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  • 1
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    Transonic perturbation analysis of wing-fuselage-nacelle-pylon configurations with powered jet exhausts (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A method using a transonic small disturbance code with successive line over-relaxation is described for treating wing/fuselage configurations with a nacelle/pylon/powered jet. Examples illustrating its use for the NASA transport research model are given. Reasonable test/theory comparisons were obtained.
    Keywords: AERODYNAMICS
    Type: NASA-CR-165852
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Calculation of turbulent shear stress in supersonic boundary-layer flows (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 13; Feb. 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Flowfield analysis for successive oblique shock wave-turbulent boundary-layer interactions (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Description of a procedure for predicting the flowfields that develop when successive interactions between oblique shock waves and a turbulent boundary layer occur. Such interactions may occur, for example, in engine inlets for supersonic aircraft. A control volume analysis is used to predict changes in the flow field across the interactions. Two bleed flow models are considered. The predicted results are compared with measured results and are shown to be in good agreement when the bleed flow rate is low, or when there is no bleed. Shortcomings of the bleed flow models at higher bleed flow rates are discussed.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 11; Jan. 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Wall-wake velocity profile for compressible nonadiabatic flows (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The paper suggests a new form of the wall-wake profile which is applicable to flows with heat transfer, and for which the velocity gradient at the boundary-layer edge is zero. The modified profile - which takes into account the effect of turbulent Prandtl number - is found to provide a good representation of experimental data for a wide range of Mach numbers and heat transfer. The skin friction coefficient values determined by a least squares fit of the profile to the data are in good agreement with values measured by the floating element technique. The values of boundary-layer thickness determined by the fit correspond more closely to the outer edge of the viscous flow region than those obtained with earlier versions of the wall-wake profile.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 14; June 197
    Format: text
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    NASA TECHNICAL REPORTS
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