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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01 Jan 1981
TL;DR: In this paper, a second-order accurate method for solving viscous flow equations has been proposed that preserves conservation form, requires no block or scalar tridiagonal inversions, is simple and straightforward to program (estimated 10% modification for the update of many existing programs), and should easily adapt to current and future computer architectures.
Abstract: Although much progress has already been made In solving problems in aerodynamic design, many new developments are still needed before the equations for unsteady compressible viscous flow can be solved routinely. This paper describes one such development. A new method for solving these equations has been devised that 1) is second-order accurate in space and time, 2) is unconditionally stable, 3) preserves conservation form, 4) requires no block or scalar tridiagonal inversions, 5) is simple and straightforward to program (estimated 10% modification for the update of many existing programs), 6) is more efficient than present methods, and 7) should easily adapt to current and future computer architectures. Computational results for laminar and turbulent flows at Reynolds numbers from 3 x 10(exp 5) to 3 x 10(exp 7) and at CFL numbers as high as 10(exp 3) are compared with theory and experiment.
427 citations
TL;DR: In this paper, a second-order accurate method for solving viscous flow equations has been proposed that preserves conservation form, requires no block or scalar tridiagonal inversions, is simple and straightforward to program (estimated 10% modification for the update of many existing programs), and should easily adapt to current and future computer architectures.
Abstract: Although much progress has already been made In solving problems in aerodynamic design, many new developments are still needed before the equations for unsteady compressible viscous flow can be solved routinely. This paper describes one such development. A new method for solving these equations has been devised that 1) is second-order accurate in space and time, 2) is unconditionally stable, 3) preserves conservation form, 4) requires no block or scalar tridiagonal inversions, 5) is simple and straightforward to program (estimated 10% modification for the update of many existing programs), 6) is more efficient than present methods, and 7) should easily adapt to current and future computer architectures. Computational results for laminar and turbulent flows at Reynolds numbers from 3 x 10(exp 5) to 3 x 10(exp 7) and at CFL numbers as high as 10(exp 3) are compared with theory and experiment.
326 citations
TL;DR: In this paper, a general method for calculating turbulent boundary layers in two-dimensional flows is presented, based on the ideas of eddy transport coefficients and the numerical solution of the governing equations in differential form.
Abstract: In this paper we present a general method for calculating turbulent boundary layers in twodimensional flows and investigate its accuracy for compressible flows with heat and mass transfer The method is based on the ideas of eddy transport coefficients and the numerical solution of the governing equations in differential form The experimental data considered cover a Mach number range of 0 to 67 and include flows with and without pressure gradients The results indicate good agreement at high Reynolds numbers At low Reynolds numbers the agreement is not as good, and further work needs to be done in such cases
121 citations
TL;DR: Heat transfer from turbulent boundary layer interacting with shock and expansion waves in supersonic flow was studied in this article. But the results were limited to the case of a single wave.
Abstract: Heat transfer from turbulent boundary layer interacting with shock and expansion waves in supersonic flow
43 citations
"Numerical investigation of the impi..." refers methods or result in this paper
...The value of c~ is found to be 0.85 which is the same as predicted experimentally [ 8 ]....
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...The experiments conducted by Back and Cuffer [ 8 ] are selected for comparison at Mach number 3.7 and free-stream Reynolds number 8.202 x 106/m....
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...The upstream boundary conditions match the experimental conditions [ 8 ], A zero-gradient boundary condition is used at the down-stream boundary....
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01 Sep 1974
TL;DR: In this article, an experimental investigation of interference heating resulting from interactions of shock waves and turbulent boundary layers was conducted, where pressure and heat-transfer distributions were measured on a flat plate in the free stream and on the wall of the test section of the Langley Mach 6 high Reynolds number tunnel for Reynolds numbers ranging from 2 million to 400 million.
Abstract: An experimental investigation of interference heating resulting from interactions of shock waves and turbulent boundary layers was conducted. Pressure and heat-transfer distributions were measured on a flat plate in the free stream and on the wall of the test section of the Langley Mach 6 high Reynolds number tunnel for Reynolds numbers ranging from 2 million to 400 million. Various incident shock strengths were obtained by varying a wedge-shock generator angle (from 10 deg to 15 deg) and by placing a spherical-shock generator at different vertical positions above the instrumented flat plate and tunnel wall. The largest heating-rate amplification factors obtained for completely turbulent boundary layers were 22.1 for the flat plate and 11.6 for the tunnel wall experiments. Maximum heating correlated with peak pressures using a power law with a 0.85 exponent. Measured pressure distributions were compared with those calculated using turbulent free-interaction pressure rise theories, and separation lengths were compared with values calculated by using different methods.
11 citations