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  • 1
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    Numerical solution of the Navier-Stokes equations for arbitrary blunt bodies in supersonic flows (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: A time-dependent, two-dimensional Navier-Stokes code employing the body-fitted coordinate technique has been developed for supersonic flows past blunt bodies of arbitrary shape. The computer program is based on the finite-difference approximation of the compressible Navier-Stokes equations transformed to nonorthogonal curvilinear coordinates with the contravariant components of the velocity vector as dependent variables. The bow shock ahead of the body is obtained as part of the solution, by 'shock capturing'. Numerical solutions of the complete equations are presented in detail for free-stream Mach number 4.6, Reynolds number 10,000, and an isothermal wall temperature of 556 K for a circular cylinder with the free-stream outer boundaries forming a hyperbola in the front and a circular arc in the back.
    Keywords: AERODYNAMICS
    Type: Numerical Heat Transfer; 1; Oct
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Numerical solution of the Navier-Stokes equations for super-sonic flows with strong shocks (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The numerical solution of the full Navier-Stokes Equations for viscous flows with high Mach numbers and a strong detached bow shock was obtained. Two dimensional flows around a circular cylinder, and a circular cylinder with an aft-body in the form of a fairing, were considered. The solution of the compressible N.S. equations was accomplished by the method of finite differences. An implicit scheme of solution, the S.O.R., was used with the optimum acceleration parameters determined by trial and error. The tensor notation was used in writing the N-S Equations transformed into general curvilinear coordinates. The equations for the generation of the coordinate system were solved, followed by the solution of the N.S. equations, at the end of a set of given number of time steps. "Wiggles", constituted the one major problem that needed to be overcome. These oscillations give rise to quantities such as negative temperatures, which ultimately caused the computational program to break down. Certain dissipative finite-difference schemes damped these oscillations.
    Keywords: AERODYNAMICS
    Type: NASA-CR-157230
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Numerical solution of the Navier-Stokes equations for blunt nosed bodies in supersonic flows (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A time dependent, two dimensional Navier-Stokes code employing the method of body fitted coordinate technique was developed for supersonic flows past blunt bodies of arbitrary shapes. The bow shock ahead of the body is obtained as part of the solution, viz., by shock capturing. A first attempt at mesh refinement in the shock region was made by using the forcing function in the coordinate generating equations as a linear function of the density gradients. The technique displaces a few lines from the neighboring region into the shock region. Numerical calculations for Mach numbers 2 and 4.6 and Reynolds numbers from 320 to 10,000 were performed for a circular cylinder with and without a fairing. Results of Mach number 4.6 and Reynolds number 10,000 for an isothermal wall temperature of 556 K are presented in detail.
    Keywords: AERODYNAMICS
    Type: NASA-CR-157053 , MSSU-EIRS-ASE-78-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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