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  • 1990-1994  (3)
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  • 1
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    Navier-Stokes and Euler solutions for lee-side flows over supersonic delta wings. A correlation with experiment (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An Euler flow solver and a thin layer Navier-Stokes flow solver were used to numerically simulate the supersonic leeside flow fields over delta wings which were observed experimentally. Three delta wings with 75, 67.5, and 60 deg leading edge sweeps were computed over an angle-of-attack range of 4 to 20 deg at a Mach number 2.8. The Euler code and Navier-Stokes code predict equally well the primary flow structure where the flow is expected to be separated or attached at the leading edge based on the Stanbrook-Squire boundary. The Navier-Stokes code is capable of predicting both the primary and the secondary flow features for the parameter range investigated. For those flow conditions where the Euler code did not predict the correct type of primary flow structure, the Navier-Stokes code illustrated that the flow structure is sensitive to boundary layer model. In general, the laminar Navier-Stokes solutions agreed better with the experimental data, especially for the lower sweep delta wings. The computational results and a detailed re-examination of the experimental data resulted in a refinement of the flow classifications. This refinement in the flow classification results in the separation bubble with the shock flow type as the intermediate flow pattern between separated and attached flows.
    Keywords: AERODYNAMICS
    Type: NASA-TP-3035 , L-16751 , NAS 1.60:3035
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Adaptive computations of flow around a delta wing with vortex breakdown (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An adaptive unstructured mesh solution method for the three-dimensional Euler equations was used to simulate the flow around a sharp edged delta wing. Emphasis was on the breakdown of the leading edge vortex at high angle of attack. Large values of entropy, which indicate vortical regions of the flow, specified the region in which adaptation was performed. The aerodynamic normal force coefficients show excellent agreement with wind tunnel data measured by Jarrah, and demonstrate the importance of adaptation in obtaining an accurate solution. The pitching moment coefficient and the location of vortex breakdown are compared with experimental data measured by Hummel and Srinivasan, showing good agreement in cases in which vortex breakdown is located over the wing.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-3400 , In: AIAA Applied Aerodynamics Conference, 11th, Monterey, CA, Aug. 9-11, 1993, Technical Papers. Pt. 1 (A93-47201 19-02); p. 1-9.
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Computed Hypersonic Viscous Flows Over Delta Wings (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: Report describes development of algorithm for finite-volume solution of conical Navier-Stokes equations of hypersonic viscous flow over conical delta wing.
    Keywords: MECHANICS
    Type: ARC-12179 , NASA Tech Briefs (ISSN 0145-319X); 15; 12; P. 70
    Format: text
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    NASA TECHNICAL REPORTS
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