A flat plate airfoil with chord C = 1.2 m is to have a lift of 30

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A flat plate airfoil with chord C = 1.2 m is to have a lift of 30 kN/m when flying at 5000-m standard altitude with U∞ = 641 m/s. Using Ackeret theory, estimate
(a) The angle of attack; and
(b) The drag force in N/m.
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Principles of heat transfer

ISBN: 978-0495667704

7th Edition

Authors: Frank Kreith, Raj M. Manglik, Mark S. Bohn

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