Accession Number : AD0466489


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


Descriptive Note : Technical memo.,


Corporate Author : JOHNS HOPKINS UNIV LAUREL MD APPLIED PHYSICS LAB


Personal Author(s) : Makofski, R A ; Dickens, W P


Report Date : Apr 1965


Pagination or Media Count : 45


Abstract : 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)


Descriptors :   *ROTARY COMPRESSORS , *HYPERSONIC FLOW , *HYPERSONIC FLIGHT , HYPERSONIC WIND TUNNELS , SIMULATION , TEST FACILITIES , MATHEMATICAL ANALYSIS , HEAT TRANSFER , TURBULENCE , FRICTION , SURFACES , ENTHALPY , FUNCTIONAL ANALYSIS , SUPERSONIC FLOW , COMPRESSIBLE FLOW , TURBULENT BOUNDARY LAYER , ADIABATIC GAS FLOW , CONFIGURATIONS , AERODYNAMIC HEATING , LOW ALTITUDE


Distribution Statement : APPROVED FOR PUBLIC RELEASE