Calculation of three-dimensional shock/turbulent boundary-layer interaction generated by sharp fin

Knight, Doyle

doi:10.2514/3.9192

Cited by 17 publications

(3 citation statements)

References 15 publications

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“…Fifth, the streamwise grid spacing Ax is typically 0.32600 for Grid 1 and 0.16600 for Grid 2 in the interaction region. This is clearly within the requirement (Knight 1984;Knight 1985) Ax/6oo < 1.0 established in previous 3-D single fin interaction computations.…”

Section: Grid Detailssupporting

confidence: 62%

“…and z m = These values are well within the requirement (Knight 1984) y~ < 60.0 and z + _< 60.0. Third, a total of 23 and 30 points were typically contained within the fiat plate boundary layer for Grids 1 and 2, respectively, thereby satisfying the requirement (Knight 1984;Knight 1985; of a minimum of 20 points Within the boundary layer. Fourth, the maximum grid spacing in the y direction is 0.36600 and 0.16600 for Grids 1 and 2, respectively, and the maximum grid spacing in the z direction is 0.166oo for both Grids 1 and 2.…”

Section: Grid Detailsmentioning

confidence: 99%

“…The interaction strength (defined as the theoretical inviscid pressure ratio P2/P1 across the shock) varied from P2/PI = 1.35 to 5.1 for the supersonic (Mach 3 to 4) cases and from 5.4 to 9.7 for the hypersonic (Mach 8.2) case. Theoretical (numerical) studies for the 3-D single fin interaction have been performed at Mach 3 and Mach 4 by Horstman and Hung (1979), Knight (1984Knight ( , 1985, Horstman (1986), Knight et al (1987, Knight (1989, 1991), and Knight and Badekas (1991), and at Mach 8.2 by . The theoretical models were either the full 3-D or conical Reynolds-averaged Navier-Stokes (RANS) equations incorporating algebraic (Cebeci and Smith 1974;Baldwin and Lomax 1978) or two equation (Jones-Launder 1972;Rodi 1991) turbulence models.…”

Section: Introductionmentioning

confidence: 99%

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Investigation of a hypersonic crossing shock wave/turbulent boundary layer interaction

1993

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Abstract. A combined theoretical and experimental study is presented for the in~teraction between crossing shock waves generated by (10% 10 ~ sharp fins and a flat plate turbulent boundary layer at Mach 8.3. The theoretical model is the full 3-D mean compressible Reynolds-averaged NavierStokes (RANS) eqtuations incorporating the algebraic turbulent eddy viscosity model of Baldwin and Lomax. A grid refinement study indicated that adequate resolution of the flowfield has been achieved. Computed results agree well with experiment for surface pressure and surface flow patterns and for pitot pressure and yaw angle profiles in the flowfield. The computations, however, significantly overpredic, surface heat transfer. Analysis of the computed flowfield results indicates the formation of complex streamline and wave structures within the interaction region.

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Section: Grid Detailssupporting

confidence: 62%