Unformatted text preview: 3 Consider the problem o± shock refection ±rom a fat wall. The refection ±rom regions 2 to 3 happens because in region 3 the fow must become parallel to the upper wall. ²or the conFguration shown above ( M 1 = 4, θ = 20 o ), Fnd M and p in regions 2 and 3. Consider the “weak solution” only. PROBLEM 3 (10 points) y x 1 M 1 = 2 y i x i y= 0.1 x 2 M An isentropic compression turn occurs ±or 0 ≤ x ≤ 1 and has the shape y = 0 . 1 x 2 No ±urther turning occurs ±or x > 1. The incoming Mach number is M 1 = 2. (a) Calculate the coordinates ( x i , y i ) o± the intersection o± the Frst and last Mach waves o± the compression. (b) Determine the Mach number M 2 downstream o± the isentropic compression 1...
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 Spring '08
 staff
 Aerodynamics, Mach number, Turn, Shock wave, 20 deg, 10deg

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