High-speed Wind-tunnel Investigation of a Flying-boat Hull with High Length-beam Ratio
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Riebe, John M↗
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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Investigation of Combustion in 16-inch Ram Jet Under Simulated Conditions of High Altitude and High Mach Number
Results obtained with three different burner configurations in a connected-pipe investigation of a 16-inch ram jet are presented. The radial position of the fuel injector and the engine-outlet area both affected burner performance. For a given configuration, only slight changes in total-pressure ratio across the combustion chamber were obtained over the complete range of operation. With one burner, combustion efficiencies obtained at a combustion-chamber-inlet static pressure of 800 pounds per square foot absolute were greater than those obtained at 1920 pounds per square foot absolute.
ENGINES, RAM JET↗
A Transonic-wing Investigation in the Langley 8-foot High-speed Tunnel at High Subsonic Mach Numbers and at a Mach Number of 1.2 : Wing-fuselage Configuration with a Wing of 45 Degrees Sweepback, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfo
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Osborne, Robert S↗
A Transonic-wing Investigation in the Langley 8-foot High-speed Tunnel at High Subsonic Mach Numbers and at a Mach Number of 1.2 : Wing-fuselage Configuration Having a Wing of 60 Degree Sweepback, Aspect-ratio 4, Taper Ratio 0.6, and NACA 65A006 Airf
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Wood, Raymond B↗
A Transonic-wing Investigation in the Langley 8-foot High-speed Tunnel at High Subsonic Mach Numbers and at a Mach Number of 1.2. : Wing-fuselage Configuration Having a Wing of 0 Degrees Sweepback, Aspect Ratio 4.0,taper Ratio 0.6, and NACA 65A006 Ai
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Cahn, Maurice S↗
A Transonic Wing Investigation in the Langley 8-foot High-speed Tunnel at High Subsonic Mach Numbers and at a Mach Number of 1.2 : Wing-fuselage Configuration Having a Wing of 35 Degrees Sweepback, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006
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Henry, Beverly Z , Jr↗
Investigation of Engine Performance and High-temperature Properties of Precision-cast Turbine Blades of High Carbon Stellite 21 and Controlled Grain-size-stellite 21
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Yaker, Charles↗
Investigation at High and Low Subsonic Mach Numbers of Two Symmetrical 6-percent-thick Airfoil Sections Designed to Have High Maximum Lift Coefficients at Low Speeds
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Paradiso, Nicholas J↗
Notes on damping in roll and load distributions in roll at high angles of attack and high subsonic speed
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Source record↗
Wind-tunnel Investigation at High and Low Subsonic Mach Numbers of a Thin Sweptback Wing Having an Airfoil Section Designed for High Maximum Lift
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Racisz, Stanley F↗
Recovery corrections for butt-welded, straight-wire thermocouples in high-velocity, high-temperature gas streams
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Simmons, Frederick S↗
Experimental Investigation at High Subsonic Speeds of the Rolling Stability Derivatives of a Complete Model with an Aspect-ratio-2.52 Wing Having an Unswept 72-percent-chord Line and a High Horizontal Tail
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Sleeman, William C↗
High-speed Cascade Tests of a Blade Section Designed for Typical Hub Conditions of High-flow Transonic Rotors
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Savage, Melvyn↗
Comparison Between Analytical and Wind-tunnel Results on Flutter of Several Low-aspect-ratio, High-density, Unswept Wings at High Subsonic Speeds and Zero Angle of Attack
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WARNER ROBERT W↗
Experimental Investigation at High Subsonic Speed of the Rolling Stability Derivatives of a Complete Model Having a Clipped-delta Wing and a High Horizontal Tail
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Sleeman, William C , Jr↗
Aircraft configurations developing high lift-drag ratios at high supersonic speeds
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Eggers, A J , Jr↗
Mach Number Measurements and Calibrations During Flight at High Speeds and at High Altitudes Including Data for the D-558-II Research Airplane
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Brunn, Cyril D↗