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Unformatted text preview: 650:460 Aerodynamics Homework Assignment No. 8 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 Problem 8.13 You are to measure the surface pressure on a simple model in a supersonic wind tunnel. The air flows from right to left. To evaluate the experimental accuracy, it is necessary to obtain theoretical pressures for comparison with the data. If a 30 ◦ wedge is to be placed in a Mach 3.5 stream, calculate a) the surface pressure (N/m 2 ), b) the pressure difference (in mm Hg) between the presssure experienced by the wedge surface and the wall (which measures p ∞ ), and c) the dynamic pressure of the freestream flow. Solution For δ = 30 ◦ , θ = 47 . 75 ◦ from (8.71) or Fig. 8.12 Thus, all ratios across the shock can be determined in terms of θ , M 1 and γ = 1 . 4. 2 Problem 8.13 Thus p 2 p 1 = 7 . 665 using (8.72) T 2 T 2 = 2 . 229 using (8.74) ρ 2 ρ 1 = 3 . 439 using (8.73) M 2 = 1 . 655 using (8.75) p t 2 p t 1 = 0 . 464 using (8.76) 3 Problem 8.13 Since the stagnation pressure p t 1 = 6 . · 10 5 Pa, thus p 1 = p t 1 bracketleftBig 1 + ( γ − 1) 2 M 2 1 bracketrightBig γ/ ( γ − 1) = 7 . 867 · 10 3 Pa and thus the surface pressure is p 2 = (7...
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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.
 Spring '09
 Knight

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