Accession Number : AD0869314

Title :   Results of Supersonic Heat-Transfer Studies on Blunt Swept Leading Edges.

Descriptive Note : Aerodynamic investigative study 1967-1968,

Corporate Author : MASSACHUSETTS INST OF TECH CAMBRIDGE AEROPHYSICS LAB

Personal Author(s) : Gollnick,Albert F. , Jr

Report Date : MAR 1970

Pagination or Media Count : 58

Abstract : Stagnation-line heat-transfer distributions were obtained on blunt swept leading edges at Mach 3.66 and a Reynolds number per foot of 210,000. Pressure distributions were obtained for comparable test conditions. The results illustrate the effects of various flow nonuniformities on leading-edge heat transfer and pressure, including those arising from finite span and nonuniform leading-edge sweep; free-stream nonuniformity induced by the bow shock of typical blunt body; boundary-layer interaction near the leading-edge root; and impingement of a trailing-tip vortex. None of these effects can be predicted analytically as yet, and all may lead to significant deviation from the levels based on infinite-cylinder theory. The importance of the individual results are discussed, and, where possible, appropriate design criteria are presented. (Author)

Descriptors :   (*AIR TO AIR MISSILES, HEAT TRANSFER), (*LEADING EDGES, SUPERSONIC CHARACTERISTICS), BLUNT BODIES, AIRCRAFT, AERODYNAMIC HEATING, PRESSURE, STAGNATION POINT, REYNOLDS NUMBER, SHOCK WAVES, BOUNDARY LAYER, VORTICES

Subject Categories : Aircraft
      Air- and Space-launched Guided Missiles
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE