NASA Technical Reports Server (NTRS) : Aerodynamic pdf

NASA Technical Reports Server (NTRS) : Aerodynamic

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The component integration of a class of hypersonic high-lift configurations known as waveriders into hypersonic cruise vehicles was evaluated. A wind-tunnel model was developed which integrates realistic vehicle components with two waverider shapes, referred to as the straight-wing and cranked-wing shapes. Both shapes were conical-flow-derived waveriders for a design Mach number of 4.0. Experimental data and limited computational fluid dynamics (CFD) predictions were obtained over a Mach number range of 1.6 to 4.63 at a Reynolds number of 2.0 x 10(exp 6) per foot. The CFD predictions and flow visualization data confirmed the shock attachment characteristics of the baseline waverider shapes and illustrated the waverider flow-field properties. Experimental data showed that no significant performance degradations, in terms of maximum lift-to-drag ratios, occur at off-design Mach numbers for the waverider shapes and the integrated configurations. A comparison of the fully-integrated waverider vehicles to the baseline shapes showed that the performance was significantly degraded when all of the components were added to the waveriders, with the most significant degradation resulting from aftbody closure and the addition of control surfaces.

Both fully-integrated configurations were longitudinally unstable over the Mach number range studied with the selected center of gravity location and for unpowered conditions. The cranked-wing configuration provided better lateral-directional stability characteristics than the straight-wing configuration

• Creator/s: NASA Technical Reports Server (NTRS
• Date: 1/1/1995
• Year: 1995
• Book Topics/Themes: NASA Technical Reports Server (NTRS), AERODYNAMIC CONFIGURATIONS, COMPUTATIONAL FLUID DYNAMICS, FLOW DISTRIBUTION, HYPERSONIC VEHICLES, WAVERIDERS, WIND TUNNEL MODELS, AERODYNAMIC CHARACTERISTICS, CONICAL FLOW, FOREBODIES, NAVIER-STOKES EQUATION, ROLLING MOMENTS, MACH NUMBER, SHOCK WAVES, WING PLANFORMS, COMPUTATIONAL GRIDS, CONTROL SURFACES, LIFT DRAG RATIO, Cockrell, Charles E., Jr., Huebner, Lawrence D., Finley, Dennis B

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