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  • Other Sources  (28)
  • AERODYNAMICS  (14)
  • AIRCRAFT DESIGN, TESTING AND PERFORMANCE  (14)
  • 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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    Status of F16XL SSLFC numerical design validation (1992)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The viewgraphs and discussion of the status of the F-16XL SSLFC numerical design validation are provided. The F-16XL Supersonic Laminar Flow Control Program (SSLFC) is a joint effort involving Rockwell's North American Aircraft Division, NASA Ames-Dryden Flight Research Facility, and NASA Langley Research Center. The objectives of the program are to demonstrate that laminar flow can be obtained on a highly swept wing at supersonic speeds, validate the capabilities of a numerical methodology designed to predict boundary layer transition, and validate the capabilities of the methodology in the design of active and passive laminar flow control (LFC) concepts. The F-16XL SSLFC Program consists of the design, fabrication, installation, and flight test of an active laminar flow control glove for the F-16XL. The glove design emphasized the active (suction) control of attachment line and crossflow boundary condition instabilities. The glove design envelop was constrained by the existing geometry, safety of flight considerations, and space requirements for the suction mechanism. The leading edge extension of the glove was limited to 10 inches for consideration of asymmetric flying qualities and the glove height above the existing surface restricted to two inches. The active (suction) portion of the wing extends to nominally 25 percent chord. The glove was constructed of a micro-perforated titanium sheet (hole diameter = 0.025 inches, spacing ratio = 1/8, and sheet thickness = 0.0025 inches). The glove design includes 22 separate chambers to allow suction variation in the chordwise direction. The F-16XL SSLFC program is currently in the flight test phase.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center, First Annual High-Speed Research Workshop, Part 4; p 1843-1889
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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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
  • 4
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    Flight-Measured Aerodynamic Loads on a 0.92 Aspect Ratio Lifting Surface (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Ventral fin loads, expressed as normal force coefficients, bending moment coefficients, and torque coefficients, were measured during flight tests of a YF-12A airplane. Because of the proximity of the ventral fin to the ailerons, the aerodynamic loads presented were the result of both sideslip loads and aileron crossflow loads. Aerodynamic data obtained from strain gage loads instrumentation and some flight pressure measurements are presented for several Mach numbers ranging from 0.70 to 2.00. Selected wind tunnel data and results of linear theoretical aerodynamic calculations are presented for comparison.
    Keywords: AERODYNAMICS
    Type: YF-12 Experiments Symp., Vol. 1; p 73-91
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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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
  • 6
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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
  • 7
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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
  • 8
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    Constructing Gloved wings for aerodynamic studies (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Recently, two aircraft from the Dryden Flight Research Facility were used in the general study of natural laminar flow (NLF). The first, an F-14A aircraft on short-term loan from the Navy, was used to investigate transonic natural laminar flow. The second, an F-15A aircraft on long-term loan from the Air Force, was used to examine supersonic NLF. These tests were follow-on experiments to the NASA F-111 NLF experiment conducted in 1979. Both wings of the F-14A were gloved, in a two-phased experiment, with full-span(upper surface only) airfoil shapes constructed primarily of fiberglass, foam, and resin. A small section of the F-15A right wing was gloved in a similar manner. Each glove incorporated provisions for instrumentation to measure surface pressure distributions. The F-14A gloves also had provisions for instrumentation to measure boundary layer profiles, acoustic environments, and surface pitot pressures. Discussions of the techniques used to construct the gloves and to incorporate the required instrumentation are presented.
    Keywords: AERODYNAMICS
    Type: NASA-TM-100440 , H-1487 , NAS 1.15:100440 , AIAA PAPER 88-2109
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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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
  • 10
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    Effect of winglets on a first-generation jet transport wing. 4: Stability characteristics for a full-span model at Mach 0.30 (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The static longitudinal and lateral directional characteristics of a 0.035 scale model of a first generation jet transport were obtained with and without upper winglets. The data were obtained for take off and landing configurations at a free stream Mach number of 0.30. The results generally indicated that upper winglets had favorable effects on the stability characteristics of the aircraft.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1119 , L-11705
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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