Accession Number : AD0631647

Title :   A PRELIMINARY STUDY OF SHOCK-DUCT DIFFUSERS IN A HYPERSONIC HELIUM TUNNEL,

Corporate Author : JOHNS HOPKINS UNIV SILVER SPRING MD APPLIED PHYSICS LAB

Personal Author(s) : Makofski,R. A. ; Rea,S. N.

Report Date : JAN 1963

Pagination or Media Count : 35

Abstract : Tests of a fixed geometry shock-duct diffuser were conducted using helium at supply pressures from 400 to 1000 psia and Mach numbers from 16 to 18. The tests were made in a blow-down tunnel having a 12-degree conical nozzle with a 2-inch exit diameter. Pitot pressures were measured in the test section and at the diffuser exit. These studies have shown that this type of diffuser could provide a pressure recovery equivalent to test section pitot pressure. Furthermore, the pressure recovery was found to be dependent upon the diffuser inlet angle and Reynolds number and only weakly dependent upon the shock-duct diameter. Values of diffuser efficiency of 53 per cent were obtained. (Author)

Descriptors :   (*HYPERSONIC WIND TUNNELS, *DIFFUSERS), SHOCK WAVES, HELIUM, WIND TUNNEL NOZZLES, PRESSURE, PITOT TUBES, REYNOLDS NUMBER, DUCTS

Subject Categories : Test Facilities, Equipment and Methods
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE