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  • 1
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    Euler/experiment correlation of a generic fighter (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 29; 5, Se; 839-846
    Format: text
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  • 2
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    Accounting for Laminar Run & Trip Drag in Supersonic Cruise Performance Testing (1999)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Description: An improved laminar run and trip drag correction methodology for supersonic cruise performance testing was derived. This method required more careful analysis of the flow visualization images which revealed delayed transition particularly on the inboard upper surface, even for the largest trip disks. In addition, a new code was developed to estimate the laminar run correction. Once the data were corrected for laminar run, the correct approach to the analysis of the trip drag became evident. Although the data originally appeared confusing, the corrected data are consistent with previous results. Furthermore, the modified approach, which was described in this presentation, extends prior historical work by taking into account the delayed transition caused by the blunt leading edges.
    Keywords: Aerodynamics
    Type: 1999 NASA High-Speed Research Performance Workshop; Volume 1; Part 2; 1163-1196; NASA/CP-1999-209704/VOL1/PT2
    Format: text
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  • 3
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    Model 2b Test Results (1999)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: This activity is part of the Wind Tunnel Database and Wind Tunnel Data Corrections Programs. The main purpose of this test was to evaluate the aerodynamic performance of the TCA Baseline configuration around the supersonic cruise point.
    Keywords: Aircraft Design, Testing and Performance
    Type: 1998 NASA High-Speed Research Program Aerodynamic Performance Workshop; Volume 1; Part 2; 1461-1503; NASA/CP-1999-209692/VOL1/PT2
    Format: application/pdf
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  • 4
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    Transonic and supersonic Euler computations of vortex-dominated flow fields about a generic fighter (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Flow fields about a generic flighter model were computed using FL057, a 3-D, 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. FL057 predicted pressure distributions, forces, and moments well at low angles of attack, at which the flow was fully attached. The FL057 predictions were also accurate for some test conditions once the leading edge vortex became well established. At the subsonic speeds, FL057 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: NASA-TP-3156 , A-90161 , NAS 1.60:3156
    Format: application/pdf
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  • 5
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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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  • 6
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    Leading-edge vortex solutions with large total pressure losses (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Computations are presented for a Lambda = 75 deg delta wing in a supersonic freestream under two conditions which lead to leading-edge vortices. For one condition, analysis of the computed vortical flow reveals a closed streamline in the core. From varying computational parameters, it appears that this is due to truncation error of the convective derivatives. For the other condition, comparisons are made with wind-tunnel data, and good agreement is noted for pitot pressure distributions, flow angles on the symmetry plane, and the position of an embedded shock. Many of the aerodynamic parameters are shown to be insensitive to grid spacing.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 87-0039
    Format: text
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  • 7
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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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  • 8
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    Skin Friction and Transition Location Measurement on Supersonic Transport Models (2000)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Flow visualization techniques were used to obtain both qualitative and quantitative skin friction and transition location data in wind tunnel tests performed on two supersonic transport models at Mach 2.40. Oil-film interferometry was useful for verifying boundary layer transition, but careful monitoring of model surface temperatures and systematic examination of the effects of tunnel start-up and shutdown transients will be required to achieve high levels of accuracy for skin friction measurements. A more common technique, use of a subliming solid to reveal transition location, was employed to correct drag measurements to a standard condition of all-turbulent flow on the wing. These corrected data were then analyzed to determine the additional correction required to account for the effect of the boundary layer trip devices.
    Keywords: Life Sciences (General)
    Type: 9th International Symposium on Flow Visualization 2000; Jan 01, 2000; Edinburgh
    Format: application/pdf
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