Accession Number : AD0669328

Title :   PRESSURE DISTRIBUTION ON A CONE-CYLINDER-FLARE BODY AT MACH 14 IN THE PRESENCE OF FLOW SEPARATION.

Descriptive Note : Final rept.,

Corporate Author : AEROSPACE RESEARCH LABS WRIGHT-PATTERSON AFB OHIO

Personal Author(s) : Friberg,Eric G.

Report Date : FEB 1968

Pagination or Media Count : 61

Abstract : Surface pressure data are presented for a cone-cylinder-flare body with 20 deg and 40 deg flare angles at a nominal freestream Mach number of fourteen. Separation of the flow due to the adverse pressure gradient induced by the flare was found in both cases. Appreciable extent of separation existed in the 40 deg flare case, while for the 20 deg flare separation was less severe. A correlation formula using the viscous interaction parameter is shown to be valid for a wide range of Mach numbers and model geometries. (Author)

Descriptors :   (*FLARED AFTERBODIES, *FLOW SEPARATION), HYPERSONIC CHARACTERISTICS, CONICAL BODIES, CYLINDRICAL BODIES, PRESSURE, DISTRIBUTION, REYNOLDS NUMBER, WIND TUNNEL MODELS, MODEL TESTS, HYPERSONIC AIRCRAFT, HYPERSONIC TEST VEHICLES

Subject Categories : Aerodynamics
      Research and Experimental Aircraft
      Unmanned Spacecraft

Distribution Statement : APPROVED FOR PUBLIC RELEASE