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  • 1
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    Application of advanced aerodynamics to future transport aircraft (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Applications of supercritical airfoils to transport aircraft designs
    Keywords: AERODYNAMICS
    Type: NASA AIRCRAFT SAFETY AND OPERATING PROBL., VOL. 1 1971; P 165-176
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Report of the wind tunnel/flight correlation panel (1981)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Basic calibration of the tunnel prior to conducting any tests, the areas requiring wind tunnel/flight test correlation for validating the NTF, and recommendations for achieving validation of the NTF are discussed.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center High Reynolds Number Res. - 1980; p 249-262
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Review of the 1980 Wind-Tunnel/Flight Correlation Panel (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Wind tunnel/flight correlation history from the P-51 to the F-8 supercritical wing is reviewed, showing that researchers continue to be faced with nearly identical discrepancies in predicted versus measured drag. The capabilities of the National Transonic Facility to allow assessment of the effects which have heretofore plagued researchers and aircraft designers are anticipated.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Wind-Tunnel(Flight Correlation, 1981; p 23-32
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Effect of wing-transition location and slotted and unslotted flaps on aerodynamic characteristics of a fighter model at high subsonic speeds (1969)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was conducted in the Langley 8 foot transonic pressure tunnel to determine the effects of wing transition location and of slotted and unslotted full span flaps on the longitudinal aerodynamic characteristics of a 1/15 scale model of a variable wing sweep tactical fighter model. Tests were at Mach numbers from 0.70 to 0.85 for a wing leading edge sweep of 26 deg.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-1849 , L-6613
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Historical background and design evolution of the transonic aircraft technology supercritical wing (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Two dimensional wind tunnel test results obtained for supercritical airfoils indicated that substantial improvements in aircraft performance at high subsonic speeds could be achieved by shaping the airfoil to improve the supercritical flow above the upper surface. Significant increases in the drag divergence Mach number, the maximum lift coefficient for buffer onset, and the Mach number for buffet onset at a given lift coefficient were demonstrated for the supercritical airfoil, as compared with a NACA 6 series airfoil of comparable thickness. These trends were corroborated by results from three dimensional wind tunnel and flight tests. Because these indicated extensions of the buffet boundaries could provide significant improvements in the maneuverability of a fighter airplane, an exploratory wind tunnel investigation was initiated which demonstrated that significant aerodynamic improvements could be achieved from the direct substitution of a supercritical airfoil on a variable wing sweep multimission airplane model.
    Keywords: AERODYNAMICS
    Type: NASA-TM-81356 , H-1148
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    A Wind-Tunnel Investigation of the Application of the NASA Supercritical Airfoil to a Variable-Wing-Sweep Fighter Airplane (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was conducted in the Langley 8 foot transonic pressure tunnel and the Langley Unitary Plan wind tunnel to evaluate the effectiveness of three variations of the NASA supercritical airfoil as applied to a model of a variable wing sweep fighter airplane. Wing panels incorporating conventional NACA 64A series airfoil with 0.20 and 0.40 camber were used as bases of reference for this evaluation. Static force and moment measurements were obtained for wing leading edge sweep angles of 26, 33, 39, and 72.5 degrees. Fluctuating wing root bending moment data were obtained at subsonic speeds to determine buffet characteristics. Subsonic data were also obtained for determining the effects of wing transition location and spoiler deflection. Limited lateral directional data are included for the conventional 0.20 cambered wing and the supercritical wing.
    Keywords: AERONAUTICS (GENERAL)
    Type: NASA-TM-X-2759 , L-8689 , NAS 1.15:X-2759
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Transonic wind-tunnel investigation of the maneuver potential of the NASA supercritical wing concept, phase 1 (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation was conducted in the NASA Langley 8-foot transonic pressure tunnel at Mach numbers from 0.60 to 0.975 with a variable-wing-sweep airplane model in order to evaluate a series of wings designed to demonstrate the maneuver potential of the supercritical airfoil concept. Both conventional and supercritical wing designs for several planform configurations were investigated with wing sweep angles from 16.0 deg to 72.5 deg, depending on Mach number and wing configuration. The supercritical wing configuration showed significant improvements over the conventional configurations in drag-divergence Mach number and in drag level at transonic maneuver conditions.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3534 , L-11064
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Supercritical aerodynamics - Worthwhile over a range of speeds. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-08-13
    Description: Supercritical flow exists whenever a high enough forward speed causes local flow over a lifting surface or body to exceed the sonic or critical value. The principal difference between conventional subsonic aerodynamic technology and supercritical technology lies in the cross-sectional profile of lifting surfaces. The characteristics of the supercritical airfoil suggests three potential benefits from applications to civil aircraft. For aircraft designed to operate at moderate subsonic speeds the supercritical airfoil may permit the reduction of structural weight. Supercritical technology would have a second application in permitting efficient high subsonic speed cruise by delaying the transonic drag rise. Another advantage of the thick supercritical wing shows up at low speeds.
    Keywords: AERODYNAMICS
    Type: Astronautics and Aeronautics; 10; Aug. 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    The need for a hypersonic demonstrator (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The requirement for research aircraft and demonstrator vehicles has been seriously challenged by tight budgets and erroneous impressions that aeronautical technology has matured to a point where the value added by flight research and/or demonstration is not sufficient to offset the costs. While this issue may be debatable with respect to subsonic/transonic speeds, such is not the case for high-speed (supersonic and hypersonic) operation. The aerodynamic performance, weight/payload fractions, and thermodynamic problems are such that small margins of error can be tantamount to the vehicle being unable to reach its design point or so inefficient as to render it useless. This paper addresses some of the critical design considerations and operational constraints which make it mandatory to carry out flight research and develop a demonstrator vehicle in order that the risks be reduced to an acceptable level to assure technology readiness for viable hypersonic flight.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: European Symposium on the Future of High Speed Air Transport; Nov 06, 1989 - Nov 08, 1989; Strasbourg; France
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    NACA/NASA supersonic flight research (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The use of experimental and testbed vehicles and their contributions to fundamental problem solving and overall vehicle characteristics are presented. A chronological description of aircraft from the first supersonic flight in the X-1 through the development of the F-100 series, the X-15, and the B-1 is given. One of the early significant contributions made was the development of the all-moving stabilizer that solved the problem associated with high-speed tuck and the trim requirements of entry into the supersonic regime. Some wind tunnel/flight drag characteristics studies associated with the B-1 bomber involving flexibility effects and wind tunnel effects are shown. Finally, the evolution of digital systems to enhance maintainability and reliability and to reduce the work load in the cockpit are described.
    Keywords: AERONAUTICS (GENERAL)
    Type: European Symposium on the Future of High Speed Air Transport; Nov 06, 1989 - Nov 08, 1989; Strasbourg; France
    Format: text
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    NASA TECHNICAL REPORTS
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