Fuselage C_L values are greater than the wing (Beginner at CFD)

Kirbs

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?

rgiri

Hello,

The first thing to look as to why your solution is blowing up, is to check the Diagnostics tab of your FlightStream model. Check if there are any free edges/unwanted edges or faces (red boxes) and try to eliminate them completely.

Are there any blunt trailing edges in your wings/vertical or horizontal tails? If you can share the simulation model (*.fsm file)/ mesh files, I can provide a better assessment of what's happening.

Thanks & Regards

Ritangshu Giri