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):

Report Date:

1965-04-01

Pagination or Media Count:

45.0

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

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE