Accession Number : AD0816591

Title :   A SHOCK-ON-SHOCK TEST FACILITY.

Descriptive Note : Technical information series,

Corporate Author : GENERAL ELECTRIC CO PHILADELPHIA PA MISSILE AND SPACE DIV

Personal Author(s) : Harris, Clarence J. ; Warren, W. R. ; Pridgen, Robert G.

Report Date : OCT 1966

Pagination or Media Count : 19

Abstract : In current re-entry technology as well as in supersonic aircraft evaluation studies there is interest in the effects which occur when a strong aerodynamic wave traverses and reflects from a vehicle in supersonic or hypersonic flight. To study this problem experimentally in the laboratory an existing combustion driver shock tunnel has been converted into a heated blow down wind tunnel - normal blast wave generator shock-on-shock test facility. This facility has been used to obtain shock interaction surface pressure data on sting mounted and wire supported models. The test facility configuration and the approach used present unique operational features. This paper reports on the basic facility design approaches and concepts considered, the actual conversion of the shock tunnel into a shock-on-shock test facility, and the resulting performance of this facility. Also presented are shock-on-shock model surface transient pressure results obtained using this facility. (Author)

Descriptors :   (*SHOCK TUBES, AERODYNAMICS), (*REENTRY VEHICLES, SHOCK WAVES), (*SUPERSONIC AIRCRAFT, SHOCK WAVES), REFLECTION, SUPERSONIC FLIGHT, HYPERSONIC FLIGHT, TEST FACILITIES, PRESSURE, INTERACTIONS, AERODYNAMIC CHARACTERISTICS, SONIC BOOM, TRANSPORT PROPERTIES, NOSE CONES, HYPERSONIC CHARACTERISTICS, SUPERSONIC CHARACTERISTICS.

Subject Categories : Test Facilities, Equipment and Methods
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE