The Application of Cryogenic Pumping in a High-Mass-Flow System
The requirement for simulated high-altitude testing of propulsion systems is complicated by the extremely high volume pumping rates required for even a small mass flow of propeliant gases. To obtain reasonable model sizes, a pumping capacity of one to two million cubic feet per min may be required. One approach to this problem is the Cold Wall Vacuum Chamber constructed at the Propulsion Wind Tunnel Facility, Arnold Engineering Development Center, Propulsion problems are investigated in this chamber by using carbon dioxide to simulate the rocket propeliant gas and using the liquid-nitrogen-cooled surfaces of the chamber to provide the pumping capacity by cryopumping.
KeywordsTotal Temperature Specific Heat Ratio Total Pressure Ratio Transition Flow Regime Capture Coefficient
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