Accession Number : AD0735744

Title :   Measurements of Heat Transfer Rates Behind Axially Symmetric Backward Facing Steps in the Shock Tube and the Shock Tunnel.

Descriptive Note : Final scientific rept. (Part 3),

Corporate Author : TECHNION - ISRAEL INST OF TECH HAIFA DEPT OF AERONAUTICAL ENGINEERING

Personal Author(s) : Green,Michael ; Rom,Josef

Report Date : MAY 1971

Pagination or Media Count : 78

Abstract : Measurements of heat transfer rates on cone-cylinder models and in the separated regions behind an axially symmetric backward facing step are reported. The measurements were obtained in the shock tube at flow Mach numbers between 1.4 to 2.5. The heat transfer in the separated region is studied for variation of the flow Mach number from the supersonic values obtained in the shock tube to the hypersonic value obtained in the shock tunnel. The position of the maximum heating rate is noted for step height and forebody length. It is found that the point of maximum heating moves downstream with increasing step height while increasing forebody length causes an upstream movement of this point.

Descriptors :   (*HYPERSONIC WIND TUNNELS, HEAT TRANSFER), MODEL TESTS, CONICAL BODIES, CYLINDRICAL BODIES, ANALYSIS OF VARIANCE, AERODYNAMIC CONFIGURATIONS, ENTHALPY, ISRAEL

Subject Categories : Test Facilities, Equipment and Methods

Distribution Statement : APPROVED FOR PUBLIC RELEASE