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  • 1
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    Flight test and numerical simulation of transonic flow around YAV-8B Harrier II wing (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A computational fluid dynamics (CFD) method is used to study the aerodynamics of the YAV-8B Harrier II wing in the transonic region. A numerical procedure is developed to compute the flow field around the complicated wing-pylon-fairing geometry. The surface definition of the wing and pylons were obtained from direct measurement using theodolite triangulation. A thin-layer Navier-Stokes code with the Chimera technique is used to compute flow solutions. The computed pressure distributions at several span stations are compared with flight test data and show good agreement. Computed results are correlated with flight test data that show the flow is severely separated in the vicinity of the wing-pylon junction. Analysis shows that shock waves are induced by pylon swaybrace fairings, that the flow separation is much stronger at the outboard pylon and that the separation is caused mainly by the crossflow passing the geometry of wing-pylon junction.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-1628
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Effects of bleed-hole geometry and plenum pressure on three-dimensional shock-wave/boundary-layer/bleed interactions (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A numerical study was performed to investigate 3D shock-wave/boundary-layer interactions on a flat plate with bleed through one or more circular holes that vent into a plenum. This study was focused on how bleed-hole geometry and pressure ratio across bleed holes affect the bleed rate and the physics of the flow in the vicinity of the holes. The aspects of the bleed-hole geometry investigated include angle of bleed hole and the number of bleed holes. The plenum/freestream pressure ratios investigated range from 0.3 to 1.7. This study is based on the ensemble-averaged, 'full compressible' Navier-Stokes (N-S) equations closed by the Baldwin-Lomax algebraic turbulence model. Solutions to the ensemble-averaged N-S equations were obtained by an implicit finite-volume method using the partially-split, two-factored algorithm of Steger on an overlapping Chimera grid.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-3259 , AIAA, Shear Flow Conference; Jul 06, 1993 - Jul 09, 1993; Orlando, FL; United States|; 19 p.
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Juncture flow improvement for wing/pylon configurations by using CFD methodology (1993)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Transonic flow field around a fighter wing/pylon configuration was simulated by using an implicit upwinding Navier-Stokes flow solver (F3D) and overset grid technology (Chimera). Flow separation and local shocks near the wing/pylon junction were observed in flight and predicted by numerical calculations. A new pylon/fairing shape was proposed to improve the flow quality. Based on numerical results, the size of separation area is significantly reduced and the onset of separation is delayed farther downstream. A smoother pressure gradient is also obtained near the junction area. This paper demonstrates that computational fluid dynamics (CFD) methodology can be used as a practical tool for aircraft design.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-0522 , ; 10 p.|AIAA, Aerospace Sciences Meeting and Exhibit; Jan 11, 1993 - Jan 14, 1993; Reno, NV; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Navier-Stokes simulation of external/internal transonic flow on the forebody/inlet of the AV-8B Harrier II (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: In this work, the computation of combined external/internal transonic flow on the complex forebody/inlet configuration of the AV-8B Harrier II is performed. The actual aircraft has been measured and its surface and surrounding domain, in which the fuselage and inlet have a common wall, have been described using structured grids. The 'thin-layer' Navier-Stokes equations were used to model the flow along with the Chimera embedded multi-block technique. A fully conservative, alternating direction implicit (ADI), approximately factored, partially fluxsplit algorithm was employed to perform the computation. Comparisons to some experimental wind tunnel data yielded good agreement for flow at zero incidence and angle of attack. The aim of this paper is to provide a methodology or computational tool for the numerical solution of complex external/internal flows.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-3057 , ; 12 p.|AIAA, Fluid Dynamics Conference; Jul 06, 1993 - Jul 09, 1993; Orlando, FL; United States
    Format: text
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    NASA TECHNICAL REPORTS
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