4.16) Using shock-expansion theory, calculate the lift and drag (in pounds) on a symmetrical diamond airfoil of semiangle 15 (see Fig. 4.35) at an angle of attack to the free stream of 5 when the upstream Mach number and pressure are 2.0 and 2116 l
There were two requests with this assignment. The first was to reproduce Fig. 5.15 with both the exact relations and the super-fantastic nozzle simulator. The second was to determine the pressure requirement (if any) to keep the nozzle from Lab1 pure
MAE 362 Solution HW # 5 1. [25pts] Recall that we developed normal shock relations for the limiting case of M 1 (sec 3.6). Do the same for the oblique shock relations and determine relations for P2 P , T2 T1 , , M 2 . (For completeness I'll provide 1
4.6) A supersonic stream at M 1 3.6 flows past a compression corner with a deflection angle of 20 . The incident shock wave is reflected from an opposite wall which is parallel to the upstream supersonic flow, as sketched in Fig. 4.18. Calculate the