16 research outputs found
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NACA Research Memorandums
Report presenting time histories of rolling and yawing moments on inclined bodies of revolution with vertical-tail surfaces at several Mach numbers and Reynolds numbers. Three ogival-nose bodies with three overall fineness ratios and a conical-nosed body with a fineness ratio of 12.0 were tested. Results regarding the visual-flow studies, rolling- and yawing-moment measurements, and pressure measurements are provided
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NACA Technical Notes
Report presenting heat-transfer measurements on an air-cooled 20 degree cone with a laminar boundary layer at Mach number 2.02. The surface temperature in the instrumented area on the cone was essentially constant at all test conditions, but the area was preceded by severe surface-temperature gradients
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NACA Research Memorandums
Report presenting a preliminary investigation of a variable-area, variable-internal-contraction air inlet at a range of Mach numbers. The total pressure recovery after supersonic compression, total pressure recovery at the exit of the subsonic diffuser, and the pressure distribution along the diffuser walls were measured
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NACA Research Memorandums
From Summary: "Pressure distributions around circular cylinders placed perpendicular to the stream for subsonic and supersonic flow conditions have been obtained. Drag coefficients calculated from these wind-tunnel tests and from transonic free-flight tests are presented. Drag data are presented for the Mach number range of 0.3 to 2.9.