AeroE 241              Homework 9                 Spring, 1995
A Mach = 2 supersonic wind tunnel is to be designed to have a 3 foot by 3 foot square test section, and will use air to be supplied by a reservoir at standard atmospheric temperature and 5 atmospheres absolute pressure. The nozzle is of constant width of 3 ft.

Using the 1-D compressible eqDetermine the following

  1. At the throat
    1. height, in
    2. pressure, psia
    3. temperature, R
  2. At the test section
    1. pressure, psia
    2. temperature, R
    3. speed of sound, ft/s
    4. flow speed, ft/s 
<= BACK