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5- The lift slope for an airfoil is 0.1123 degree-, and az-o = -0.8. Consider a finite wing using this airfoil, with AR =
5- The lift slope for an airfoil is 0.1123 degree-, and az-o = -0.8. Consider a finite wing using this airfoil, with AR = 6 and taper ratio = 0.8. Assume that 6 = T. Calculate the lift coefficient and induced drag coefficients for this wing at a angle of attack of 6. 18P MOTANDS URU (as) 8 0.16 0.12 0.08 0.04 0 0.2 0.4 0.6 Taper ratio, c,/e, AR-10 0.8 1.0
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Fundamentals of Aerodynamics
Authors: J. Anderson
2nd Edition
978-0071254083, 1259129918, 71254080, 70016798, 9781259129919, 978-0070016798
