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Unformatted text preview: Problem 5. Consider the airfoil shown below whose surface varies according to the sine function shown. If the airfoil is in a Mach 2 flow then use linearized theory to do the following: (a) assusming M ∞ =2 find the pressure ratio P/P ∞ , Mach number and temperature ratio T/T ∞ at point P on the surface. (b) derive a relation for the drag coefficient C D (per unit span) for the airfoil. (c) plot C D vs. M ∞ for this airfoil over the range 1.1<M ∞ <5. M ∞ =3 P ∞ = 1 atm T ∞ = 300 K x y x=0.1 x=-0.1 M ∞ P (x=0.75C) x y C y/C=0.05sin( π x/C)...
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This note was uploaded on 09/18/2011 for the course ASE 362K taught by Professor Dolling,d during the Spring '07 term at University of Texas.
- Spring '07