AEROSP 225 Lecture Notes - Lecture 32: Stagnation Temperature, Mach Wave, Vacuum Chamber

• School: U of M
• Department: Aerospace Engineering
• Course: AEROSP 225
• Professor: Mirko Gamba

Document Summary

Given m1=1, 1=0o , po1=100 kpa, to1=300 k, and 2=10o, (a) the static and stagnation temperature (k) and pressures (kpa), the. Mach number and the mach angle (deg) in region 1. (b) repeat (a) for region 2. (c) the angle (deg) between the leading and trailing waves of the prandtl- The stagnation pressure and temperature of the flow are 200 kpa and. 400 k, the mach number at the passage exit is 2, and the pressure in the vacuum chamber is 15 kpa. A supersonic flow with a mach number of 2 flows between parallel walls. At a point, the lower wall turns at an expansion angle of 4o.