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  • 11
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    Flow Visualization Techniques for Flight Research (1988)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: In-flight flow visualization techniques used at the Dryden Flight Research Facility of NASA Ames Research Center (Ames-Dryden) and its predecessor organizations are described. Results from flight tests which visualized surface flows using flow cones, tufts, oil flows, liquid crystals, sublimating chemicals, and emitted fluids have been obtained. Off-surface flow visualization of vortical flow has been obtained from natural condensation and two methods using smoke generator systems. Recent results from flight tests at NASA Langley Research Center using a propylene glycol smoker and an infrared imager are also included. Results from photo-chase aircraft, onboard and postflight photography are presented.
    Keywords: AERODYNAMICS
    Type: NASA-TM-100455 , H-1524 , NAS 1.15:100455 , AGARD-PAPER-20 , AGARD Symposium of the Flight Mechanics Panel on Flight Test Techniques; Oct 17, 1988 - Oct 20, 1988; Edwards AFB, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 12
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    The use of oil for in-flight flow visualization (1984)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Oil was used to visualize inflight aerodynamic characteristics such as boundary layer transition, shock wave location, regions of separated flow, and surface flow direction. The technique, which is similar to wind tunnel oil-flow testing, involves an oil mixture to test aircraft before takeoff. After takeoff, the airplane climbs immediately to the test altitude and photographs are taken. The developmental experience is summarized, several examples of inflight oil-flow photographs are presented and discussed, and an approach for potential users of the technique is presented.
    Keywords: AERODYNAMICS
    Type: NASA-TM-84915 , H-1195 , NAS 1.15:84915 , Ann. Symp. of the Soc. of Flight Test Engr.; Aug 15, 1983 - Aug 19, 1983; Newport Beach, Ca; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 13
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    Overview of supersonic laminar flow control research on the F-16XL ships 1 and 2 (1992)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: NASA is directing research to develop technology for a high-speed civil transport. Supersonic laminar flow control has been identified as a program element, since it offers significant drag-reduction benefits and is one of the more promising technologies for producing an economically viable aircraft design. NASA is using two prototype F-16XL aircraft to research supersonic laminar flow control. The F-16XL planform is similar to design planforms of high-speed civil transports. The planform makes the aircraft ideally suited for developing technology pertinent to high-speed transports. The supersonic laminar flow control research programs for both aircraft are described. Some general results of the ship-1 program demonstrate that significant laminar flow was obtained using laminar flow control on a highly swept wing at supersonic speeds.
    Keywords: AERODYNAMICS
    Type: NASA-TM-104257 , H-1858 , NAS 1.15:104257 , SAE PAPER 92-1994 , 1992 Aerotech Conference; Oct 05, 1992 - Oct 08, 1992; Anaheim, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 14
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    Nonlinear development of crossflow vortices (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Nonlinear crossflow vortices in an incompressible three-dimensional boundary layer are computed by weakly nonlinear theory and direct numerical simulations. The parallel basic flow is defined by Falkner-Skan-Cooke similarity profiles. The temporal evolution of spanwise periodic, quasi-two-dimensional disturbances without variations along the vortex axis is considered. The nonlinear theory is based on the approach of Herbert (1980, 1983). The theory predicts the existence of the finite amplitude equilibrium states seen in earlier simulations. When the disturbance amplitudes are small, there is very good quantitative agreement in the fundamental disturbance velocity components between the theory and the simulations.
    Keywords: AERODYNAMICS
    Type: Instability and Transition; May 15, 1989 - Jun 09, 1989; Hampton, VA; United States
    Format: text
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    NASA TECHNICAL REPORTS
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