Consider an airfoil at 12 angle of attack. The normal and axial force coefficients are 1.2 and

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Consider an airfoil at 12° angle of attack. The normal and axial force coefficients are 1.2 and 0.03, respectively. Calculate the lift and drag coefficients.

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Fundamentals of Aerodynamics

ISBN: 978-0070016798

2nd Edition

Authors: J. Anderson

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Question Posted: Dec 09, 2010 03:24 AM

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Consider an airfoil at 12 angle of attack. The normal and axial force coefficients are 1.2 and

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C Cn cosa Ca 12 cos ...View the full answer

Fundamentals of Aerodynamics

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