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  • 1
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    Sonic boom prediction for the Langley Mach 2 low-boom configuration (1992)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Sonic boom pressure signatures and aerodynamic force data for the Langley Mach 2 low sonic boom configuration were computed using the TranAir full-potential code. A solution-adaptive Cartesian grid scheme is utilized to compute off-body flow field data. Computations were performed with and without nacelles at several angles of attack. Force and moment data were computed to measure nacelle effects on the aerodynamic characteristics and sonic boom footprints of the model. Pressure signatures were computed both on and off ground-track. Near-field pressure signature computations on ground-track were in good agreement with experimental data. Computed off ground-track signatures showed that maximum pressure peaks were located off ground-track and were significantly higher than the signatures on ground-track. Bow shocks from the nacelle inlets increased lift and drag, and also increased the magnitude of the maximum pressure both on and off ground-track.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Research Center, High-Speed Research: Sonic Boom, Volume 2; p 157-173
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    TranAir: Recent advances and applications (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: TranAir is a computer code which solves the full-potential equation for transonic flow about very general and complex configurations. Piecewise flat surface panels are used to describe the surface geometry. This paneled definition is then embedded in an unstructured cartesian flow field grid. Finite elements are used in the discretization of the flow field grid in a manner which is fully conservative and second-order accurate. Since geometries may be defined with relative ease, and since the user is not involved in the generation of the flow field grid, computational results may be generated rather quickly for a wide range of geometries. For transonic cases in the cruise angle-of-attack range, TranAir has generated results which are in generally good agreement with both Euler results and wind tunnel data. A typical transonic case runs in 1 to 2 CPU hours on a Cray X-MP. For subcritical cases, the code runs in 15 to 30 CPU minutes, even for geometries in which several thousand surface panels are used in the definition. This ability to rapidly and accurately provide both subsonic and transonic predictions about very complex aircraft configurations gives TranAir the potential of being a very powerful and widely used design tool.
    Keywords: AERODYNAMICS
    Type: NASA Computational Fluid Dynamics Conference. Volume 1: Sessions 1-6; p 411-427
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Sonic boom predictions using a solution-adaptive full-potential code (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The TranAir full-potential code, which utilizes a solution-adaptive, unstructured Cartesian grid, was used to compute near-field pressure signatures of three generic geometries: (1) a cone-cylinder; (2) a low aspect ratio rectangular wing; and (3) a delta-wing/body. Pressure signatures computed by TranAir are extrapolated to near- and midfield distances using a quasilinear extrapolation technique. Results are compared with wind-tunnel data and, where possible, with extrapolated wind-tunnel data and Whitham-method results. In general, extrapolated TranAir data is in good agreement with experimental and Whitham-method pressure signatures, but peak pressures are slightly underpredicted. It is felt that data computed too close to the model caused some of the discrepancies. The flowfield grid structure was also found to be an important issue in obtaining accurate off-body data. Results were encouraging enough to proceed with the application of TranAir to conceptual configurations in support of the NASA high speed research program (HSRP).
    Keywords: Acoustics
    Type: NASA-TM-111269 , NAS 1.15:111269
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    TranAir and Euler computations of a generic fighter including comparisons with experimental data (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The TranAir full-potential code and the FLO57 Euler code were used to calculate transonic flow solutions over two configurations of a generic fighter model. The results were computed at Mach numbers of 0.60 and 0.80 for angles of attack between 0 and 12 deg for TranAir and between 4 and 20 deg for FLO57. Due to the fact that TranAir solves the full-potential equations for transonic flow, TranAir is only accurate to about alpha = 8 deg, at which point the experimental results show the formation of a vortex at the leading edge. Euler results show good agreement with experimental results until vortex breakdown occurs in the solutions.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 89-0263
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Toward the routine aerodynamic analysis of complex configurations (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An evaluation is made of the ability of the TranAir CFD code to routinely compute the aerodynamic characteristics of complex subsonic and supersonic aircraft configurations. TranAir solves the full-potential equation for transonic flow about completely arbitrary geometries, using the surface-paneling PanAir technique in geometry definition. The uniform global grid may be locally refined in regions where flow properties are rapidly changing, such as regions where shocks arise, and around wing leading edges. Unlike panel method codes, TranAir solutions are not undermined by small-perturbation assumptions. Illustrative results are presented for such configurations as the F-16A with wingtip-mounted missiles and underwing fuel tanks, a generic fighter configuration, and a model of NASA-Ames' 12-ft Pressure Wind Tunnel.
    Keywords: AERODYNAMICS
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    PAN AIR analysis of the NASA/MCAIR 279-3: An advanced supersonic V/STOL fighter/attack aircraft (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: PAN AIR is a computer program for predicting subsonic or supersonic linear potential flow about arbitrary configurations. The program was applied to a highly complex single-engine-cruise V/STOL fighter/attack aircraft. Complexities include a close-coupled canard/wing, large inlets, and four exhaust nozzles mounted directly under the wing and against the fuselage. Modeling uncertainties involving canard wake location and flow-through approximation through the inlet and the exhaust nozzles were investigated. The recently added streamline capability of the program was utilized to evaluate visually the predicted flow over the model. PAN AIR results for Mach numbers of 0.6, 0.9, and angles of attack of 0, 5, and 10 deg. were compared with data obtained in the Ames 11- by 11-Foot Transonic Wind tunnel, at a Reynolds number of 3.69 x 10 to the 6th power based on c bar.
    Keywords: AERODYNAMICS
    Type: NASA-TM-86838 , A-85414 , NAS 1.15:86838
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Sonic boom predictions for three generic models using a solution-adaptive full-potential code (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: The TranAir full-potential code, which utilizes a solution-adaptive, unstructured Cartesian grid, was used to compute near-field pressure signatures of three generic supersonic configurations: a cone-cylinder, a low aspect ratio rectangular wing, and a delta-wing/body. TranAir pressure signatures are extrapolated to near- and mid-field distances using a quasi-linear extrapolation technique. Results are compared with existing wind tunnel data and, where possible, with extrapolated experimental data and quasi-linear Whitham-method results. In general, the extrapolated TranAir data is in good agreement with experimental and Whitham-method pressure signatures, but peak pressures are slightly under-predicted. It is thought that computed data obtained too near to the model was the main reason for the discrepancies. Flow-field grid structure was also found to be important in obtaining accurate offbody data.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-3278 , AIAA Applied Aerodynamics Conference; Sept. 23-25, 1991; Baltimore, MD; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    A transonic/supersonic CFD analysis of a generic fighter (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Flow fields about a generic fighter model have been computed using FLO57, a three-dimensional, finite-volume Euler code. Computed pressure coefficients, forces, and moments at several Mach numbers - 0.6, 0.8, 1.2, 1.4, and 1.6 - are compared with wind tunnel data over a wide range of angles of attack in order to determine the applicability of the code for the analysis of fighter configurations. Two configurations were studied, a wing/body and a wing/body/chine. FLO57 predicted pressure distributions, forces, and moments well at low angles of attack, at which the flow was fully attached. The FLO57 predictions were also accurate for some test conditions once the leading-edge vortex became well established. At the subsonic speeds, FLO57 predicted vortex breakdown earlier than that seen in the experimental results. Placing the chine on the forebody delayed the onset of bursting and improved the correlation between numerical and experimental data at the subsonic conditions.
    Keywords: AERODYNAMICS
    Type: ICAS Congress; Sept. 9-14, 1990; Stockholm; Sweden
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Transonic analysis of the F-16A with under-wing fuel tanks - An application of the TranAir full-potential code (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Initial results obtained using the TranAir transonic full-potential code are presented for a fully configured F-16A geometry, including two 370-gal under-wing fuel tanks, at freestream Mach numbers of 0.6 and 0.9 and angle of attack of 4 deg. The geometry is modeled using surface panels, and the flow field is defined by a rectangular array of flow-field grid points. The paneled geometry is embedded within this rectangular flow field. By avoiding the use of surface-conforming flow-field grids, the modeling generality afforded by surface panels can be utilized to analyze very complex configurations in the transonic flow regime.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 87-1198
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Aerodynamic tailoring of the Learjet Model 60 wing (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The wing of the Learjet Model 60 was tailored for improved aerodynamic characteristics using the TRANAIR transonic full-potential computational fluid dynamics (CFD) code. A root leading edge glove and wing tip fairing were shaped to reduce shock strength, improve cruise drag and extend the buffet limit. The aerodynamic design was validated by wind tunnel test and flight test data.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAE PAPER 932534 , SAE, Aerotech ''93; Sep 27, 1993 - Sep 30, 1993; Costa Mesa, CA; United States|(ISSN 0148-7191); 7 p.
    Format: text
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    NASA TECHNICAL REPORTS
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