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  • 1
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    Numerical Solution for Navier-Stokes Equations (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Carefully selected blend of computational techniques solves complete set of equations for viscous, unsteady, hypersonic flow in general curvilinear coordinates. New algorithm has tested computation of axially directed flow about blunt body having shape similar to that of such practical bodies as wide-body aircraft or artillery shells. Method offers significant computational advantages because of conservation-law form of equations and because it reduces amount of metric data required.
    Keywords: MATHEMATICS AND INFORMATION SCIENCES
    Type: MFS-25617 , NASA Tech Briefs (ISSN 0145-319X); 6; 3; P. 357
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    A combined direct/inverse three-dimensional transonic wing design method for vector computers (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A three-dimensional transonic-wing design algorithm for vector computers is developed, and the results of sample computations are presented graphically. The method incorporates the direct/inverse scheme of Carlson (1975), a Cartesian grid system with boundary conditions applied at a mean plane, and a potential-flow solver based on the conservative form of the full potential equation and using the ZEBRA II vectorizable solution algorithm of South et al. (1980). The accuracy and consistency of the method with regard to direct and inverse analysis and trailing-edge closure are verified in the test computations.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-2156
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    On the solution of the unsteady Navier-Stokes equations for hypersonic flow about axially-symmetric blunt bodies (1980)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A formulation of the complete Navier-Stokes problem for a viscous hypersonic flow in general curvilinear coordinates is presented. This formulation is applicable to both the axially symmetric and three dimensional flows past bodies of revolution. The equations for the case of zero angle of attack were solved past a circular cylinder with hemispherical caps by point SOR finite difference approximation. The free stream Mach number and the Reynolds number for the test case are respectively 22.04 and 168883. The whole algorithm is presented in detail along with the preliminary results for pressure, temperature, density and velocity distributions along the stagnation line.
    Keywords: AERODYNAMICS
    Type: NASA-CR-161609 , MSSU-EIRS-ASE-80-6
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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