1,302 research outputs found
Investigation of the Flow Over Simple Bodies at Mach Numbers of the Order of 20
Get PDFIt is shown that adequate means are available for calculating inviscid direct and induced pressures on simple axisymmetric bodies at zero angle of attack. The extent to which viscous effects can alter these predictions is indicated. It is also shown that inviscid induced pressures can significantly affect the stability of blunt, two-dimensional flat wings at low angles of attack. However, at high angles of attack, the inviscid induced pressure effects are negligible
Pitching-moment Derivatives Cmq and Cma at Supersonic Speeds for a Slender-delta-wing and Slender-body Combination and Approximate Solutions for Broad-delta-wing and Slender-body Combinations
Get PDFWind-tunnel investigation of the static longitudinal and lateral stability of a 1/62-scale model of the X-1E at supersonic speeds
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Experimental Investigation of the Zero-lift Wave Drag of Seven Pairs of Delta Wings with Constant and Varying Thickness Ratios at Mach Numbers of 1.62, 1.93, and 2.41
Get PDFWind-tunnel investigation of the static longitudinal and lateral stability of the Bell X-1A at supersonic speeds
Get PDFWind-tunnel investigation of static lateral and longitudinal stability characteristics of a 1/62-scale model of the X-1E airplane at combined angles of attack and sideslip at supersonic speeds
Get PDFEffects of boundary-layer displacement and leading-edge bluntness on pressure distribution, skin friction, and heat transfer of bodies at hypersonic speeds
Get PDFThe zero-lift wave drag of a particular family of unswept, tapered wings with linearly varying thickness ratio
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