Engineering topics
Publications and source records attributed to Whitehead, A. H., Jr..
Features of hypersonic, finite-span separated flows with a turbulent boundary layer have been studied to provide a partial assessment of transverse outflow effects on separated flowfield characteristics. Results demonstrate the critical importance of transverse outflow in determining some of the characteristic features of a turbulent, separated boundary layer.
Lee surface heating data, obtained at relatively low unit Reynolds numbers at Mach 6 and 19, are discussed with emphasis on the peak heating behavior. Surface pressures measured along the lee meridian of the delta-wing orbiter are presented and analyzed in conjunction with the heating. The effects of nose bluntness and lee surface geometry on the heating are discussed and general guidelines are presented for modifying the lee surface geometry of the shuttle to reduce vortex-induced heating. The application of the wind tunnel results to realistic shuttle flight conditions is discussed.
The role of vortices in producing intense localized hea ting to the leeward regions of a variety of configurations is shown and discussed. From experimental results, flow-field models are proposed which account for the interaction of the vortex and the upper surface boundary layer; correlation of the heating is then possible for planar delta wings. Guidelines derived from these studies are offered which reduce the vortex-induced heating by appropriate shaping of configurations such as the space shuttle. Reynolds number is shown to exert a large influence on the magnitude and location of the induced heating.
Vortex-induced heating alleviation to lee side of slender wings in hypersonic flow by contouring leading edge planform
Lee surface flow and aerodynamic heating on delta wing orbiter
Vortices in axisymmetrically separated flows, comparing results of various experiments
Off-centerline heating on lee surface of supersonic delta wing with separation and vortex initiation at leading edge
Flow field and drag characteristics of several laminar boundary layer tripping element in hypersonic flow
Boundary layer trip geometry, size and location effects on position of transition at hypersonic speeds
Hypersonic flow distribution and separation types over highly swept delta wings with trailing edge flaps at Mach 6
Hypersonic turbulent boundary layers on flat plates and delta wings
Hypersonic flow distribution and separation types over highly swept delta wings with trailing edge flaps at Mach 6
Boundary layer trips for producing turbulence in hypersonic flow
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Effect of body cross sections and width-height ratio on performance of bodies and delta-wing- body combinations at Mach 6.9
Pressure and heat transfer over 80-degree sweep slab delta wing in hypersonic flow - wind tunnel test