Air flows at Ma = 2.5 past a half wedge airfoil whose angles are 4°, as in

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Air flows at Ma = 2.5 past a half wedge airfoil whose angles are 4°, as in Fig. P9.151. Compute the lift and drag coefficients at α equal to
(a) 0°; and
(b) 6°.

Air flows at Ma = 2.5 past a half
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Heat Transfer

ISBN: 978-0073529363

10th edition

Authors: Jack Holman

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