Consider a thin, symmetric airfoil at 1.5 angle of attack. From the results of thin airfoil theory,

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Consider a thin, symmetric airfoil at 1.5° angle of attack. From the results of thin airfoil theory, calculate the lift coefficient and the moment coefficient about the leading edge.

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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 a thin, symmetric airfoil at 1.5 angle of attack. From the results of thin airfoil theory,

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Fundamentals of Aerodynamics

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