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  • 1
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    Vortex-flow aerodynamics - An emerging design capability (1981)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Promising current theoretical and simulational developments in the field of leading edge vortex-generating delta, arrow ogival wings are reported, along with the history of theory and experiment leading to them. The effects of wing slenderness, leading edge nose radius, Mach number and incidence variations, and planform on the onset of vortex generation and redistribution of aerodynamic loads are considered. The range of design possibilities in this field are consequential for the future development of strategic aircraft, supersonic transports and commercial cargo aircraft which will possess low-speed, high-lift capability by virtue of leading edge vortex generation and control without recourse to heavy and expensive leading edge high-lift devices and compound airfoils. Attention is given to interactive graphics simulation devices recently developed.
    Keywords: AERODYNAMICS
    Type: Astronautics and Aeronautics; 19; May 1981
    Format: text
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  • 2
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    Leading-edge vortex research: Some nonplanar concepts and current challenges (1986)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Some background information is provided for the Vortex Flow Aerodynamics Conference and that current slender wing airplanes do not use variable leading edge geometry to improve transonic drag polar is shown. Highlights of some of the initial studies combining wing camber, or flaps, with vortex flow are presented. Current vortex flap studies were reviewed to show that there is a large subsonic data base and that transonic and supersonic generic studies have begun. There is a need for validated flow field solvers to calculate vortex/shock interactions at transonic and supersonic speeds. Many important research opportunities exist for fundamental vortex flow investigations and for designing advanced fighter concepts.
    Keywords: AERODYNAMICS
    Type: Vortex Flow Aerodynamics, Vol. 1; p 31-63
    Format: application/pdf
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  • 3
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    Overview of powered-lift technology (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The concept and application of powered lift and the effects of some fundamental design variables are discussed. A brief chronology of significant developments in the field is also presented and the direction of research efforts in recent years is indicated. All powered lift concepts are included, but emphasis is on the two externally blown schemes which involve blowing either above or below the wing and which are utilized in the YC-14 and YC-15 aircraft. Aerodynamics and vehicle design are emphasized. The areas of acoustics, propulsion, and loads are briefly considered.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Powered-Lift Aerodyn. and Acoustics; p 1-27
    Format: application/pdf
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  • 4
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    Recent studies at NASA-Langley of vortical flows interacting with neighboring surfaces (1983)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The importance of leading edge vortical flows, which occur near and interact with neighboring surfaces, is stressed. Research in this area conducted or sponsored by the NASA Langley Research Center since 1978 is surveyed. Particular attention is given to the cumulative results of a number of theoretical and experimental studies. It is noted that these studies have been carried out in order to understand and use this kind of flow. Much of the work has been devoted to improving the lift-to-drag ratio and pitch characteristics for wings in this flow, although work has also been done on examining the unsteady and lateral characteristics.
    Keywords: AERODYNAMICS
    Type: AGARD Aerodyn. of Vortical Type Flows in Three Dimensions; 32 p
    Format: text
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  • 5
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    Recent studies at NASA-Langley of vortical flows interacting with neighboring surfaces (1983)
    In:  Other Sources
    Details
    Publication Date: 2018-12-01
    Description: The importance of leadingedge vortical flows, which occur near and interact with neighboring surfaces, is stressed. Research in this area conducted or sponsored by the NASA Langley Research Center since 1978 is surveyed. Particular attention is given to the cumulative results of a number of theoretical and experimental studies. It is noted that these studies have been carried out in order to understand and use this kind of flow. Much of the work has been devoted to improving the lift-to-drag ratio and pitch characteristics for wings in this flow, although work has also been done on examining the unsteady and lateral characteristics.
    Keywords: AERODYNAMICS
    Format: text
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  • 6
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    Flow field survey and decelerator drag characteristics in the wake of a model of the X-15 airplane at Mach 2.30 and 4.65 (1966)
    In:  CASI
    Details
    Publication Date: 2019-05-29
    Description: Flow field survey and decelerator drag characteristics in wake of model X-15 airplane at Mach 2.30 and 4.65
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-3285
    Format: application/pdf
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  • 7
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    Effects of wing dihedral and planform on sta- bility characteristics of a research model at mach numbers from 1.80 to 4.63 (1965)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Effects of wing dihedral and planform on stability characteristics of aircraft model - wind tunnel testing
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-2914
    Format: application/pdf
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  • 8
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    Improvement of maneuver aerodynamics by spanwise blowing (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Spanwise blowing was used to test a generalized wind-tunnel model to investigate component concepts in order to provide improved maneuver characteristics for advanced fighter aircraft. Primary emphasis was placed on performance, stability, and control at high angles of attack and subsonic speeds. Test data were obtained in the Langley high speed 7 by 10 foot tunnel at free stream Mach numbers up to 0.50 for a range of model angles of attack, jet momentum coefficients, and leading and trailing edge flap deflection angles. Spanwise blowing on a 44 deg swept trapezoidal wing resulted in leading edge vortex enhancement with subsequent large vortex induced lift increments and drag polar improvements at the higher angles of attack. Small deflections of a leading edge flap delayed these lift and drag benefits to higher angles of attack. In addition, blowing was more effective at higher Mach numbers. Spanwise blowing in conjunction with a deflected trailing edge flap resulted in lift and drag benefits that exceeded the summation of the effects of each high lift device acting alone. Asymmetric blowing was an effective lateral control device at the higher angles of attack.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1065 , L-11642
    Format: application/pdf
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  • 9
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    Theoretical aerodynamics of upper-surface-blowing jet-wing interaction (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A linear, inviscid subsonic compressible flow theory is formulated to treat the aerodynamic interaction between the wing and an inviscid upper-surface-blowing (USB) thick jet with Mach number nonuniformity. The predicted results show reasonably good agreement with some available lift and induced-drag data. It was also shown that the thin-jet-flap theory is inadequate for the USB configurations with thick jet. Additional theoretical results show that the lift and induced drag were reduced by increasing jet temperature and increased by increasing jet Mach number. Reducing jet aspect ratio, while holding jet area constant, caused reductions in lift, induced drag, and pitching moment at a given angle of attack but with a minimal change in the curve of lift coefficient against induced-drag coefficient. The jet-deflection effect was shown to be beneficial to cruise performance. The aerodynamic center was shifted forward by adding power or jet-deflection angle. Moving the jet away from the wing surface resulted in rapid changes in lift and induced drag. Reducing the wing span of a rectangular wing by half decreased the jet-circulation lift by only 24 percent at a thrust coefficient of 2.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7936 , L-10037
    Format: application/pdf
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  • 10
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    Vortex maneuver lift for super-cruise configurations (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Some of the theoretical and experimental research conducted at the NASA Langley Research Center is presented to investigate the subsonic vortex-lift producing capabilities for two classes of Super-Cruise designs: a close-coupled wing-canard arrangement and a slender wing configuration. In addition, several analytical methods are discussed for estimating critical structural design loads for thin, highly swept wings having separated leading-edge vortex flows.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-72836
    Format: application/pdf
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