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  • 1980-1984  (5)
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  • 1
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    Unknown
    Effect of thrust vectoring and wing maneuver devices on transonic aeropropulsive characteristics of a supersonic fighter (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The aeropropulsive characteristics of an advanced fighter designed for supersonic cruise were determined in the Langley 16-Foot Transonic Tunnel. The objectives of this investigation were to evaluate the interactive effects of thrust vectoring and wing maneuver devices on lift and drag and to determine trim characteristics. The wing maneuver devices consisted of a drooped leading edge and a trailing-edge flap. Thrust vectoring was accomplished with two dimensional (nonaxisymmetric) convergent-divergent nozzles located below the wing in two single-engine podded nacelles. A canard was utilized for trim. Thrust vector angles of 0 deg, 15 deg, and 30 deg were tested in combination with a drooped wing leading edge and with wing trailing-edge flap deflections up to 30 deg. This investigation was conducted at Mach numbers from 0.60 to 1.20, at angles of attack from 0 deg to 20 deg, and at nozzle pressure ratios from about 1 (jet off) to 10. Reynolds number based on mean aerodynamic chord varied from 9.24 x 10 to the 6th to 10.56 x 10 to the 6th.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2119 , L-15526 , NAS 1.60:2119
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Unknown
    Flow-field investigation of a supercruise fighter model (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A NASA Langley investigation was conducted in the 16-foot Transonic Tunnel to survey the flow field around a model of a Supersonic cruise fighter configuration. In this investigation, a model of a supersonic cruise fighter configuration formerly utilized in afterbody-nozzle performance investigations was surveyed with a single, multiholed probe to determine local values of angle of attack, side flow, and Mach number. The investigation was conducted at Mach numbers of 0.6, 0.9, and 1.2 at angles of attack from 0 to 10 deg. The purpose of the investigation was to provide a data base of experimental data for use in verification of theoretical methods, and to compare the experimental data with predictions from currently available theoretical techniques. Results from this investigation show that local angles of attack were generally greater than free stream above the wing and generally less than free stream below the wing. Also there were large spanwise gradients above the wing at the higher angles of attack. The comparisons of experimental data with theoretical predictions show that the theoretical techniques give a qualitative estimate of the flow-field but will require much work to give good quantitative results.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-1331
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Unknown
    Effects of installation of F101 DFE exhaust nozzles on the afterbody-nozzle characteristics of the F-14 airplane (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A wind-tunnel investigation was conducted to determine the effects of F101 DFE (derivative fighter engine) nozzle axial positioning on the afterbody-nozzle longitudinal aerodynamic characteristics of the F-14 airplane. The model was tested in the Langley 16-Foot Transonic Tunnel at Mach numbers from 0.7 to 1.25 and angles of attack from about -2 to 6 degrees. Compressed air was used to simulate nozzle exhaust flow at jet total-pressure ratios from 1 (jet off) to about 8. The results of the investigation show that for subsonic Mach numbers the intermediate cruise nozzle position of the three positions tested resulted in the lowest drag.
    Keywords: AERODYNAMICS
    Type: NASA-TM-83250 , L-14895
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
    facet.materialart.
    Unknown
    Effects of varying podded nacelle-nozzle installations on transonic aeropropulsive characteristics of a supersonic fighter aircraft (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The aeropropulsive characteristics of an advanced twin engine fighter designed for supersonic cruise was investigated in the 16 foot Transonic Tunnel. The performance characteristics of advanced nonaxisymmetric nozzles installed in various nacelle locations, the effects of thrust induced forces on overall aircraft aerodynamics, the trim characteristics, and the thrust reverser performance were evaluated. The major model variables included nozzle power setting; nozzle duct aspect ratio; forward, mid, and aft nacelle axial locations; inboard and outboard underwing nacelle locations; and underwing and overwing nacelle locations. Thrust vectoring exhaust nozzle configurations included a wedge nozzle, a two dimensional convergent divergent nozzle, and a single expansion ramp nozzle, each with deflection angles up to 30 deg. In addition to the nonaxisymmetric nozzles, an axisymmetric nozzle installation was also tested. The use of a canard for trim was also assessed.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2120 , L-15525 , NAS 1.60:2120
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Unknown
    Some solutions to the problems and pitfalls of laser velocimetry in a large transonic wind tunnel (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Attention is given to engineering design and development features of a two-component, coaxial backscatter laser velocimetry system which attempts to realize the long-recognized desirability of this technique's use for nonintrusive flow measurement. The design of the optics for the present 16-foot transonic wind tunnel device, and problems associated with the installation of the system in the hostile, test section plenum chamber environment are discussed.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: Engineering applications of laser velocimetry; Symposium; Nov 14, 1982 - Nov 19, 1982; Phoenix, AZ
    Format: text
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    NASA TECHNICAL REPORTS
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