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# solution10 - 650:460 Aerodynamics Homework Assignment No 10...

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650:460 Aerodynamics Homework Assignment No. 10 Prof. Doyle Knight Tel: 732 445 4464, Email: [email protected] OFce hours: Tues and Thur, 4:30 pm - 6:00 pm and by appointment ±all 2009 1

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Problem 10.1 Consider supersonic fow past a thin airFoil. The airFoil is symmetric about the chord line. Use linearized theory to develop expressions For the liFt coe±cient, the drag coe±cient and the pitching moment coe±cient about the midchord. The resultant expressions should include the Freestream Mach number, the constants a 1 and a 2 , and the thickness ratio τ = t / c . Show that, For a ²xed thickness ratio, the wave drag due to thickness is a minimum when a 1 = a 2 = 0 . 5. 2
Problem 10.1 The section lift coeFcient is c l = 4 α r M 2 - 1 and is independent of the cross-sectional shape of the airfoil. The section moment coeFcient is c m xo = - 4 α r M 2 - 1 p 1 2 - x o c P + 4 α r M 2 - 1 i 1 o dz c dx ( x - x o ) c d ± x c ² ±or a symmetric airfoil, z c = 0 and taking x o = c 2 , c m xo = 0 3

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Problem 10.1
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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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solution10 - 650:460 Aerodynamics Homework Assignment No 10...

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