Hello,
I am working on a project to design a composite experimental plane. One of the challenges I face is to determine the chord load distribution of the wing. I have used the shrenk approximation method and openvsp results to obtain the wing lift distribution . I have also interpolated the cp values from the xflr5 2d analysis, but I am not sure how to convert them into force. I would appreciate any guidance or suggestions on how to solve this problem.
Thank you for your attention.
I am working on a project to design a composite experimental plane. One of the challenges I face is to determine the chord load distribution of the wing. I have used the shrenk approximation method and openvsp results to obtain the wing lift distribution . I have also interpolated the cp values from the xflr5 2d analysis, but I am not sure how to convert them into force. I would appreciate any guidance or suggestions on how to solve this problem.
Thank you for your attention.
