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June 23, 2019, 13:37
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induced angle of attack in VLM
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Member
Zack
Join Date: Dec 2015
Location: uk
Posts: 35
Rep Power: 11  |
Hi,
In vortex lattice method for swept wing. Is it correct to assume that cl = a(aoa_effective) . IS the local angle of attack of at any spanwise location is a function of a lift gradient which is constant for a given aerofoil. Or that only true for unswept wing. If so, how would we calculate the effective or induced angle of attack spanwise distribution. I have tried many methods such as the one stated in Katz and the results does not seem to be correct for swept wing. My validation method is modelling a flat wing where a = 2pi cos (sweep angle). I would appreciate any help. Many thanks |
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| effective angle of attack, induced angle if attack, vlm, vortex lattice method |
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