Prem Naik asked 11 months ago
Hello,
I have conducted a fuselage analysis using uniform and linear-density triangular panels. However, I am encountering an issue where the Cl and Cd values are consistently zero. I would appreciate guidance on how to obtain valid Cl and Cd values in my analysis.
Thank you kindly for your assistance.
1 Answers
techwinder Staff answered 11 months ago
In potential methods a fuselage does not create lift or drag. It’s d’Alembert’s paradox. Only lifting surfaces i.e. wings create lift.
André