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  • AIRCRAFT DESIGN, TESTING AND PERFORMANCE  (6)
  • LAUNCH VEHICLES AND SPACE VEHICLES  (2)
  • 1
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    F-14 VSTFE and results of the cleanup flight test program (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: 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.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA, Langley Research Center, Research in Natural Laminar Flow and Laminar-Flow Control, Part 3; p 819-844
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Techniques used in the F-14 variable-sweep transition flight experiment (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Aircraft (ISSN 0021-8669); 28; 622-629
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Flow visualization techniques for flight research (1989)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    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 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.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AGARD, Flight Test Techniques; 32 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Overview of the NASA Dryden Flight Research Facility aeronautical flight projects testing (1992)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: 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.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AGARD, Flight Testing; 17 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Aerodynamic flight research using the Pegasus air-launched space booster (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Completed and planned flight research using the Pegasus as a research vehicle and booster for other hypersonic research vehicles is reviewed. Highlights from flights 1 and 2 are discussed and compared with some analytical results. In particular, attention is given to total vehicle aerodynamics (performance and trim), local aerodynamics (pressure and heat flux distributions), and response of the thermal protection system. Future programs will include a metallic wing test section for laminar flow studies and the use of the Pegasus to boost a research vehicle to hypersonic speeds. The proposed concepts for a dedicated hypersonic research vehicle project are also discussed.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: AIAA PAPER 92-3990
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Techniques used in the F-14 variable-sweep transition flight experiment (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: 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.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 88-2110 , AIAA Flight Test Conference; May 18, 1988 - May 20, 1988; San Diego, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Pegasus hypersonic flight research (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Hypersonic aeronautics research using the Pegasus air-launched space booster is described. Two areas are discussed in the paper: previously obtained results from Pegasus flights 1 and 2, and plans for future programs. Proposed future research includes boundary-layer transition studies on the airplane-like first stage and also use of the complete Pegasus launch system to boost a research vehicle to hypersonic speeds. Pegasus flight 1 and 2 measurements were used to evaluate the results of several analytical aerodynamic design tools applied during the development of the vehicle as well as to develop hypersonic flight-test techniques. These data indicated that the aerodynamic design approach for Pegasus was adequate and showed that acceptable margins were available. Additionally, the correlations provide insight into the capabilities of these analytical tools for more complex vehicles in which design margins may be more stringent. Near-term plans to conduct hypersonic boundary-layer transition studies are discussed. These plans involve the use of a smooth metallic glove at about the mid-span of the wing. Longer-term opportunities are proposed which identify advantages of the Pegasus launch system to boost large-scale research vehicles to the real-gas hypersonic flight regime.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: SAE PAPER 921995 , ; 16 p.|SAE, Aerotech ''92 Conference; Oct 05, 1992 - Oct 08, 1992; Anaheim, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Overview of the NASA Dryden Flight Research Facility aeronautical flight projects (1992)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: 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.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-104254 , H-1847 , NAS 1.15:104254 , AGARD-16 , AGARD Flight Mechanics Panel; May 11, 1992; Chania, Crete; Greece
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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