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  • 1
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    Full-potential analysis of a supersonic delta wing/body (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 26; 235-240
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Design and experimental verification of an equivalent forebody representation of flowing inlets (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 26; 1059-106
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Investigation of leading-edge flap performance on delta and double-delta wings at supersonic speeds (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation of the aerodynamic performance of leading-edge flaps on three clipped delta and three clipped double-delta wing planforms with aspect ratios of 1.75, 2.11, and 2.50 was conducted in the Langley Unitary Plan Wind Tunnel at Mach numbers of 1.60, 1.90, and 2.16. A primary set of fullspan leading-edge flaps with similar root and tip chords were investigated on each wing, and several alternate flap planforms were investigated on the aspect-ratio-1.75 wings. All leading-edge flap geometries were effective in reducing the drag at lifting conditions over the range of wing aspect ratios and Mach numbers tested. Application of a primary flap resulted in better flap performance with the double-delta planform than with the delta planform. The primary flap geometry generally yielded better performance than the alternate flap geometries tested. Trim drag due to flap-induced pitching moments was found to reduce the leading-edge flap performance more for the delta planform than for the double-delta planform. Flow-visualization techniques showed that leading-edge flap deflection reduces crossflow shock-induced separation effects. Finally, it was found that modified linear theory consistently predicts only the effects of leading-edge flap deflection as related to pitching moment and lift trends.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2656 , L-16143 , NAS 1.60:2656
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    A full-potential theory analysis of the supersonic aerodynamics of a 60-deg delta wing-body configuration (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Experimental spanwise pressure distributions for a 60-deg delta wing/body of approximate fineness ratio 7.6 have been obtained and compared to predictions using full-potential theory. Analysis was performed at Mach 1.6 for angles of attack in the range 0.8 to 10 deg, and for Mach numbers ranging from 1.4 to 1.8 at lift coefficients 0.3 and 0.4. The intent of the study was to examine an attached flow approach for maneuver wing design in the presence of a fuselage. For the Mach number, angle-of-attack conditions considered, the full-potential theory accurately modeled the pressure distributions provided the flow remained attached. By combining the full-potential theory results with an empirical shock-induced separation criterion, it was found that the onset of shock-induced separation can be predicted. The investigation showed that, if an attached-flow approach is used with an empirical method of indicating shock-induced separation, the full-potential method is capable of being used as an effective tool for designing maneuver wings.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 88-0480
    Format: text
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  • 5
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    Design and experimental verification of an equivalent forebody to produce disturbances equivalent to those of a forebody with flowing inlets (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A method by which a simple equivalent faired body can be designed to replace a more complex body with flowing inlets has been demonstrated for supersonic flow. An analytically defined, geometrically simple faired inlet forebody has been designed using a linear potential code to generate flow perturbations equivalent to those produced by a much more complex forebody with inlets. An equivalent forebody wind-tunnel model was fabricated and a test was conducted in NASA Langley Research Center's Unitary Plan Wind Tunnel. The test Mach number range was 1.60 to 2.16 for angles of attack of -4 to 16 deg. Test results indicate that, for the purposes considered here, the equivalent forebody simulates the original flowfield disturbances to an acceptable degree of accuracy.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 88-0195
    Format: text
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  • 6
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    Investigation of the vortex flap concept on a 75-deg sweep delta wing at supersonic speeds (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An experimental investigation of the aerodynamic performance of vortex flaps on a 75-deg sweep delta wing has been conducted in the NASA Langley Unitary Plan Wind Tunnel at Mach numbers from 1.7 to 2.8. The sharp leading edge vortex flaps consisted of the outboard 30 percent of the local wing semispan. Flap deflections of 0, 5, 10, and 15 deg were investigated, for both a wing-alone and a wing-body configuration. The flaps were effective in reducing the drag across the lift-coefficient range. Integration of the upper surface pressure distributions showed that the suction pressures induced by the vortex on the flap were responsible for the drag reductions. At some lift conditions, the minimum drag condition permitted hinge line separation or vortex migration inboard of the hinge line. This result is in contrast to subsonic results, where optimum conditions call for no hinge line separation. The magnitude of the drag reduction due to flap deflection generally decreased as Mach number increased. The effect of a cylindrical forebody on the drag reduction due to flap deflection was minimal.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 87-2475
    Format: text
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  • 7
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    Comparison of experimental and numerical results for delta wings with vortex flaps (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 25; 405-412
    Format: text
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  • 8
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    Implementation of control point form of algebraic grid-generation technique (1991)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The control point form (CPF) provides explicit control of physical grid shape and grid spacing through the movement of the control points. The control point array, called a control net, is a space grid type arrangement of locations in physical space with an index for each direction. As an algebraic method CPF is efficient and works well with interactive computer graphics. A family of menu-driven, interactive grid-generation computer codes (TURBO) is being developed by using CPF. Key features of TurboI (a TURBO member) are discussed and typical results are presented. TurboI runs on any IRIS 4D series workstation.
    Keywords: AERODYNAMICS
    Type: NASA-TM-103748 , E-5997 , NAS 1.15:103748 , International Conference on Numerical Grid Generation in Computational Fluid Dynamics and Related Fields; Jun 03, 1991 - Jun 07, 1991; Barcelona; Spain
    Format: application/pdf
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