We’re currently designing and building VTOLs, and I’m trying to validate my wing design. I created a general wing model in XFLR5, and I want to compare the results to those I’m getting in my CFD setup. I’m running an incompressible simulation with the geometry scaled to real-life size.
The issue is that my simulated lift force is about 10× higher than expected, and both the lift and drag coefficients look incorrect as well. I suspect I’ve set up the reference values wrong, but I’m not sure where the mistake is.
Here are the wing specifications for context:
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Total wingspan: 2.7 m
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Total area: 0.69 m²
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Mean aerodynamic chord: 0.288 m
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Root chord: 0.31 m
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Mass: 10 kg
If anyone has experience with reference area/chord settings in CFD (especially for XFLR5 comparison), I’d appreciate any guidance on what to double-check.