ASE 362K - HW 9 - Problem 5. Consider the airfoil shown...

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ASE 362K Problem Set #9 Clemens / Spring 2010 Due: Friday, May 7 Problem 1. Anderson Prob. 9.2. Problem 2. Anderson Prob. 9.3. Problem 3. Anderson Prob. 9.11 Problem 4. A Mach 3 flow of air flows past a wall as shown. The flow is isentropic and irrotational. A bump on the wall is thin enough that the flow can be treated with linearized theory. The bump has a shape given by the function 01 . 0 2 + = x y , which is valid between -0.1 < x < 0.1. Both x and y have units of meters . (a) What is the net force per unit span that acts on the bump in the x -direction? (b) What is the minimum temperature in the flowfield? (c) Estimate the Mach number at the location in the flow where (x=0.1, y=0.05).
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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.

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ASE 362K - HW 9 - Problem 5. Consider the airfoil shown...

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