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Journal ArticleDOI

Numerical investigation of the impingement of an oblique shock on a flat plate

01 Mar 1988-Vol. 23, Iss: 2, pp 123-125
TL;DR: In this paper, the unsteady, compressible Navier-Stokes equations in Reynolds-averaged variables are solved for a shock wave turbulent boundary layer interaction for the free stream Mach number 37 and Reynolds number 8202×106 computation is performed using MacCormack's explicit-implicit finite difference scheme with 42×42 grid points.
Abstract: The unsteady, compressible Navier-Stokes equations in Reynolds-averaged variables are solved for a shock wave turbulent boundary layer interaction For the free stream Mach number 37 and Reynolds number 8202×106 computation is performed using MacCormack's explicit-implicit finite difference scheme with 42×42 grid points It is found that the peak heating amplification correlation agrees well with computational results
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Proceedings ArticleDOI
01 May 1983
TL;DR: In this paper, an implicit analogue of a widely used explicit method to external axisymmetric laminar flows with strong entropy gradients is extended and the details of the "numerics" of the implicit part are provided in a body oriented coordinate system with a moving outer boundary during the transient part of the solutions.
Abstract: An implicit analogue of a widely used explicit method to external axisymmetric laminar flows with strong entropy gradients is extended. The details of the "numerics" of the implicit part are provided in a body oriented coordinate system with a moving outer (shock) boundary during the transient part of the solutions. The limiting values of the Courant number are obtained when the shock boundary is treated explicitly. The solution algorithm outlined includes the treatment of the source term associated with the equations in weak conservation form. From the results obtained for two sample problems, it becomes clear that accuracy of predictions is, indeed, very good at higher values of the Courant number. There is a significant saving in overall computing time, depending on the Courant number used and the flow Reynolds number. These properties combined with the simplicity of programming the implicit analog may appeal to researchers for using it in the analysis of 3-D flow problems.

8 citations

01 Jul 1972
TL;DR: In this article, the interference heating phenomenon at Mach number 8 over a Reynolds number range from 400 thousand to 3.7 million per ft in the hypersonic wind tunnel was investigated.
Abstract: : Investigation of the interference heating phenomenon was conducted at Mach number 8 over a Reynolds number range from 400 thousand to 3.7 million per ft in the hypersonic wind tunnel. Shock generator models consisted of 1.5, 5, 10 and 15 deg wedges; 2.5, 7.5 and 12.5 deg cones; .5 and 2.0 in. diameter hemispheres, and an orbiter-type vehicle. Shock receiver models included sharp and blunt flat plates and a booster vehicle. Both pressure distributions and heat transfer distributions were obtained in the regions of shock impingement. The test program was organized in a building-block approach. A limited number of sharp plate runs were performed with a boundary layer trip to obtain turbulent data for comparison with other experiments.

6 citations