Dear developers, hello. I have encountered several issues while using your program to calculate airfoil shapes.
First, when I used the WingBase case in the tutorial folder, around time step 450, a sharp spike appeared in the CFy plot. Does this indicate that the calculation diverged?
Second, when I use my own defined airfoil in the calculation, it always diverges very easily. The passport file I used is the WingBase one, only with changes in the angle and time. Are there any points I need to pay attention to when defining my own geometry and writing the passport file?
Also, it seems that when calculating for an airfoil, I cannot obtain the velocity and pressure distributions in the flow field. Is there any way to solve this?
Finally, while studying the source code, I did not seem to find any application related to the Kutta condition. In practical calculations, what condition is used to replace it?
I look forward to your reply！
Dear developers, hello. I have encountered several issues while using your program to calculate airfoil shapes.
First, when I used the WingBase case in the tutorial folder, around time step 450, a sharp spike appeared in the CFy plot. Does this indicate that the calculation diverged?
Second, when I use my own defined airfoil in the calculation, it always diverges very easily. The passport file I used is the WingBase one, only with changes in the angle and time. Are there any points I need to pay attention to when defining my own geometry and writing the passport file?
Also, it seems that when calculating for an airfoil, I cannot obtain the velocity and pressure distributions in the flow field. Is there any way to solve this?
Finally, while studying the source code, I did not seem to find any application related to the Kutta condition. In practical calculations, what condition is used to replace it?
I look forward to your reply！