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  • Other Sources  (9)
  • 1985-1989  (9)
  • 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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    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
  • 3
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    Piloted simulator study of allowable time delay in pitch flight control system of a transport airplane with negative static stability (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A piloted simulation study was conducted to determine the permissible time delay in the flight control system of a 10-percent statically unstable transport airplane during cruise flight conditions. The math model used for the simulation was a derivative Lockheed L-1011 wide-body jet transport. Data were collected and analyzed from a total of 137 cruising flights in both calm- and turbulent-air conditions. Results of this piloted simulation study verify previous findings that show present military specifications for allowable control-system time delay may be too stringent when applied to transport-size airplanes. Also, the degree of handling-qualities degradation due to time delay is shown to be strongly dependent on the source of the time delay in an advanced flight control system. Maximum allowable time delay for each source of time delay in the control system, in addition to a less stringent overall maximum level of time delay, should be considered for large aircraft. Preliminary results also suggest that adverse effects of control-system time delay may be at least partially offset by variations in control gearing. It is recommended that the data base include different airplane baselines, control systems, and piloting tasks with many pilots participating, so that a reasonable set of limits for control-system time delay can be established to replace the military specification limits currently being used.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TM-89147 , L-16282 , NAS 1.15:89147
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    In-flight surface oil-flow photographs with comparisons to pressure distribution and boundary-layer data (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Upper surface oil-flow photographs were obtained at transonic speeds on an F-111 transonic aircraft technology (TACT) aircraft, which had been fitted with a natural laminar-flow airfoil section. The oil-flow photographs were interpreted with regard to shock and boundary-layer characteristics and compared to results obtained from pressure distributions and boundary-layer measurements. Results indicated that flow phenomena (such as shock location and strength) and chord location of boundary-layer characteristics (such as transition location) could be correctly identified from the oil-flow photographs.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2395 , H-1184 , NAS 1.60:2395
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    In-flight rain damage tests of the shuttle thermal protection system (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: NASA conducted in-flight rain damage tests of the Shuttle thermal protection system (TPS). Most of the tests were conducted on an F-104 aircraft at the Dryden Flight Research Facility of NASA's Ames Research Center, although some tests were conducted by NOAA on a WP-3D aircraft off the eastern coast of southern Florida. The TPS components tested included LI900 and LI2200 tiles, advanced flexible reusable surface insulation, reinforced carbon-carbon, and an advanced tufi tile. The objective of the test was to define the damage threshold of various thermal protection materials during flight through rain. The test hardware, test technique, and results from both F-104 and WP-3D aircraft are described. Results have shown that damage can occur to the Shuttle TPS during flight in rain.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-100438 , H-1484 , NAS 1.15:100438 , AIAA PAPER 88-2137
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Effects of winglets on a first-generation jet transport wing. 7: Sideslip effects on winglet loads and selected wing loads at subsonic speeds for a full-span model (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effect of sideslip on winglet loads and selected wing loads was investigated at high and low subsonic Mach numbers. The investigation was conducted in two separate wind tunnel facilities, using two slightly different 0.035-scale full-span models. Results are presented which indicate that, in general, winglet loads as a result of sideslip are analogous to wing loads caused by angle of attack. The center-of-pressure locations on the winglets are somewhat different than might be expected for an analogous wing. The spanwise center of pressure for a winglet tends to be more inboard than for a wing. The most notable chordwise location is a forward center-of-pressure location on the winglet at high sideslip angles. The noted differences between a winglet and an analogous wing are the result of the influence of the wing on the winglet.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2619 , H-1193 , NAS 1.60:2619
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Techniques used in the F-14 variable-sweep transition flight experiment (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    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: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-100444 , H-1461 , NAS 1.15:100444 , AIAA PAPER 88-2110
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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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
  • 9
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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
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