Aerothermal environment in chordwise gaps between split elevons at Mach 6.8
Lewis Roane Hunt, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, Langley Research Center
National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1980 - Technology & Engineering - 42 pages
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8-Foot High-Temperature Structures adjacent elevons aerodynamic heating aerothermally tested angle of attack attack and elevon cm cm cm CN CN CN cn o cn CN O O dynamic pressure elevon deflection angle elevon gap heating elevon sidewalls elevon surface elevon windward surfaces elevon-stub gap heating free-stream unit Reynolds heating rates High-Temperature Structures Tunnel hypersonic Langley 8-Foot High-Temperature Langley Research Center leeward surface Lower elevon model angle NASA number of 4.6 O O CN O O O O o o o o o o o o o oil-flow patterns OOOOOOOO O O O O o o o o o o peak heating pressure and heating shown in figure Space Shuttle split elevons stub and elevons stub sidewall temperature of 1500 Thermocouples total temperature turbulent boundary layer unit Reynolds number Unticked Upper elevon Ticked width between elevons wing and elevon wing surface wing-elevon junction