Experimental aerodynamic heating of simulated space shuttle tiles in laminar and turbulent boundary layers with variable flow angles at a nominal Mach number of 7
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8-Foot High-Temperature Tunnel Aerodynamic Heating approximately boundary layer boundary-layer flow centerline combustor data are presented decreases edge radius effect of gap effects of flow energy turbulent flow flat-plate heating rate flow angle flow angularity flow penetrating forward-facing step free-stream dynamic pressure gap are shown gap length gap region grid H CM H CN H H H Heat Transfer heating increases heating levels high localized heating high-energy turbulent flow increase in heating increased heating instrumented tile interpolated Laminar and Turbulent laminar flow Langley 8-Foot High-Temperature Langley Research Center longitudinal gap low-energy turbulent flow NASA Niculoy 22 nominal Mach number nondimensionalized panel holder peak heating primary structure psia reference 11 sharp leading edge shown in figure Shuttle Tiles sidewalls surface normal test stream thermal protection system thermocouples thin-wall tile tile array tile center top surface total heat load transverse gap turbulent-flow upstream corner