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  • FLUID MECHANICS  (2)
  • AERODYNAMICS  (1)
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  • 1
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    Asymmetric hypersonic flow (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A general method for the analysis of the inviscid asymmetric hypersonic flow fields enveloping smooth bodies of general shape is given. The method is based on the assumption of a thin shock layer which yields an expression for pressure in generalized Mises coordinates. Numerical results for elliptic cones at angle of attack are shown to compare well with experiments and other theories. The computing logic for a blunt body is described, and a limiting solution at the stagnation point is presented.
    Keywords: FLUID MECHANICS
    Type: NASA-CR-2123
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 2
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    Unknown
    Inviscid flow about blunted cones of large opening angle at angle of attack (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Application of a general method for calculation of inviscid hypersonic flow fields is discussed. General considerations are analyzed along with the sonic corner and the stagnation region. It is concluded that the complications caused by the requirement for sonic flow at the rear corner and particularly by the uncertain position of the stagnation streamline lead to sufficient difficulties with convergence of iterations that a practical procedure is not likely to be found.
    Keywords: AERODYNAMICS
    Type: NASA-CR-132652 , MML-TR-75-10C
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 3
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    Unknown
    Development of a method of analysis and computer program for calculating the inviscid flow about the windward surfaces of space shuttle configurations at large angles of attack (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A general method developed for the analysis of inviscid hypersonic shock layers is discussed for application to the case of the shuttle vehicle at high (65 deg) angle of attack. The associated extensive subsonic flow region caused convergence difficulties whose resolution is discussed. It is required that the solution be smoother than anticipated.
    Keywords: FLUID MECHANICS
    Type: NASA-CR-132453 , MML-TR-74-5C
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
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