AN ANALYTICAL STUDY OF THE SUPERSONIC COMPRESSOR AS A MEANS OF OBTAINING HYPERSONIC FLOW SIMULATION AT LOW ALTITUDES

A study of the potentialities of the supersonic compressor as a means of obtaining hypersonic flow simulation at low altitudes is presented. For compressors operating at tip speeds of about 2000 fps., an optimum simulation exists at a compressor supply temperature of about 600 K and an inlet Mach nu...

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Bibliographic Details
Main Authors: Makofski, R A, Dickens, W P
Format: Report
Language:English
Subjects:
ADIABATIC GAS FLOW
AERODYNAMIC HEATING
COMPRESSIBLE FLOW
CONFIGURATIONS
ENTHALPY
FRICTION
FUNCTIONAL ANALYSIS
HEAT TRANSFER
HYPERSONIC FLIGHT
HYPERSONIC FLOW
HYPERSONIC WIND TUNNELS
LOW ALTITUDE
MATHEMATICAL ANALYSIS
ROTARY COMPRESSORS
SIMULATION
SUPERSONIC FLOW
SURFACES
TEST FACILITIES
TURBULENCE
TURBULENT BOUNDARY LAYER
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Summary:A study of the potentialities of the supersonic compressor as a means of obtaining hypersonic flow simulation at low altitudes is presented. For compressors operating at tip speeds of about 2000 fps., an optimum simulation exists at a compressor supply temperature of about 600 K and an inlet Mach number of 2. This optimum provides true temperature, sea level simulation at a test Mach number of 9. (Author)