Abstract
A thin profile with parabolic camber \(\frac{d}{c}=0.02\) is set at angle of attack \(\alpha =5^\circ \). Find the lift coefficient \(C_{l}\) in incompressible flow. Find the lift coefficient in compressible flow at \(M_{0}=0.7\). Hint: use linear correction method.
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Chattot, J.J., Hafez, M.M. (2015). Problems. In: Theoretical and Applied Aerodynamics. Springer, Dordrecht. https://doi.org/10.1007/978-94-017-9825-9_14
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DOI: https://doi.org/10.1007/978-94-017-9825-9_14
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Online ISBN: 978-94-017-9825-9
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