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  • 1
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    Flowfield investigation of a supercruise fighter model (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 22; 289-295
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Theoretical and experimental flow fields for a supersonic cruise fighter forebody (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The capability of two numerical methods to predict the flow field about a representative supersonic cruise aircraft was examined. The two codes were a small-disturbance transonic program of Boppe and a conservative form full-potential transonic program of Shankar and Szema. For the former code, comparisons were made with wind-tunnel data at Mach numbers of 0.6, 0.9, and 1.2 and angles of attack of 0 deg, 5 deg, and 10 deg (7.5 deg instead of 10 deg at a Mach number of 1.2). Predictions from the two codes were compared at a Mach number of 1.2 and an angle of attack of 7.5 deg. The comparison criteria were contours of local angle of attack, local angle of sideslip, and local Mach number. The comparisons indicated that both codes may be considered useful for design applications, depending on the degree of accuracy required by the user's solution. Both solutions show an inaccuracy in their predictions, particularly as Mach number and/or angle of attack increases, because of their lack of viscous effects and any mechanisms to predict vortex development.
    Keywords: AERODYNAMICS
    Type: NASA-TM-86450 , L-15914 , NAS 1.15:86450
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Theoretical and experimental engine-inlet flow fields for fighter forebodies (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The capability of two numerical methods, one for transonic and one for supersonic flows, to predict the flow fields about representative fighter aircraft forebodies in the vicinity of the engine inlets was examined. The Mach number range covered was 0.9 to 2.5 and the angle-of-attack range was 0 deg to 25 deg. The computer progams that implement each of the numerical methods are described as to their features and usage, and results are compared with comprehensive wind tunnel data. Although both prediction methods were inviscid, results show that the aerodynamic effects of the forebody, with and without a wing, can be simulated fairly well. Futher work is needed to include the effects of viscosity, including vortex shedding.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2270 , L-15639 , NAS 1.60:2270
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    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
  • 5
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    Evaluation of a velocity-split solution of the Navier-Stokes equations for fighter forebodies (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A velocity-splitting method of solving the three-dimensional Navier-Stokes equations, originally designed for afterbody flows, is examined for its applicability for predicting fighter forebody flows. Results from the AFTEND Code are compared with wind tunnel data for two fighter configurations at a Mach number of 0.9 and angles-of-attack from 0 deg to 20 deg. Results compare well with data, and in areas where data do not exist, the viscous AFTEND results show realistic effects of viscosity compared to inviscid predictions. The inviscid results themselves are in general superior to results obtained from a small-disturbance transonic potential code.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-2160
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Evaluation of 3 numerical methods for propulsion integration studies on transonic transport configurations (1986)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An effort has been undertaken at the NASA Langley Research Center to assess the capabilities of available computational methods for use in propulsion integration design studies of transonic transport aircraft, particularly of pylon/nacelle combinations which exhibit essentially no interference drag. The three computer codes selected represent state-of-the-art computational methods for analyzing complex configurations at subsonic and transonic flight conditions. These are: EULER, a finitie volume solution of the Euler equation; VSAERO, a panel solution of the Laplace equation; and PPW, a finite difference solution of the small disturbance transonic equations. In general, all three codes have certain capabilities that allow them to be of some value in predicting the flows about transport configurations, but all have limitations. Until more accurate methods are available, careful application and interpretation of the results of these codes are needed.
    Keywords: AERODYNAMICS
    Type: NASA-TM-87727 , NAS 1.15:87727 , AIAA PAPER 86-1814 , AIAA Applied Aerodynamics Conference; Jun 09, 1986 - Jun 11, 1986; San Diego, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Evaluation of two analytical methods for the prediction of inlet flow fields in the vicinity of generalized forebodies (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An investigation of the capability of two computer programs to simulate transonic and supersonic flows about representative fighter aircraft forebodies has been carried out for purpose of predicting flow fields in the vicinity of typical inlet locations. Each computer program is described as to its features and usage, and results are compared with comprehensive wind tunnel data. Although both computer codes were inviscid, results show that the gross aerodynamic effects of the forebody, with and without a wing, can be simulated fairly well. Further work is needed to include the effects of viscosity including vortex shedding.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 82-0959 , Joint Thermophysics, Fluids, Plasma and Heat Transfer Conference; Jun 07, 1982 - Jun 11, 1982; St. Louis, MO
    Format: text
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    NASA TECHNICAL REPORTS
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