For the steady flow around a flat plate airfoil without thickness at small angle of attack, try

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For the steady flow around a flat plate airfoil without thickness at small angle of attack, try to prove that the concentrated vortex is arranged at 1/4 chord and the boundary condition is satisfied at 3/4 chord.

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Aerodynamics

ISBN: 9789811945861

1st Edition

Authors: Peiqing Liu

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Question Posted: Apr 29, 2024 06:00 AM

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For the steady flow around a flat plate airfoil without thickness at small angle of attack, try

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Aerodynamics

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