quiz-solution11

# quiz-solution11 - 650:460 Aerodynamics Quiz No 11 Solution...

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Unformatted text preview: 650:460 Aerodynamics Quiz No. 11 - Solution Prof. Doyle Knight Tel: 732 445 4464, Email: [email protected] Oﬃce hours: Tues and Thur, 4:30 pm - 6:00 pm and by appointment Fall 2009 1 Quiz No. 11 Consider the two dimensional airfoil shown in the ﬁgure. The √ freestream Mach number M∞ = 5 and the angle of attack α = 5◦ . The angle δ = 2.5◦ . Calculate the axial force coeﬃcient ca using linear theory. 2 Quiz No. 11 Solution The lift coeﬃcient is cl = The drag coeﬃcient is cd = Now 2 σu 4α 2 M∞ − 1 = 0.1745 4α2 2 M∞ −1 2 + 2 2 M∞ −1 c 2 σu + σl2 = σl2 1 = c c o dz dx dx = 1 c (tan δ )2 dx = tan2 δ o 3 Quiz No. 11 Thus cd = 1.904 · 10−2 From geometry, ca = cd cos α − cl sin α = 3.76 · 10−3 4 ...
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## This note was uploaded on 12/15/2009 for the course 650 460 taught by Professor Knight during the Spring '09 term at Rutgers.

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quiz-solution11 - 650:460 Aerodynamics Quiz No 11 Solution...

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