integrated totals of thrust, torque and radial forces on the disk. See Aero Files for more details.
A positive value for the total torque will mean that the torque vector points in the same direction as the disk's normal vector. With this normal vector pointing towards the screen, the swirl (rotational velocity induced on the flow) will appear to move in the clockwise direction.
Aero Files
These files must be in a comma-separated value format (CSV), with each line of the file containing four values, in this order:
Radial position (as a fraction of the total radius)
Non-dimensional thrust profile
Non-dimensional torque profile
Non-dimensional radial force profile
Important:
The final value on each line should not be followed by a comma. If the first line of the file is text, such as the headers of the following columns, it will be ignored.
The size of the file is limited to a maximum of 10MB, and you will be alerted if any errors are discovered on upload.
After successful upload, you’ll see sparklines showing the overall shapes of the force distributions. If you subsequently want to remove/replace this file, you can click the small X to its right to delete it.
Blade Element Theory
Blade Element Theory uses tables of airfoil aerodynamic data to model the forces across a disk. This allows you to model a propeller or rotor based on the real shape and movement of its blades together with knowledge of the aerodynamic coefficients of its airfoil cross sections under different angles of attack and Mach numbers. This information is used to create thrust, azimuthal, and radial forces to apply to the flow field.
When you select this model:
Set the Blade Count (number of rotor or propeller blades) to model and the Rotation Rate in radians per second.
Upload a Blade Geometry file. Learn more about this file below.
Add an Airfoil, then set the r/R radial position. You can add additional airfoils as needed.
Upload a Performance file for each airfoil. Learn more about this file below.
(Optional) Set the Pitch Schedule for the blades. This schedule dynamically alters the pitch of the blades as they rotate about the hub. Schedules are defined by the first harmonic (a constant, a cosine coefficient, and a sine coefficient) in blade azimuth. The zero azimuth is set to the positive x direction by default (or the positive z direction when the disk normal is parallel to the x axis).
Note: A positive value for Rotation Rate means that with the disk's normal vector pointing towards you from the screen, the swirl (rotational velocity induced on the flow) will appear to move in the anti-clockwise direction. In this case, the torque vector will point in the opposite direction to this normal vector.
If modeling a constant density flow, you will also need to input a reference Sound Speed. This number is used to calculate the Mach number along the blade. While under the assumption of constant density the Mach number will be zero, the tips of a rotor will likely be moving at a significant fraction of the speed of sound, and calculating their Mach number improves the accuracy of results.
Blade Geometry File
The blade geometry file must be in CSV format, with each line of the file containing five values:
Radial position as a fraction of the total radius
Twist in degrees (the angle between the airfoil chord line and the plane of the actuator disk at the current position)
Sweep in degrees (the angle between the lines defined by adjacent quarter chord positions and the disk center to blade root in the plane of the actuator disk at the current position, with a positive value meaning sweep backwards from the direction of rotation)
Anhedral in degrees (the angle between the lines defined by adjacent quarter chord positions and the disk center to blade root in the plane normal to the disk at the current position).
Relative chord (the airfoil chord length at the current station divided by the outer radius of the disk) at each station along the blade.
Important: The final value on each line should not be followed by a comma. If the first line of the file is text, such as the headers of the following columns, it will be ignored.
Performance File
The Performance file must be in C81 or LC81 format (Luminary's own version of the format) and include the lift, drag, and pitching moment coefficients for an airfoil with a range of angles of attack and Mach number.
If you only create one airfoil, the associated performance file is used for every location along the blade.
If you create multiple airfoils, the file used will depend on the r/R radial position of each airfoil. From 0 until the first airfoil location, the file used will be for that first airfoil. From the last airfoil location until r/R equals 1, the file used will be from that last airfoil. Radial positions between two airfoils will use data linearly interpolated from the files for the two airfoils.
Alternatively, Luminary will also read in Continuum Dynamics’ CHARM airfoil performance data input files.
Important: The size of these files is limited to a maximum of 10MB, and you will be alerted if any errors are discovered on upload.
After a successful upload, you’ll see sparklines showing the overall shapes of the geometries or coefficient distributions. Selecting between Degree [°] and Mach will show sparklines with respect to angle of attack or Mach number, respectively, but does not affect the simulation.
Example C81 File
Example C81 File
NACA 0015 735 735 735
0.000 0.050 0.100 0.200 0.300 0.400 0.500
-180.0 -0.001 -0.001 -0.003 -0.004 -0.004 -0.003 -0.002
-170.0 0.392 0.392 0.373 0.353 0.338 0.327 0.321
-120.0 0.533 0.533 0.524 0.529 0.545 0.556 0.569
-110.0 0.342 0.342 0.333 0.336 0.348 0.339 0.316
-100.0 0.108 0.108 0.100 0.100 0.108 0.083 0.042
-90.0 -0.134 -0.134 -0.140 -0.140 -0.134 -0.137 -0.151
-80.0 -0.351 -0.351 -0.358 -0.360 -0.355 -0.339 -0.331
-70.0 -0.589 -0.589 -0.596 -0.601 -0.600 -0.589 -0.585
-60.0 -0.777 -0.777 -0.786 -0.793 -0.795 -0.788 -0.784
-16.0 -1.116 -1.116 -1.156 -1.146 -1.076 -0.656 -0.602
-14.0 -1.118 -1.118 -1.148 -1.172 -1.181 -0.848 -0.675
-12.0 -1.025 -1.025 -1.046 -1.070 -1.095 -0.955 -0.840
-10.0 -0.890 -0.890 -0.906 -0.927 -0.953 -0.938 -0.920
-8.0 -0.731 -0.731 -0.743 -0.760 -0.782 -0.804 -0.822
-6.0 -0.559 -0.559 -0.568 -0.581 -0.598 -0.620 -0.639
-4.0 -0.377 -0.377 -0.383 -0.392 -0.404 -0.419 -0.440
-2.0 -0.190 -0.190 -0.193 -0.198 -0.204 -0.212 -0.223
0.0 0.001 0.001 0.000 0.000 0.000 0.000 0.000
2.0 0.190 0.190 0.193 0.198 0.204 0.212 0.223
4.0 0.377 0.377 0.383 0.392 0.404 0.419 0.440
6.0 0.559 0.559 0.568 0.581 0.598 0.620 0.639
8.0 0.731 0.731 0.743 0.760 0.782 0.804 0.822
10.0 0.890 0.890 0.906 0.927 0.953 0.938 0.920
12.0 1.025 1.025 1.046 1.070 1.095 0.955 0.840
14.0 1.118 1.118 1.148 1.172 1.181 0.848 0.561
16.0 1.116 1.116 1.156 1.146 1.076 0.571 0.602
60.0 0.777 0.777 0.786 0.793 0.795 0.788 0.784
70.0 0.589 0.589 0.596 0.601 0.600 0.589 0.517
80.0 0.351 0.351 0.358 0.360 0.355 0.341 0.240
90.0 0.134 0.134 0.140 0.140 0.134 0.163 0.133
100.0 -0.108 -0.108 -0.100 -0.100 -0.108 -0.053 0.012
110.0 -0.342 -0.342 -0.333 -0.336 -0.348 -0.307 -0.260
120.0 -0.533 -0.533 -0.524 -0.529 -0.545 -0.556 -0.569
170.0 -0.392 -0.392 -0.373 -0.353 -0.338 -0.327 -0.321
180.0 0.001 0.001 0.003 0.004 0.004 0.003 0.002
0.000 0.050 0.100 0.200 0.300 0.400 0.500
-180.0 0.017 0.017 0.015 0.014 0.014 0.013 0.014
-170.0 0.084 0.084 0.082 0.082 0.083 0.086 0.090
-120.0 1.226 1.226 1.220 1.232 1.251 1.254 1.262
-110.0 1.370 1.370 1.365 1.376 1.387 1.387 1.358
-100.0 1.405 1.405 1.405 1.413 1.409 1.369 1.269
-90.0 1.533 1.533 1.533 1.544 1.525 1.447 1.294
-80.0 1.406 1.406 1.408 1.414 1.408 1.360 1.282
-70.0 1.381 1.381 1.379 1.387 1.396 1.382 1.374
-60.0 1.240 1.240 1.238 1.248 1.259 1.260 1.265
-16.0 0.077 0.077 0.072 0.075 0.089 0.161 0.196
-14.0 0.052 0.052 0.050 0.049 0.053 0.096 0.133
-12.0 0.040 0.040 0.038 0.038 0.039 0.053 0.073
-10.0 0.031 0.031 0.030 0.029 0.030 0.034 0.042
-8.0 0.024 0.024 0.023 0.022 0.022 0.024 0.027
-6.0 0.019 0.019 0.018 0.017 0.017 0.017 0.019
-4.0 0.015 0.015 0.014 0.013 0.013 0.013 0.013
-2.0 0.013 0.013 0.011 0.011 0.010 0.010 0.010
0.0 0.012 0.012 0.011 0.010 0.009 0.009 0.009
2.0 0.013 0.013 0.011 0.011 0.010 0.010 0.010
4.0 0.015 0.015 0.014 0.013 0.013 0.013 0.013
6.0 0.019 0.019 0.018 0.017 0.017 0.017 0.019
8.0 0.024 0.024 0.023 0.022 0.022 0.024 0.027
10.0 0.031 0.031 0.030 0.029 0.030 0.034 0.042
12.0 0.040 0.040 0.038 0.038 0.039 0.053 0.073
14.0 0.052 0.052 0.050 0.049 0.053 0.096 0.138
16.0 0.077 0.077 0.072 0.075 0.089 0.170 0.196
60.0 1.240 1.240 1.238 1.248 1.259 1.260 1.265
70.0 1.381 1.381 1.379 1.387 1.396 1.382 1.349
80.0 1.406 1.406 1.408 1.414 1.408 1.300 1.121
90.0 1.533 1.533 1.533 1.544 1.525 1.274 0.939
100.0 1.405 1.405 1.405 1.413 1.409 1.248 0.963
110.0 1.370 1.370 1.365 1.376 1.387 1.331 1.201
120.0 1.226 1.226 1.220 1.232 1.251 1.254 1.262
170.0 0.084 0.084 0.082 0.082 0.083 0.086 0.090
180.0 0.017 0.017 0.015 0.014 0.014 0.013 0.014
0.000 0.050 0.100 0.200 0.300 0.400 0.500
-180.0 -0.000 -0.000 -0.001 -0.001 -0.001 -0.001 -0.000
-170.0 0.287 0.287 0.284 0.280 0.277 0.275 0.277
-120.0 0.506 0.506 0.510 0.514 0.515 0.507 0.500
-110.0 0.495 0.495 0.500 0.503 0.500 0.510 0.523
-100.0 0.460 0.460 0.466 0.469 0.462 0.471 0.480
-90.0 0.452 0.452 0.456 0.459 0.451 0.446 0.433
-80.0 0.375 0.375 0.379 0.381 0.378 0.370 0.361
-70.0 0.349 0.349 0.352 0.355 0.356 0.351 0.351
-60.0 0.302 0.302 0.305 0.308 0.310 0.310 0.311
-16.0 -0.022 -0.022 -0.025 -0.024 -0.017 0.053 0.043
-14.0 -0.031 -0.031 -0.032 -0.033 -0.036 -0.007 0.010
-12.0 -0.027 -0.027 -0.026 -0.027 -0.029 -0.037 -0.035
-10.0 -0.021 -0.021 -0.020 -0.020 -0.021 -0.030 -0.045
-8.0 -0.015 -0.015 -0.014 -0.015 -0.015 -0.017 -0.027
-6.0 -0.010 -0.010 -0.010 -0.009 -0.010 -0.010 -0.015
-4.0 -0.006 -0.006 -0.006 -0.005 -0.006 -0.006 -0.007
-2.0 -0.003 -0.003 -0.002 -0.002 -0.002 -0.003 -0.003
0.0 -0.000 -0.000 -0.000 -0.000 -0.000 -0.000 -0.000
2.0 0.003 0.003 0.002 0.002 0.002 0.003 0.003
4.0 0.006 0.006 0.006 0.005 0.006 0.006 0.007
6.0 0.010 0.010 0.010 0.009 0.010 0.010 0.015
8.0 0.015 0.015 0.014 0.015 0.015 0.017 0.027
10.0 0.021 0.021 0.020 0.020 0.021 0.030 0.045
12.0 0.027 0.027 0.026 0.027 0.029 0.037 0.035
14.0 0.031 0.031 0.032 0.033 0.036 0.007 -0.044
16.0 0.022 0.022 0.025 0.024 0.017 -0.067 -0.043
60.0 -0.302 -0.302 -0.305 -0.308 -0.310 -0.310 -0.311
70.0 -0.349 -0.349 -0.352 -0.355 -0.356 -0.351 -0.316
80.0 -0.375 -0.375 -0.379 -0.381 -0.378 -0.352 -0.275
90.0 -0.452 -0.452 -0.456 -0.459 -0.451 -0.406 -0.323
100.0 -0.460 -0.460 -0.466 -0.469 -0.462 -0.449 -0.415
110.0 -0.495 -0.495 -0.500 -0.503 -0.500 -0.506 -0.490
120.0 -0.506 -0.506 -0.510 -0.514 -0.515 -0.507 -0.500
170.0 -0.287 -0.287 -0.284 -0.280 -0.277 -0.275 -0.277
180.0 0.000 0.000 0.001 0.001 0.001 0.001 0.000
Example LC81 File
Example LC81 File
C_L ,0.000,0.050,0.100,0.200,0.300,0.400,0.500
-180.0,-0.001,-0.001,-0.003,-0.004,-0.004,-0.003,-0.002
-170.0,0.392,0.392,0.373,0.353,0.338,0.327,0.321
-120.0,0.533,0.533,0.524,0.529,0.545,0.556,0.569
-110.0,0.342,0.342,0.333,0.336,0.348,0.339,0.316
-100.0,0.108,0.108,0.100,0.100,0.108,0.083,0.042
-90.0,-0.134,-0.134,-0.140,-0.140,-0.134,-0.137,-0.151
-80.0,-0.351,-0.351,-0.358,-0.360,-0.355,-0.339,-0.331
-70.0,-0.589,-0.589,-0.596,-0.601,-0.600,-0.589,-0.585
-60.0,-0.777,-0.777,-0.786,-0.793,-0.795,-0.788,-0.784
-16.0,-1.116,-1.116,-1.156,-1.146,-1.076,-0.656,-0.602
-14.0,-1.118,-1.118,-1.148,-1.172,-1.181,-0.848,-0.675
-12.0,-1.025,-1.025,-1.046,-1.070,-1.095,-0.955,-0.840
-10.0,-0.890,-0.890,-0.906,-0.927,-0.953,-0.938,-0.920
-8.0,-0.731,-0.731,-0.743,-0.760,-0.782,-0.804,-0.822
-6.0,-0.559,-0.559,-0.568,-0.581,-0.598,-0.620,-0.639
-4.0,-0.377,-0.377,-0.383,-0.392,-0.404,-0.419,-0.440
-2.0,-0.190,-0.190,-0.193,-0.198,-0.204,-0.212,-0.223
0.0,0.001,0.001,0.000,0.000,0.000,0.000,0.000
2.0,0.190,0.190,0.193,0.198,0.204,0.212,0.223
4.0,0.377,0.377,0.383,0.392,0.404,0.419,0.440
6.0,0.559,0.559,0.568,0.581,0.598,0.620,0.639
8.0,0.731,0.731,0.743,0.760,0.782,0.804,0.822
10.0,0.890,0.890,0.906,0.927,0.953,0.938,0.920
12.0,1.025,1.025,1.046,1.070,1.095,0.955,0.840
14.0,1.118,1.118,1.148,1.172,1.181,0.848,0.561
16.0,1.116,1.116,1.156,1.146,1.076,0.571,0.602
60.0,0.777,0.777,0.786,0.793,0.795,0.788,0.784
70.0,0.589,0.589,0.596,0.601,0.600,0.589,0.517
80.0,0.351,0.351,0.358,0.360,0.355,0.341,0.240
90.0,0.134,0.134,0.140,0.140,0.134,0.163,0.133
100.0,-0.108,-0.108,-0.100,-0.100,-0.108,-0.053,0.012
110.0,-0.342,-0.342,-0.333,-0.336,-0.348,-0.307,-0.260
120.0,-0.533,-0.533,-0.524,-0.529,-0.545,-0.556,-0.569
170.0,-0.392,-0.392,-0.373,-0.353,-0.338,-0.327,-0.321
180.0,0.001,0.001,0.003,0.004,0.004,0.003,0.002
C_D ,0.000,0.050,0.100,0.200,0.300,0.400,0.500
-180.0,0.017,0.017,0.015,0.014,0.014,0.013,0.014
-170.0,0.084,0.084,0.082,0.082,0.083,0.086,0.090
-120.0,1.226,1.226,1.220,1.232,1.251,1.254,1.262
-110.0,1.370,1.370,1.365,1.376,1.387,1.387,1.358
-100.0,1.405,1.405,1.405,1.413,1.409,1.369,1.269
-90.0,1.533,1.533,1.533,1.544,1.525,1.447,1.294
-80.0,1.406,1.406,1.408,1.414,1.408,1.360,1.282
-70.0,1.381,1.381,1.379,1.387,1.396,1.382,1.374
-60.0,1.240,1.240,1.238,1.248,1.259,1.260,1.265
-16.0,0.077,0.077,0.072,0.075,0.089,0.161,0.196
-14.0,0.052,0.052,0.050,0.049,0.053,0.096,0.133
-12.0,0.040,0.040,0.038,0.038,0.039,0.053,0.073
-10.0,0.031,0.031,0.030,0.029,0.030,0.034,0.042
-8.0,0.024,0.024,0.023,0.022,0.022,0.024,0.027
-6.0,0.019,0.019,0.018,0.017,0.017,0.017,0.019
-4.0,0.015,0.015,0.014,0.013,0.013,0.013,0.013
-2.0,0.013,0.013,0.011,0.011,0.010,0.010,0.010
0.0,0.012,0.012,0.011,0.010,0.009,0.009,0.009
2.0,0.013,0.013,0.011,0.011,0.010,0.010,0.010
4.0,0.015,0.015,0.014,0.013,0.013,0.013,0.013
6.0,0.019,0.019,0.018,0.017,0.017,0.017,0.019
8.0,0.024,0.024,0.023,0.022,0.022,0.024,0.027
10.0,0.031,0.031,0.030,0.029,0.030,0.034,0.042
12.0,0.040,0.040,0.038,0.038,0.039,0.053,0.073
14.0,0.052,0.052,0.050,0.049,0.053,0.096,0.138
16.0,0.077,0.077,0.072,0.075,0.089,0.170,0.196
60.0,1.240,1.240,1.238,1.248,1.259,1.260,1.265
70.0,1.381,1.381,1.379,1.387,1.396,1.382,1.349
80.0,1.406,1.406,1.408,1.414,1.408,1.300,1.121
90.0,1.533,1.533,1.533,1.544,1.525,1.274,0.939
100.0,1.405,1.405,1.405,1.413,1.409,1.248,0.963
110.0,1.370,1.370,1.365,1.376,1.387,1.331,1.201
120.0,1.226,1.226,1.220,1.232,1.251,1.254,1.262
170.0,0.084,0.084,0.082,0.082,0.083,0.086,0.090
180.0,0.017,0.017,0.015,0.014,0.014,0.013,0.014
C_M ,0.000,0.050,0.100,0.200,0.300,0.400,0.500
-180.0,0.000,0.000,-0.001,-0.001,-0.001,-0.001,0.000
-170.0,0.287,0.287,0.284,0.280,0.277,0.275,0.277
-120.0,0.506,0.506,0.510,0.514,0.515,0.507,0.500
-110.0,0.495,0.495,0.500,0.503,0.500,0.510,0.523
-100.0,0.460,0.460,0.466,0.469,0.462,0.471,0.480
-90.0,0.452,0.452,0.456,0.459,0.451,0.446,0.433
-80.0,0.375,0.375,0.379,0.381,0.378,0.370,0.361
-70.0,0.349,0.349,0.352,0.355,0.356,0.351,0.351
-60.0,0.302,0.302,0.305,0.308,0.310,0.310,0.311
-16.0,-0.022,-0.022,-0.025,-0.024,-0.017,0.053,0.043
-14.0,-0.031,-0.031,-0.032,-0.033,-0.036,-0.007,0.010
-12.0,-0.027,-0.027,-0.026,-0.027,-0.029,-0.037,-0.035
-10.0,-0.021,-0.021,-0.020,-0.020,-0.021,-0.030,-0.045
-8.0,-0.015,-0.015,-0.014,-0.015,-0.015,-0.017,-0.027
-6.0,-0.010,-0.010,-0.010,-0.009,-0.010,-0.010,-0.015
-4.0,-0.006,-0.006,-0.006,-0.005,-0.006,-0.006,-0.007
-2.0,-0.003,-0.003,-0.002,-0.002,-0.002,-0.003,-0.003
0.0,0.000,0.000,0.000,0.000,0.000,0.000,0.000
2.0,0.003,0.003,0.002,0.002,0.002,0.003,0.003
4.0,0.006,0.006,0.006,0.005,0.006,0.006,0.007
6.0,0.010,0.010,0.010,0.009,0.010,0.010,0.015
8.0,0.015,0.015,0.014,0.015,0.015,0.017,0.027
10.0,0.021,0.021,0.020,0.020,0.021,0.030,0.045
12.0,0.027,0.027,0.026,0.027,0.029,0.037,0.035
14.0,0.031,0.031,0.032,0.033,0.036,0.007,-0.044
16.0,0.022,0.022,0.025,0.024,0.017,-0.067,-0.043
60.0,-0.302,-0.302,-0.305,-0.308,-0.310,-0.310,-0.311
70.0,-0.349,-0.349,-0.352,-0.355,-0.356,-0.351,-0.316
80.0,-0.375,-0.375,-0.379,-0.381,-0.378,-0.352,-0.275
90.0,-0.452,-0.452,-0.456,-0.459,-0.451,-0.406,-0.323
100.0,-0.460,-0.460,-0.466,-0.469,-0.462,-0.449,-0.415
110.0,-0.495,-0.495,-0.500,-0.503,-0.500,-0.506,-0.490
120.0,-0.506,-0.506,-0.510,-0.514,-0.515,-0.507,-0.500
170.0,-0.287,-0.287,-0.284,-0.280,-0.277,-0.275,-0.277
180.0,0.000,0.000,0.001,0.001,0.001,0.001,0.000
LC81 Format
The LC81 format is Luminary's own, simplified, version of the C81 file format. It differs from a traditional C81 in that:
No header is required
Values are comma-separated
Tables are separated by text or a blank space (any non-float character)
The file should contain three tables: lift coefficient, drag coefficient, and pitching moment.
C81 Format
The C81 file does not use commas or spaces to separate values, but instead reserves specific numbers of characters for each piece of data.
The first line starts with a 30-character space reserved for the airfoil name or designation.
Immediately following that are six two-digit integers that represent how many columns and rows are in each table.
In order these are:
Number of Mach numbers and angles of attack in the lift table
Number of Mach numbers and angles of attack in the drag table
Number of Mach numbers and angles of attack in the pitching moment table
The rest of the file contains three tables: lift coefficient, drag coefficient, and pitching moment coefficient, respectively. There is no separator between tables, and so the drag coefficient table, for example, will begin on the data line immediately following the last data line of the lift coefficient table.
Every data line is made up of 10 spaces of seven characters, and table rows can span multiple lines in the file. Lines that begin a header row start with seven blank spaces followed by up to nine Mach number values. Lines that begin subsequent rows start with the angle of attack followed by up to nine coefficient values. And lines that are a continuation of either the header row or subsequent rows begin with seven blank spaces followed by up to nine Mach number or coefficient values. Each Mach number, angle of attack or coefficient value is a floating-point number of exactly seven characters, including minus signs, decimal points and blank spaces.
For more information about the structure of .C81 files see Appendix A from Jason Stanko’s 2017 thesis “Automated Design and Evaluation of Airfoils for Rotorcraft Applications.”
Fan
With the Fan model, you can upload a fan curve table and incorporate a fan's effect on the flow without modeling detailed fan blades. A fan curve is a statistical description of a fan's performance, typically provided by the fan manufacturer, that provides the relationship between flow rate and pressure across the fan.
Your fan curve file must be in CSV format and contain the following columns, in this order:
Volume Flow Rate (m3/s)
Pressure Rise (Pa)
When you select the Fan model, you'll need to:
Upload a Fan Curve table.
Specify the Head Loss Coefficient, or the fraction of dynamic pressure lost through the fan.
Select disks to apply the model to.
You can upload multiple CSV files to switch fan curves between simulations by unlinking the current file, then clicking on the dropdown and selecting Upload File.
