Dear Mohamed,
What input perturbation have you applied to the linear model? Does the output from your linear model match that of the nonlinear model when no input perturbations to the linear model are specified, such that all states, state derivatives, and input perturbations are zero? This should be the case because the output perturbations from the linear model are then zero, and when the periodic OP is added the perturbation, the result should match the nonlinear model.
Best regards,
Dear Jason
Thank you for your explanation.
However, I found less deviation between the linearized model and the nonlinear model, although I set all perturbations to zeros. I add the periodic OPs that are retrieved from the linearization txt file (*.lin). The operating conditions of the nonlinear model are the same as the linearization point. Moreover, I made another simulation with accounting the periodicity of A, B, C, and D matrices, but, it gives me the same results.
The Blade RootMFlp1 VS Simulation time ( kN.m VS seconds).
The yellow line for the nonlinear model. The blue line for the linear model.
The connection diagram is shown below
Regards
M.Fekry
Dear Mohamed,
I still have not fully understood your Simulink model, but if the perturbations zero, then the linear and nonlinear model should agree if the OP from the linear model is derived from the conditions of the nonlinear model. Are you adding the periodic OP to perturbation (which are all zeros for now) when comparing the linear and nonlinear models, including inputs, states, and outputs?
Best regards,
Dear Dr. Jason
The connection diagram of the Simulink is shown below:
Continuing from above
However, The RootMFlp1, RootMFlp2, and RootMFlp3 have some deviation as shown below:
RootMFlp1 kN.m VS Time S
Are there any precautions should I take when dealing with C and D matrices?
Regards
M.Fekry
Dear Mohamed,
Are the perturbed outputs from the linear model (dy = Cdx + Ddu) all zero? From your Simulink model (Linear Model Diagram.jpg), it still looks like you are adding Xop to dx before multiplying it by C.
And where is the periodic OP of the blade flapwise outputs added to the perturbed outputs from the linear model, i.e., y = yop(Azimuth) + dy, after transformation of dy from the nonrotating to the rotating frame? Given that dy in your case should be zero (both rotating and nonrotating), the blade flapwise output from the linear model should just be the OP value, which should match the nonlinear model.
Best regards,
Dr. Jason
Thank you very much for your explanation
it works now.
RootMFlp1 kN.m VS Time S
Dear Jonkman,
First, thank your help on topic “Obtaining sensitivity of aerodynamic power to rotor-collective blade pitch”, I have successfully gotten the data. My version is OPENFAST 2.4.
However, I have some questions.
First, what is the difference between AD RtAeroPwr and ED RotPwr. Maybe the GenEff 94.4 in ServoDyn? I compared them in linearization files. They are not the relation about GenEff.
Second, I looked at the sensitivity of them to rotor-collective blade pith. For ED RotPwr, it is -5.904E+03. For AD RtAeroPwr, it is -5.134E+07. Owing to their units, one is KW, the other is W, so I think the sensitivity of them should differ 10^3, but it is nearly 10^4 now. I am a litter puzzled.
Could you please help me?
Best regards!
Dear Dezheng.Zhu,
A similar question was asked and answered in the following forum topic: FAST_v8.15 OutList parameters - #2 by Jason.Jonkman.
If the generator or drivetrain DOFs are enabled in ElastoDyn, I would expect large differences in the derivatives calculated from a linearization analysis between RotPwr from ElastoDyn and RtAeroPwr from AeroDyn because the former is effected by rotor acceleration/deceleration while the later is not. If the generator and drivetrain DOFs are disabled in ElastoDyn, then I would expect quite good agreement between the two.
Best regards,
Dear @Jason.Jonkman,
I am trying to linearize the onshore 5 MW reference wind turbine at a steady wind speed of 23 m/s. I have been facing some problems and I followed a debbuging process, that I will be explaining, and I would be glad if you could share your thoughts about it. The configuration I have been using can be found in this link:
First, I was receving this warning message:
"_NREL5MW_LINParametric/../5MW_Baseline/NRELOffshrBsline5MW_AeroDyn_blade.dat".
AD_Init:Init_BEMTmodule:BEMT_Init:UA_Init:UA_SetParameters:UA_ValidateAFI:File
"_NREL5MW_LINParametric/../5MW_Baseline/Airfoils/DU40_A17.dat":
The separation function f_st does not reach 1; max(f_st)=0.56668.
Check the calculation or provide f_st in the input file.
I have seen a similar issue here, and the proposed solutions are to either change the airfoil data or use a different UAMod. I got this message for all the speeds (3-25 m/s), but at the end the of the simulation I was seeing “OpenFAST terminated normally”. However, it was only when the OP was 23 m/s or higher (24 or 25 m/s) that I couldn’t apply the MBC3 to the lin files. I was getting this error message in MATLAB:
Unable to perform assignment because the size of the left side is 438-by-438 and
the size of the right side is 314-by-438.
I checked the issue and realized that the A matrix was being truncated at the 314 state variable (AD x4 blade 1, node 18, -), where it row was full of NaN. I first solved this issue by setting UAEndRad = 0.85 instead of 1, but I was still getting the first warning message.
Then, I started checking the results with UA_Mod = 5 and got the following warning messages:
AD_Init:Init_BEMTmodule:BEMT_Init:UA_Init:UA_SetParameters:UA_ValidateAFI:File
“_NREL5MW_LINParametric/../5MW_Baseline/Airfoils/DU40_A17.dat”:UA cutout parameter should be at a value where the separation function is 0; separation function is 1.29902E-02.UA_SetParameters:UA_ValidateAFI:File
“_NREL5MW_LINParametric/../5MW_Baseline/Airfoils/DU35_A17.dat”:UA cutout parameter should be at a value where the separation function is 0; separation function is 1.43151E-02.UA_SetParameters:UA_ValidateAFI:File
“_NREL5MW_LINParametric/../5MW_Baseline/Airfoils/DU30_A17.dat”:UA cutout parameter should be at a value where the separation function is 0; separation function is 1.06945E-03.
This warnings made me change the parameter UAStartRad, to avoid having UA on those airfoils. After trying some values I finally set it to 0.45. With UAStartRad = 0.45 I am able to run the linearizations without any of those warning messages and then I can apply the MBC3 without any problems.
SUMMARY:
UA_Mod = 4
UAStartRad = 0
UAEndRad = 1
“The separation function f_st does not reach 1” warning message and I can’t apply MBC3 because the matrix A gets truncated.
UA_Mod = 4
UAStartRad = 0
UAEndRad = 0.85
“The separation function f_st does not reach 1” warning message still appearing, but I can apply MBC3.
UA_Mod = 5
UAStartRad = 0
UAEndRad = 1
Second warning messages appeared, and I can apply MBC3.
UA_Mod = 5
UAStartRad = 0.45
UAEndRad = 1
No warning messages, and I can apply MBC3.
UA_Mod = 4
UAStartRad = 0.45
UAEndRad = 1
No warning messages, and I can’t apply MBC3 because the matrix A gets truncated.
Best regards,
Ignacio López
Dear @Ignacio.Lopez,
Can you clarify when you are receiving warning messages–is it during the steady-state trim solution or during the linearization process?
I see that your model is quite sophisticated, with many DOFs enabled in ElastoDyn, as well as dynamic inflow and UA enabled in AeroDyn. Do you have issues in a simpler model without aerodynamic states, e.g., DBEMT_Mod = -1 and UAMod = 0?
Best regards,
Dear @Jason.Jonkman,
I’m receiving the warning messages during the steady-state trim solution. They appear just after the simulation begins and it happens when Linearize = True and False
OpenFAST
Copyright (C) 2026 National Renewable Energy Laboratory
Copyright (C) 2026 Envision Energy USA LTD
This program is licensed under Apache License Version 2.0 and comes with ABSOLUTELY NO WARRANTY.
See the "LICENSE" file distributed with this software for details.
**************************************************************************************************
OpenFAST-v4.2.0
Compile Info:
- Compiler: GCC version 14.3.0
- Architecture: 64 bit
- Precision: single
- OpenMP: No
- Date: Jan 28 2026
- Time: 21:04:40
Execution Info:
- Date: 06/08/2026
- Time: 10:29:00+0200
OpenFAST input file heading:
FAST Certification - Test #18: NREL 5.0 MW Baseline Wind Turbine (Onshore)
Running ElastoDyn.
Nodal outputs section of ElastoDyn input file not found or improperly formatted.
Running InflowWind.
Running AeroDyn.
AeroDyn: projMod: 2
Projection: Polar, BEM: polar (3D)
Warning: Turning off Unsteady Aerodynamics because polar has constant data. (node 1, blade 1)
Warning: Turning off Unsteady Aerodynamics because polar has constant data. (node 2, blade 1)
Warning: Turning off Unsteady Aerodynamics because polar has constant data. (node 3, blade 1)
Warning: Turning off Unsteady Aerodynamics because polar has constant data. (node 4, blade 1)
Warning: Turning off Unsteady Aerodynamics because polar has constant data. (node 1, blade 2)
Warning: Turning off Unsteady Aerodynamics because polar has constant data. (node 2, blade 2)
Warning: Turning off Unsteady Aerodynamics because polar has constant data. (node 3, blade 2)
Warning: Turning off Unsteady Aerodynamics because polar has constant data. (node 4, blade 2)
Warning: Turning off Unsteady Aerodynamics because polar has constant data. (node 1, blade 3)
Warning: Turning off Unsteady Aerodynamics because polar has constant data. (node 2, blade 3)
Warning: Turning off Unsteady Aerodynamics because polar has constant data. (node 3, blade 3)
Warning: Turning off Unsteady Aerodynamics because polar has constant data. (node 4, blade 3)
Running ServoDyn.
FAST_InitializeAll:ED_Init:ED_ReadInput:ReadBladeInputs:ReadBladeFile:The ElastoDyn Blade file,
ws23_test/../5MW_Baseline/NRELOffshrBsline5MW_Blade.dat, DISTRIBUTED BLADE PROPERTIES table
contains the PitchAxis column. This column is unused and will be removed in future releases
FAST_InitializeAll:AD_Init:ReadInputFiles:Blade1:ReadBladeInputs:BlCrvAng will be calculated and
overwrite the values specified in blade file
"ws23_test/../5MW_Baseline/NRELOffshrBsline5MW_AeroDyn_blade.dat".
ReadInputFiles:Blade2:ReadBladeInputs:BlCrvAng will be calculated and overwrite the values
specified in blade file "ws23_test/../5MW_Baseline/NRELOffshrBsline5MW_AeroDyn_blade.dat".
ReadInputFiles:Blade3:ReadBladeInputs:BlCrvAng will be calculated and overwrite the values
specified in blade file "ws23_test/../5MW_Baseline/NRELOffshrBsline5MW_AeroDyn_blade.dat".
AD_Init:Init_BEMTmodule:BEMT_Init:UA_Init:UA_SetParameters:UA_ValidateAFI:File
"ws23_test/../5MW_Baseline/Airfoils/DU40_A17.dat":The separation function f_st does not reach 1;
max(f_st)=0.56668. Check the calculation or provide f_st in the input file.
Time: 0 of 600 seconds.
Time: 15 of 600 seconds. Estimated final completion at 10:32:07 (in 0.002 days).
With a simpler model without aerodynamic states (DBEMT_Mod = -1 and UAMod = 0) I don’t have any problems. I have also tried DBEMT_Mod = 3 and UAMod = 0, since DBEMT_Mod = 3 is the recommend practice according to the OpenFAST Documentation, and -1 is useful for simplified linearizations only. The moment I try to activate any unsteady aerodynamics (UAMod = 4 or 5) I get those warning messages. Reducing the number of DOFs doesn’t change anything.
Best regards,
Dear @Jason.Jonkman,
Since I need to continue with my work, is it acceptable/common practice to linearize the 5 MW wind turbine without UA (UA_Mod = 0)?
I have made a little research about the first warning:
"_NREL5MW_LINParametric/../5MW_Baseline/NRELOffshrBsline5MW_AeroDyn_blade.dat".
AD_Init:Init_BEMTmodule:BEMT_Init:UA_Init:UA_SetParameters:UA_ValidateAFI:File
"_NREL5MW_LINParametric/../5MW_Baseline/Airfoils/DU40_A17.dat":
The separation function f_st does not reach 1; max(f_st)=0.56668.
Check the calculation or provide f_st in the input file.
I’d like to share a couple of things:
Polar.py script from the openfast_toolbox and the separation function does reach 1.-180.00 | 0.00000 -175.00 | 0.00000 -170.00 | 0.00000 -160.00 | 0.00000 -155.00 | 0.00000 -150.00 | 0.00000 -145.00 | 0.00000 -140.00 | 0.00000 -135.00 | 0.00000 -130.00 | 0.00000 -125.00 | 0.00000 -120.00 | 0.00000 -115.00 | 0.00000 -110.00 | 0.00000 -105.00 | 0.00000 -100.00 | 0.00000 -95.00 | 0.00000 -90.00 | 0.00000 -85.00 | 0.00000 -80.00 | 0.00000 -75.00 | 0.00000 -70.00 | 0.00000 -65.00 | 0.00000 -60.00 | 0.00000 -55.00 | 0.00000 -50.00 | 0.00000 -45.00 | 0.00000 -40.00 | 0.00000 -35.00 | 0.00000 -30.00 | 0.00567 -25.00 | 0.02153 -24.00 | 0.02613 -23.00 | 0.03136 -22.00 | 0.03696 -21.00 | 0.04364 -20.00 | 0.05083 -19.00 | 0.05854 -18.00 | 0.06577 -17.00 | 0.07273 -16.00 | 0.07858 -15.00 | 0.08353 -14.00 | 0.08720 -13.00 | 0.08996 -12.00 | 0.09048 -11.00 | 0.08897 -10.00 | 0.08461 -8.00 | 0.06342 -6.00 | 0.03483 -5.50 | 0.03010 -5.00 | 0.03171 -4.50 | 0.09058 -4.00 | 0.22258 -3.50 | 0.04765 -3.00 | 0.04765 -2.50 | 0.00245 -2.00 | 0.19593 -1.50 | 0.48028 -1.00 | 0.03907 -0.50 | 0.00066 0.00 | 0.08165 0.50 | 0.23703 1.00 | 0.39765 1.50 | 0.53284 2.00 | 0.64278 2.50 | 0.72181 3.00 | 0.77822 3.50 | 0.82424 4.00 | 0.86429 4.50 | 0.90184 5.00 | 0.93281 5.50 | 0.95612 6.00 | 0.97697 6.50 | 0.98994 7.00 | 0.99614 7.50 | 1.00000 8.00 | 0.99849 8.50 | 0.99071 9.00 | 0.97748 9.50 | 0.96679 10.00 | 0.94155 10.50 | 0.91431 11.00 | 0.88024 11.50 | 0.84759 12.00 | 0.81740 12.50 | 0.78605 13.00 | 0.75481 13.50 | 0.73194 14.50 | 0.68965 15.00 | 0.67281 15.50 | 0.64805 16.00 | 0.62568 16.50 | 0.60384 17.00 | 0.58168 17.50 | 0.56314 18.00 | 0.54714 19.00 | 0.51205 19.50 | 0.49591 20.50 | 0.46545 21.00 | 0.44920 22.00 | 0.41679 23.00 | 0.38590 24.00 | 0.35642 25.00 | 0.32825 26.00 | 0.30180 28.00 | 0.25386 30.00 | 0.21299 32.00 | 0.17920 35.00 | 0.13770 40.00 | 0.07859 45.00 | 0.03430 50.00 | 0.00756 55.00 | 0.00019 60.00 | 0.00000 65.00 | 0.00000 70.00 | 0.00000 75.00 | 0.00000 80.00 | 0.00000 85.00 | 0.00000 90.00 | 0.00000 95.00 | 0.00000 100.00 | 0.00000 105.00 | 0.00000 110.00 | 0.00000 115.00 | 0.00000 120.00 | 0.00000 125.00 | 0.00000 130.00 | 0.00000 135.00 | 0.00000 140.00 | 0.00000 145.00 | 0.00000 150.00 | 0.00000 155.00 | 0.00000 160.00 | 0.00000 170.00 | 0.00000 175.00 | 0.00000 180.00 | 0.00000
The aforementioned Python script is throwing this warning:
[WARN] More than 20% error between estimated slope (0.1078) and the slope around alpha0 (0.0400). The window for the slope search ([-10.0 17.0]) is likely wrong.
I have also checked the following scripts: DU21_A17, DU25_A17, DU30_A17 and DU35_A17. With any of them I get that warning.
After plotting some data of the DU40_A17 airfoil I have come up with a possible reason: there is to much noise near the alpha0 region, and that’s why the script is having trouble to estimate the slope. What do you think?
Best regards,
