An Investigation of Several NACA 1-series Nose Inlets with and Without Protruding Central Bodies at High-subsonic Mach Numbers and at a Mach Number of 1.2
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Pendley, Robert E↗
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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 Variation in Base Pressure over the Reynolds Number Range in which Wake Transition Occurs for Nonlifting Bodies of Revolution at Mach Numbers from 1.62 to 2.62
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Van Hise, Vernon↗
Theoretical distribution of laminar-boundary-layer thickness, boundary-layer Reynolds number and stability limit, and roughness Reynolds number for a sphere and disk in incompressible flow
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Tetervin, Neal↗
Effects of Mach number and wall-temperature ratio on turbulent heat transfer at Mach numbers from 3 to 5
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Tendeland, Thorval↗
Low tip Mach number stall characteristics and high tip Mach number compressibility effects on a helicopter rotor having an NACA 0009 tip airfoil section
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Powell, Robert D , Jr↗
Preliminary investigation at a Mach number of 1.9 and a Reynolds number of 2,200,000 of three ailerons applicable to the Bell XS-2 airplane design
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Sivells, James C↗
Tests of a Triangular Wing of Aspect Ratio 2 in the Ames 12-foot Pressure Wind Tunnel I : the Effect of Reynolds Number and Mach Number on the Aerodynamic Characteristics of the Wing with Flap Undeflected
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Edwards, George G↗
Investigation at a Mach number of 1.9 and a Reynolds number of 2.2 x 10(exp 6) of several flap-type lateral-control devices on a wing having 42.7 degrees sweepback of the leading edge
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Goin, Kennith L↗
Free-flight Performance of 16-inch-diameter Supersonic Ram-jet Units I : Four Units Designed for Combustion-chamber-inlet Mach Number of 0.12 at Free-stream Mach Number of 1.6 (units A-2, A-3, A-4, and A-5)
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Carlton, William W↗
Tests of lifting surfaces on conical and cylindrical portions of a body at subsonic Mach numbers and at a Mach number of 1.2
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Osborne, Robert S↗
An 8-foot Axisymmetrical Fixed Nozzle for Subsonic Mach Numbers up to 0.99 and for a Supersonic Mach Number of 1.2
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Ritchie, Virgil S↗
Some Effects of Chordwise Fences on the Aerodynamic Characteristics of Four Moderately Sweptback Wings in the Low-lift Range at Transonic Mach Numbers and at Mach Number 1.9
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Guy, Lawrence D↗
Flight Measurements of the Pressure Distribution on the Wing of the X-1 Airplane (10 Percent Thick Wing) over a Chordwise Station near the Midspan, in Level Flight at Mach Numbers from 0.79 to 1.00 and in a Pull up at a Mach Number of 0.98
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Carner, H Arthur↗
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↗
Flight measurements of drag and base pressure of a fin-stabilized parabolic body of revolution (NACA RM-10) at different Reynolds numbers and at Mach numbers from 0.9 to 3.3
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Jackson, H Herbert↗
Tabulated Pressure Coefficients and Aerodynamic Characteristics Measured on the Wing of the Bell X-1 Airplane in Level Flight at Mach Numbers from 0.79 to 1.00 and in a Pull-up at a Mach Number of 0.96
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Carner, H Arthur↗
Aerodynamic Study of a Wing-fuselage Combination Employing a Wing Swept Back 63 Degrees : Effect of Reynolds Number at Supersonic Mach Numbers on the Longitudinal Characteristics of a Wing Twisted and Cambered for Uniform Load
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Heitmeyer, John C↗