The formation of vortex shocks in a 3D subsonic flow behind a weak shock wave emerging from a channel

Баженова, Т. В.; Bormotova, T. A.; Golub, V. V.; Kotel’nikov, A. L.; Makeich, A. A.; Shcherbak, S. B.

doi:10.1134/1.1505551

Cited by 3 publications

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“…Axisymmetric geometries are prevalent in the literature [8][9][10][11] , and are usually open ends of shock tubes (open) [12][13][14][15][16] or a larger tube joined to a smaller one (confined). Examples of discontinuous rectangular area enlargements [17][18][19][20][21][22][23][24][25][26][27][28][29][30][31][32][33][34] include expansion chambers [17][18][19] , adjoining square cavities 20,21 , open squareshaped or diamond-shaped ends of shock tubes [22][23][24][25][26][27] , and confined rectangular tubes [28][29][30][31][32][33][34] . These works qualitatively and quantitatively comment on the diffracting shock shape, corner vortex location, shock-vortex interactions, and secondary shock structures.…”

Section: Introductionmentioning

confidence: 99%

On the Unsteady Shock Wave Interaction with a Backward-Facing Step: Inviscid Analysis

Mendoza

Bowersox

2012

42nd AIAA Fluid Dynamics Conference and Exhibit

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A planar shock wave interacting with a backward-facing step was investigated theoretically and computationally over a parameter space defined by the incident shock strength (M S ) and the area ratio between the two channel heights (A 2 /A 1 ). The 2D rectangular geometry is representative of that found in scramjet inlets. Theoretical analyses provided a mapping of the six possible flow configurations to the parameter space, primary wave strengths, and regional flow properties. 16 time-accurate inviscid simulations were performed, which provided full-field pressure maps, wave strengths, and quantitative measurements of key parameters. Qualitative results include illuminating discussions on shock structure, expansions, shock-shock interactions, and shock-expansion interactions. Quantitative results include comparisons of primary wave strengths, measurements of the critical shock location, and the decay profile of the transmitted shock. The studies showed that these flow fields are inherently transient and multidimensional. Nomenclature a = speed of sound, RT  A = duct area (duct height times unit depth) A 2 /A 1 = ratio of large duct height to small duct height, degree of area change c P = specific heat at constant pressure D = function of Mach Number only, defined by Eq. (5) h = sensible enthalpy, c P T M = flow Mach Number, u/a M S = incident shock strength M SS = secondary shock strength M TS = transmitted shock strength P = pressure RE = reflected expansion T = temperature u = velocity (1D) γ = specific heat ratio (air) ρ = density

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