AEROSP 225 Lecture Notes - Lecture 36: Wind Tunnel, Supersonic Wind Tunnel, Perfect Gas

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

Document Summary

The u-m atmospheric inflow supersonic wind-tunnel has a square 100. 0 x 100. 0 mm2 cross sectional area at the sonic point when the test section mach number is near its minimum value of 1. 30. If to=300. 0 k, po=100. 0 kpa, =1. 40, r=287 j/kg-k, find the mass flow rate (kg/s). Example 36. 2 supersonic wind tunnel has a cross sectional area of 582 x 100. 0 mm2. Find the mach number of the flow in this component for the conditions of example 33. 1. The mercury rocket engine has nozzle inlet, throat, and exit diameters of 530. 0, 340. 0, and 740. 0 mm, respectively. The stagnation pressure and temperature at the nozzle inlet are 2300. 0 kpa and 2380 k. the gas flowing in the nozzle can be approximated as a perfect gas with a molecular weight of. 24. 1 g/mol and a specific heat ratio of 1. 20. The exit of the air storage of the u-m atmospheric-inflow (a) the static and stagnation pressures (kpa) and temperatures (k), the.