Fuselage C_L values are greater than the wing (Beginner at CFD)
Kirbs
Altair Community Member
For Reference, This Is A School Group Project
I initially had trouble getting the model initiated through the solver. After reworking the model in SolidWorks to close all gaps and turning an assembly into a single part, simulations ran better than before. I set the values of the reference length as the length of the entire plane and the area as the estimated area from the Z-Y plane. I also tested just the fuselage with the same reference length and close to a similar location and was about to get a C_L of about 0.1, the expected value from online references.
What are the possible causes of the negative coefficient of lift and the high fuselage C_L value?
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