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  • 1
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    National Transonic Facility status (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The National Transonic Facility (NTF) was operational in a combined checkout and test mode for about 3 years. During this time there were many challenges associated with movement of mechanical components, operation of instrumentation systems, and drying of insulation in the cryogenic environment. Most of these challenges were met to date along with completion of a basic flow calibration and aerodynamic tests of a number of configurations. Some of the major challenges resulting from cryogenic environment are reviewed with regard to hardware systems and data quality. Reynolds number effects on several configurations are also discussed.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: Transonic Symposium: Theory, Application and Experiment, Volume 2; p 1-39
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Maneuver and buffet characteristics of fighter aircraft (1972)
    In:  CASI
    Details
    Publication Date: 2012-05-23
    Description: The high subsonic and transonic characteristics of fighter aircraft and the factors affecting aerodynamic boundaries, such as maximum obtainable lift, buffet onset, pitchup, wing rock, and nose slice are discussed. Investigations were made using a general research configuration which encompassed a systematic matrix of wing design parameters. These results emphasized the sensitivity to section and planform geometry at the selected design point. The incorporation of variable-wing-geometry devices in the form of leading-edge slats or flaps was shown in a number of flight and wind-tunnel studies to provide controlled flow over a wide range of flight conditions and substantial improvements in maneuver capabilities. Additional studies indicated that the blending of a highly swept maneuver strake with an efficient moderately swept wing offers a promising approach for improving maneuver characteristics at high angles of attack without excessive penalties in structural weight.
    Keywords: AIRCRAFT
    Type: AGARD Fluid Dyn. of Aircraft Stalling; 11 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Operational experience with the National Transonic Facility (1984)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: Construction of the National Transonic Facility was completed in September 1982. The checkout of all systems required about one year. The facility operated to the design point of 120 million Reynolds number based on a 0.25 meter chord at a Mach number of 1.0. Performance of all systems was basically as expected. Setup for the detailed aerodynamic calibration begins late in 1983, and the calibration is expected to be complete by the last quarter of 1984.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AGARD Wind Tunnels and Testing Tech.; 8 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    A summary of NASA data relative to external-store separation characteristics (1966)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: GENERAL
    Type: Conf. on Aircarft Aerodynamics; p 105-122
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Testing and checkout experiences in the National Transonic Facility since becoming operational (1988)
    In:  Other Sources
    Details
    Publication Date: 2018-12-01
    Description: The U.S. National Transonic Facility, constructed by NASA to meet the national needs for High Reynolds Number Testing, has been operational in a checkout and test mode since the operational readiness review (ORR) in late 1984. During this time, there have been problems centered around the effect of large temperature excursions on the mechanical movement of large components, the reliable performance of instrumentation systems, and an unexpected moisture problem with dry insulation. The more significant efforts since the ORR are reviewed and NTF status concerning hardware, instrumentation and process controls systems, operating constraints imposed by the cryogenic environment, and data quality and process controls is summarized.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Wind-Tunnel/Flight Correlation, 1981 (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Wind-tunnel/flight correlation activities are reviewed to assure maximum effectiveness of the early experimental programs of the National Transonic Facility (NTF). Topics included a status report of the NTF, the role of tunnel-to-tunnel correlation, a review of past flight correlation research and the resulting data base, the correlation potential of future flight vehicles, and an assessment of the role of computational fluid dynamics.
    Keywords: AERODYNAMICS
    Type: NASA-CP-2225 , L-15368 , NAS 1.55:2225
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Canard-wing lift interference related to maneuvering aircraft at subsonic speeds (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation was conducted at Mach numbers of 0.7 and 0.9 to determine the lift interference effect of canard location on wing planforms typical of maneuvering fighter configurations. The canard had an exposed area of 16.0 percent of the wing reference area and was located in the plane of the wing or in a position 18.5 percent of the wing mean geometric chord above the wing plane. In addition, the canard could be located at two longitudinal stations. Two different wing planforms were tested: one with a leading-edge sweep angle of 60 deg and the other with a leading-edge sweep angle of 44 deg. The results indicated that although downwash from the canard reduced the wing lift at angles of attack up to approximately 16 deg, the total lift was substantially greater with the canard on than with the canard off. At angles of attack above 16 deg, the canard delayed the wing stall. Changing canard deflection had essentially no effect on the total lift, since the additional lift generated by the canard deflection was lost on the wing due to an increased downwash at the wing from the canard.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2897 , L-9096
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Maneuver and buffet characteristics of fighter aircraft (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Recent research efforts in the improvement of the maneuverability of fighter aircraft in the high-subsonic and transonic speed range are reviewed with emphasis on the factors affecting aerodynamic boundaries, such as maximum obtainable lift, buffet onset, pitchup, wing rock, and nose slice. The investigations were made using a general research configuration which encompassed a systematic matrix of wing-design parameters. These results illustrated the sensitivity of section and planform geometry to a selected design point. The incorporation of variable-geometry wing devices in the form of flaps or leading-edge slats was shown to provide controlled flow over a wide range of flight conditions and substantial improvements in maneuver capabilities. Additional studies indicated that the blending of a highly swept maneuver strake with an efficient, moderately swept wing offers a promising approach for improving maneuver characteristics at high angles of attack without excessive penalties in structural weight.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7131 , L-8554
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Some trim drag considerations for maneuvering aircraft (1970)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Aft tail and canard configurations trim drag considerations for maneuvering aircraft
    Keywords: AIRCRAFT
    Type: AIAA PAPER 70-932 , AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, AIRCRAFT DESIGN AND OPERATIONS MEETING, 2ND; Jul 20, 1970 - Jul 22, 1970; LOS ANGELES, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Status and operational characteristics of the National Transonic Facility (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The article discusses the development and capabilities of the National Transonic Facility which is planned for operation in 1981. The fan-drive, cryogenic-pressurized, closed-return facility will have operating parameters of: 0.1-1.2 Mach, 1-9 bars pressure, 78-340 K, 150 dB sound pressure, and plus or minus 0.001 rms turbulence intensity. These operating conditions have been selected on the basis of several current and future aircraft and space transportation systems. The facility will provide full-scale testing conditions for calculating subsonic drag, airloads, and stability and control information. Data for pre-test conditions, on-line information, and post-test analysis will be computer-processed.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AIAA PAPER 78-770 , Aerodynamic Testing Conference; Apr 19, 1978 - Apr 21, 1978; San Diego, CA
    Format: text
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    NASA TECHNICAL REPORTS
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