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  • 1
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    Algebraic grid generation about wing-fuselage bodies (1987)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: An algebraic procedure for generating boundary-fitted grids about wing-fuselage configurations is presented. A wing-fuselage configuration consists of two aircraft components specified by cross sections and mathematically represented by Coons' patches. Several grid blocks are constructed to cover the entire region surrounding the configuration, and each grid block maps into a computational cube. Grid points are first determined on the six boundary surfaces of a block and then in the interior. Grid points on the surface of the configuration are derived from the intersection of planes with the Coons' patch definition. Approximate arc length distributions along the resulting grid curves concentrate and disperse grid points. The two-boundary technique and transfinite interpolation are used to determine grid points on the remaining boundary surfaces and block interiors.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 24; 868-872
    Format: text
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  • 2
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    Evidence of imbedded vortices in a three-dimensional shear flow (1981)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Vortex phenomena encountered in an investigation of the streamwise development of the three-dimensional wake region behind the tip of a three-dimensional wedge model are reported. Pressure profiles were measured by pitot probes downstream of a tip with a nearly constant surface pressure level and a nearly continuous surface curvature in a blowdown air tunnel operating at Mach 6. Rather than the simple three-dimensional quasi-parallel shear flow expected, the measurements indicated the presence of a flow with large deficits in longitudinal pitot pressure, which are usually associated with the core region of quasi-steady longitudinal vortices. Vapor screen flow visualizations also support the presence of longitudinal vortices located primarily in the tip region and evidently forming in the vicinity of the wake neck. An increase in overall wake thickness by 100% is also observed. The origin of the vortices as quasi-steady Taylor-Gortler vortices generated in the concavely curved shear layer near the wake neck is considered. It is pointed out that the existence of longitudinal vortexes suggests that three-dimensional turbulence modeling may be much more difficult than previously supposed.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 19; Mar. 198
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Roughness induced transition criteria for space shuttle-type vehicles (1976)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Tripping effectiveness of surface roughness on a delta wing shuttle orbiter model at 20 deg angle of attack is compared to that on plane and axisymmetrical bodies with and without longitudinal pressure gradients. The experimental data presented are compared on the basis of effective roughness Reynolds number since this parameter is not sensitive to flow conditions downstream of the roughness. The discussion covers the effective roughness Reynolds number as a function of roughness position Reynolds number, effective size ratio as a function of pressure gradient and distance from vehicle nose, and effect of spanwise roughness position on roughness effectiveness. It is shown that conventional criteria for sizing roughness elements which promote transition in two-dimensional zero-pressure gradient flows are insufficient for high-pressure gradient flows and three-dimensional flows. Roughness much smaller than that given by conventional criteria can cause transition and significantly increase the heating load.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 13; Feb. 197
    Format: text
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  • 4
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    Aerodynamic considerations (1970)
    In:  CASI
    Details
    Publication Date: 2012-05-22
    Description: Aerodynamic loads produced by winds and launch vehicle designing
    Keywords: AERODYNAMICS
    Type: AGARD WIND EFFECTS ON LAUNCH VEHICLES FEB. 1970; P 75-114
    Format: text
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  • 5
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    Surface definition and grid generation about an Assured Crew Return Vehicle (ACRV) for Space Station Freedom (1990)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The surface definition and grid generation about an Assured Crew Return Vehicle (ACRV) for the Space Station Freedom are described. The purpose of the surface definition and grid generation is to provide the necessary geometry information for CFD calculations about the vehicle. There are two salient features in this description. The first is that the numerical model representing the ACRV configuration is obtained from the measurement of an existing wind tunnel model. The method for smoothing the measured data and obtaining the numerical model is described. The second feature is the description of the algebraic grid generation method and software to compute volume grids about the ACRV. The methods and software allow rapid computation of volume grids for a wide range of flow conditions.
    Keywords: AERODYNAMICS
    Type: Computing Systems in Engineering (ISSN 0956-0521); 1; 2-4,
    Format: text
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  • 6
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    Unsteady transonics of a wing with tip store (1986)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 23; 662-668
    Format: text
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  • 7
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    A direct method for computation of nonequilibrium flows with detached shock waves. (1966)
    In:  Other Sources
    Details
    Publication Date: 2019-05-30
    Description: Nonequilibrium inviscid flow about arbitrarily shaped body with detached shock waves, using method with time derivative and bypassing boundary conditions
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 65-24
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Aerodynamic characteristics of a family of multistage missiles at a mach number of 6.0 (1965)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Wind tunnel investigation of aerodynamic characteristics of cone-cylinder-flare multistage missile configurations at supersonic speed
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-2853
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Wind-tunnel investigation of the OMAC canard configuration (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Wind-tunnel tests were conducted on a 0.175-scale model of the OMAC Laser 300 canard configuration in the NASA Langley 12-Foot Low-Speed Wind Tunnel to determine its low-speed high angel-of-attack aerodynamic characteristics. The Laser 300 is a general aviation turboprop pusher aircraft utilizing a canard configuration. The design incorporates a low forward wing and a high main wing with a leading-edge droop installed on the outboard panel and tip fins mounted on the wing tips. The model was tested over a range of -6 to 50-deg angle-of-attack and 20 to -20 deg sideslip. Static force and moment data were measured, and the longitudinal and lateral-directional characteristics were determined.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 86-2608
    Format: text
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  • 10
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    Unsteady transonics of a wing with tip store (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The presence of tip stores influences both the aerodynamic and the aeroelastic performance of wings. Such effects are more pronounced in the transonic regime. In this study, a theoretical method is developed, for the first time, to compute unsteady transonics of oscillating wings with tip stores. The method is based on the small-disturbance, aerodynamic equations of motion from the potential-flow theory. To validate the method, subsonic and transonic aerodynamic computations are made for a lower-aspect-ratio wing, and they are compared with the available experimental data. Comparisons are favorable. The strong effects of the tip store on the transonic aerodynamics of the wing are also illustrated. The method developed in this steady can be used for transonic, aeroelastic computations of wings with tip stores.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 86-0010
    Format: text
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