Lucas

Hi, Thanks for your answer. I tried to tweak this setting without clear success, I've used parameters from 20 to 60 (anything higher crashes). What I also did is visualize the lift distribution for the last angle that succesfully converged without any error and the AoA before : here for pictures The same wing with NACA2412 doesn't create issues but this NACA64210 does even if the polars calculated by the XFOIL module are good. The main difference with a NACA2412 is the higher CL it achieves (the...

Hi, Thanks for your answer. I tried to tweak this setting without clear success, I've used parameters from 20 to 60 (anything higher crashes). What I also did is visualize the lift distribution for the last angle that succesfully converged without any error and the AoA before : here for pictures The same wing with NACA2412 doesn't create issues but this NACA64210 does even if the polars calculated by the XFOIL module are good. The main difference with a NACA2412 is the higher CL it achieves. Again,...

Hi, Thanks for your answer. I tried to tweak this setting without clear success, I've used parameters from 20 to 60 (anything higher crashes). What I also did is visualize the lift distribution for the last angle that succesfully converged without any error and the AoA before : here for pictures The same wing with NACA2412 doesn't create issues but this NACA64210 does even if the polars calculated by the XFOIL module are good. Again, I know it can be done because of the technical paper that describes...

Hi, Thanks for your answer. I tried to tweak this setting without clear success, I've used parameters from 20 to 60 (anything higher crashes). What I also did is visualize the lift distribution for the last angle that succesfully converged without any error and the AoA before : The same wing with NACA2412 doesn't create issues but this NACA64210 does even if the polars calculated by the XFOIL module are good. Again, I know it can be done because of the technical paper that describes results with...

Hi, Thanks for your answer. I tried to tweak this setting without clear success, I've used parameters from 20 to 60 (anything higher crashes). What I also did is visualize the lift distribution for the last angle that succesfully converged without any error and the AoA before : The same wing with NACA2412 doesn't create issues but this NACA64210 does even if the polars calculated by the XFOIL module are good. Again, I know it can be done because of the technical paper that describes results with...

Hi, Thank you for your answer. I understand that but 2 things make me thing that there is something else : - the case I'm trying to achieve has been successfuly predicted by XFLR5 in the technical paper that I linked in my first post. - 30° apparent aoa is not physical for an angle of attack of 13.5° and it's not a low AR either (9). The problem is during iterations it reaches a temporary too high AoA but there must be a solution because of the research paper I sent. We can also talk in French if...

Hi everyone, Currently trying to reproduce an analysis in XFLR5 made in a small article (click here) Unfortunately, I can't get the exact same case to work because at some point during the LLT process the total angle of attack (due to the induced angle) of a section is 40° and off course I have no data for that angle so it could not be interpolated by XFLR5. This problem appears at 13.5 which i very far from predicted stall characteristics for this profile. What settings can I change to achieve convergence?...