For the flow around a flat plate airfoil at a small angle of attack, try to prove

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For the flow around a flat plate airfoil at a small angle of attack, try to prove that y(0) can have the following two forms of solutions.

(1) (not met the trailing-edge condition)

(2) (met the trailing-edge condition)

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Aerodynamics

ISBN: 9789811945861

1st Edition

Authors: Peiqing Liu

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