Aerospace Engineering Laboratory:
Cold Gas Thruster:
Charles O'Neill
1st March 2001
A compressible flow supersonic nozzle using Nitrogen is experimentally tested. A
shadowgraph visualization system is setup. Specific impulse calculations are performed
from theoretical and experimental data. Compressible flow equations are reviewed.
Includes shadowgraph photos of Prandtl-Meyer fans aft of a nozzle.
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| Supersonic Nozzle Operating Above Design Pressure (250psi) with P-M waves |
The document is available here. This was an undergraduate laboratory experiment.
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