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  • Aircraft Design, Testing and Performance
  • 1985-1989  (4)
  • 1950-1954
  • 1989  (4)
  • 1
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    Unknown
    Compression Pylon (1989)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: A compression pylon for an aircraft with a wing-mounted engine, that does not cause supersonic airflow to occur within the fuselage-wing-pylon-nacelle channel is presented. The chord length of the pylon is greater than the local chord length of the wing to which it is attached. The maximum thickness of the pylon occurs at a point corresponding to the local trailing edge of the wing. As a result, the airflow through the channel never reaches supersonic velocities.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 2
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    A Patched-Grid Algorithm for Complex Configurations Directed Towards the F/A-18 Aircraft (1989)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A patched-grid algorithm for the analysis of complex configurations with an implicit, upwind-biased Navier-Stokes solver is presented. Results from both a spatial-flux and a time-flux conservation approach to patching across zonal boundaries are presented. A generalized coordinate transformation with a biquadratic geometric element is used at the zonal interface in order to treat highly stretched viscous grids and arbitrarily-shaped zonal boundaries. Applications are made to the F-18 forebody-strake configuration at subsonic, high-alpha conditions. Computed surface flow patterns compare well with ground-based and flight-test results; the large effect of Reynolds number on the forebody flow-field is shown.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Paper 89-0121 , 27th Aerospace Sciences Meeting; Jan 09, 1989 - Jan 12, 1989; Reno, NV; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Transition Flight Experiments on a Swept Wing with Suction (1989)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Flight boundary-layer transition experiments were conducted on a 30 degree swept wing with a perforated leading-edge suction panel. The transition location on the panel was changed by systematically varying the location and amount of suction. Transition from laminar to turbulent flow was due to leading-edge turbulence contamination or crossflow disturbance growth and/or Tollmien-Schlichting disturbance growth, depending on flight condition and suction variation. Amplification factor correlations with transition location were made for various suction configurations using a state-of-the-art linear stability theory which accounts for body and streamline curvature and compressibility.
    Keywords: Aircraft Design, Testing and Performance
    Type: IUTAM Third Symposium on Laminar-Turbulent Transition; Sep 11, 1989 - Sep 15, 1989; Toulouse; France
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Future Civil Aircraft and Technologies (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-07-10
    Description: New aircraft technologies are presented that have the potential to expand the air transportation system and reduce congestion through new operating capabilities while also providing greater levels of safety and environmental compatibility. These new capabilities will result from current and planned civil aeronautics technology at the NASA Ames, Lewis, and Langley Research Centers and will cover the complete spectrum of current aircraft and new vehicle concepts including rotorcraft (helicopters and tilt rotors), vertical and short takeoff and landing (V/STOL), and short takeoff and landing (STOL) aircraft, subsonic transports, high-speed transports, and hypersonic/transatmospheric vehicles. New technologies will improve efficiency, affordability, safety, and environmental compatibility of current aircraft and will enable the development of new transportation system. The new capabilities of vehicles could lead to substantial market opportunities and economic growth and could improve the competitive position of the U.S. aerospace industry.
    Keywords: Aircraft Design, Testing and Performance
    Type: SAE-1989-1642 , SAE Transactions; SAE-1989-1642
    Format: text
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    NASA TECHNICAL REPORTS
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