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  • 1
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    Airfoil wake and linear theory gust response including sub- and superresonant flow conditions (1993)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 9; 6; p. 847-857.
    Format: text
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  • 2
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    Hypersonic transition studies on a slender cone at small angles of attack. (1968)
    In:  Other Sources
    Details
    Publication Date: 2011-08-12
    Description: Angle of attack effect on laminar boundary layer transition on slender cone in contoured nozzle of helium tunnel, discussing Reynolds and Mach numbers effect
    Keywords: AERODYNAMICS
    Format: text
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  • 3
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    Airframe/propulsion integration characteristics at transonic speeds (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The aerodynamic characteristics for both single and twin-engine high-performance aircraft are significantly affected by shock induced flow interactions as well as other local flow interference effects which usually occur at transonic speeds. These adverse interactions can not only cause high drag, but also cause unusual aerodynamic loadings and/or severe stability and control problems. Many programs are under way to not only develop method for reducing the adverse effects, but also to develop an understanding of the basic flow conditions which are the primary contributors. It is anticipated that these programs will result in technologies which can reduce the aircraft cruise drag through improved integration as well as increase aircraft maneuverability through the application of thrust vectoring. Some of the primary integration problems for twin-engine aircraft at transonic speeds are identified, and several methods are demonstrated for reducing or eliminating the undersirable characteristics, while enhancing configuration effectiveness.
    Keywords: AERODYNAMICS
    Type: Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 1; p 1-31
    Format: application/pdf
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  • 4
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    Inverse boundary-layer technique for airfoil design (1979)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A description is presented of a technique for the optimization of airfoil pressure distributions using an interactive inverse boundary-layer program. This program allows the user to determine quickly a near-optimum subsonic pressure distribution which meets his requirements for lift, drag, and pitching moment at the desired flow conditions. The method employs an inverse turbulent boundary-layer scheme for definition of the turbulent recovery portion of the pressure distribution. Two levels of pressure-distribution architecture are used - a simple roof top for preliminary studies and a more complex four-region architecture for a more refined design. A technique is employed to avoid the specification of pressure distributions which result in unrealistic airfoils, that is, those with negative thickness. The program allows rapid evaluation of a designed pressure distribution off-design in Reynolds number, transition location, and angle of attack, and will compute an airfoil contour for the designed pressure distribution using linear theory.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt. 1; p 383-397
    Format: application/pdf
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  • 5
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    Hypersonic viscous flows (1969)
    In:  Other Sources
    Details
    Publication Date: 2018-12-01
    Description: Two dimensional hypersonic viscous flow, analyzing viscosity and bluntness induced pressure effects
    Keywords: AERODYNAMICS
    Format: text
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  • 6
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    Effect of wing planform modification on longitudinal characteristics of a variable- sweep m wing (1965)
    In:  CASI
    Details
    Publication Date: 2019-05-24
    Description: Wind tunnel testing to determine effects of wing planform modifications on longitudinal aerodynamic characteristics of variable-sweep M planform wing
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-3025
    Format: application/pdf
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  • 7
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    Induced drag - Historical perspective (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Induced drag is associated with the shedding of vorticity along the span of a finite wing, especially its tip region; for most subsonic aircraft configurations, induced drag constitutes about 50 percent of total aircraft drag throughout the flight envelope. NASA and the U.S. aircraft industry have aggressively studied induced-drag reduction methods. The state-of-the-art CTOL commercial aircraft wing is as a result of these efforts virtually optimal, with a total induced drag lying within a percent of the theoretical minimum. Many of the devices currently under study for induced drag reduction are added to wingtips, yielding benefits through their effects on the wake vortex as well as through forces generated in the flowfield.
    Keywords: AERODYNAMICS
    Type: SAE PAPER 892341
    Format: text
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  • 8
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    Aerodynamic characteristics of a high-wing transport configuration with a over-the-wing nacelle-pylon arrangement (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation has been conducted in the Langley 16-Foot Transonic Tunnel to determine the effects on the aerodynamic characteristics of a high-wing transport configuration of installing an over-the-wing nacelle-pylon arrangement. The tests are conducted at Mach numbers from 0.70 to 0.82 and at angles of attack from -2 deg to 4 deg. The configurational variables under study include symmetrical and contoured nacelles and pylons, pylon size, and wing leading-edge extensions. The symmetrical nacelles and pylons reduce the lift coefficient, increase the drag coefficient, and cause a nose-up pitching-moment coefficient. The contoured nacelles significantly reduce the interference drag, though it is still excessive. Increasing the pylon size reduces the drag, whereas adding wing leading-edge extension does not affect the aerodynamic characteristics significantly.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2497 , L-15959 , NAS 1.60:2497
    Format: application/pdf
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  • 9
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    Low-speed single-element airfoil synthesis (1979)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The use of recently developed airfoil analysis/design computational tools to clarify, enrich and extend the existing experimental data base on low-speed, single element airfoils is demonstrated. A discussion of the problem of tailoring an airfoil for a specific application at its appropriate Reynolds number is presented. This problem is approached by use of inverse (or synthesis) techniques, wherein a desirable set of boundary layer characteristics, performance objectives, and constraints are specified, which then leads to derivation of a corresponding viscous flow pressure distribution. Examples are presented which demonstrate the synthesis approach, following presentation of some historical information and background data which motivate the basic synthesis process.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center The Sci. and Technol. of Low Speed and Motorless Flight, Pt. 1; p 1-31
    Format: application/pdf
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  • 10
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    Studies of various factors affecting drag due to lift at subsonic speeds (1966)
    In:  CASI
    Details
    Publication Date: 2019-05-30
    Description: Drag and lift of thin swept wings at subsonic speeds
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-3584
    Format: application/pdf
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