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  • Weitere Quellen  (7)
  • AIRCRAFT DESIGN, TESTING AND PERFORMANCE  (7)
  • 1990-1994  (3)
  • 1985-1989  (4)
  • 1
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    F-14 VSTFE and results of the cleanup flight test program (1987)
    In:  CASI
    Details
    Publikationsdatum: 2013-08-31
    Beschreibung: Flight transition data applicable to swept wings at high subsonic speeds are needed to make valid assessments of the potential for natural laminar flow or laminar flow control for transports of various sizes at various cruise speeds. NASA initiated the variable sweep transition flight experiment (VSTFE) to help establish a boundary layer transition data base for use in laminar flow wing design. The carrier vehicle for this experiment is an F-14, which has variable sweep capability. The variable sweep outer panels of the F-14 were modified with natural laminar flow gloves to provide not only smooth surfaces but also airfoils that can produce a wide range of pressure distributions for which transition location can be determined. The VSTFE program is briefly described and some preliminary glove I flight results are presented.
    Schlagwort(e): AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA, Langley Research Center, Research in Natural Laminar Flow and Laminar-Flow Control, Part 3; p 819-844
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 2
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    Techniques used in the F-14 variable-sweep transition flight experiment (1991)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-19
    Schlagwort(e): AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: Journal of Aircraft (ISSN 0021-8669); 28; 622-629
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 3
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    Flow visualization techniques for flight research (1989)
    In:  CASI
    Details
    Publikationsdatum: 2017-10-02
    Beschreibung: 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 were obtained. Off-surface flow visualization of vortical flow was 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.
    Schlagwort(e): AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: AGARD, Flight Test Techniques; 32 p
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 4
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    Overview of the NASA Dryden Flight Research Facility aeronautical flight projects testing (1992)
    In:  CASI
    Details
    Publikationsdatum: 2017-10-02
    Beschreibung: Several principal aeronautics flight projects of the NASA Dryden Flight Research Facility are discussed. Key vehicle technology areas from a wide range of flight vehicles are highlighted. These areas include flight research data obtained for ground facility and computation correlation, applied research in areas not well suited to ground facilities (wind tunnels), and concept demonstration.
    Schlagwort(e): AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: AGARD, Flight Testing; 17 p
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 5
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    Techniques used in the F-14 variable-sweep transition flight experiment (1988)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: This paper discusses and evaluates the test measurement techniques used to determine the laminar-to-turbulent boundary-layer transition location in the F-14 variable-sweep transition flight experiment (VSTFE). The main objective of the VSTFE was to determine the effects of wing sweep on the laminar-to-turbulent transition location at conditions representative of transport aircraft. Four methods were used to determine the transition location: (1) a hot-film anemometer system, (2) two boundary-layer rakes, (3) surface pitot tubes, and (4) liquid crystals for flow visualization. Of the four methods, the hot-film anemometer system was the most reliable indicator of transition.
    Schlagwort(e): AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: AIAA PAPER 88-2110 , AIAA Flight Test Conference; May 18, 1988 - May 20, 1988; San Diego, CA; United States
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 6
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    Unbekannt
    Overview of the NASA Dryden Flight Research Facility aeronautical flight projects (1992)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: Several principal aerodynamics flight projects of the NASA Dryden Flight Research Facility are discussed. Key vehicle technology areas from a wide range of flight vehicles are highlighted. These areas include flight research data obtained for ground facility and computation correlation, applied research in areas not well suited to ground facilities (wind tunnels), and concept demonstration.
    Schlagwort(e): AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA-TM-104254 , H-1847 , NAS 1.15:104254 , AGARD-16 , AGARD Flight Mechanics Panel; May 11, 1992; Chania, Crete; Greece
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 7
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    Experimental investigation of the high angle of attack characteristics of a high performance general aviation aircraft (1989)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: Scale model wind tunnel tests and full scale flight tests have been conducted for the Questair Venture general aviation aircraft configuration in order to investigate its high angle-of-attack aerodynamics. Attention is given to the formulation of a wing leading-edge modification capable of enhancing stall departure characteristics. This modification, which involved both outboard wing leading-edge droop and two chordwise leading-edge slots, is found to produce almost no wing-rock tendency when tested on a wind tunnel free-to-roll apparatus; in the full-scale aircraft, the modification yielded gentle, controllable stall characteristics with little cruise and climb performance penalty.
    Schlagwort(e): AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: AIAA PAPER 89-2237 , AIAA Applied Aerodynamics Conference; Jul 31, 1989 - Aug 02, 1989; Seattle, WA; United States
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
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