AEROSP 225 Lecture Notes - Lecture 39: Isentropic Process, Supersonic Wind Tunnel, Heat Capacity

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

Document Summary

A small rocket thruster is to be designed to provide control. Stagnation temperature: 2,000 k (does not change with operating condition) The nozzle flow is one-dimensional, steady, adiabatic and frictionless; the momentum at the engine inlet is small, and the gas is a perfect gas. Do the following: (a) calculate the design point static pressure (kpa) and temperature (k), Example 39. 2 supersonic wind tunnel has a test section of area 100x100 mm2 and a stagnation pressure and temperature of 100 kpa and 300 k, respectively. The working fluid is air that can be assumed to be a perfect gas with a specific heat ratio of 1. 40 and a gas constant of 287 j/kg-k. The flow through the nozzle can be assumed to be one-dimensional, steady, adiabatic and frictionless. For the nozzle configuration and inlet conditions of example. 39. 2, find the nozzle exit conditions at the transition between flow regimes i and.