Supersonic interference flow along the corner of intersecting wedges

Charwat, A. F.; Redekopp, L. G.

doi:10.2514/6.1966-128

Cited by 8 publications

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“…Additional research conducted by Watson and Weinstein [2] and West and Korkegi [3] into supersonic and hypersonic corner flow interactions all showed a similar corner flow structure to that of Charwat and Redekopp [1]. However, further experimental research conducted by Korkegi [4] showed a region of disturbed flow that extended from the corner interaction far beyond the location of the reflected shocks in a spanwise direction and Korkegi associated this to boundary layer separation.…”

Section: Supersonic Corner Flowsmentioning

confidence: 51%

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Supersonic viscous corner flows

Naidoo

Skews

2011

Proceedings of the Institution of Mechanical Engineers, Part G:

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Results of numerical and experimental investigations of steady state supersonic viscous corner flows in simplified geometries that resemble typical wing body-fuselage intersections are presented. These flows are numerically calculated using the computational fluid dynamics code of Fluent and include the use of standard turbulence models. Experimental work includes the use of the oil film flow visualization technique to visualize the surface flow patterns. The flows considered are symmetric about the corner bisector. This article focuses on the development of the three shock structure along the various geometries, specifically focusing on the formation and growth of the shear layers that result from the Mach reflection. The resultant effects of this shear layer on pressure distributions, shear stress, and changes in Mach numbers are discussed. The shock wave boundary layer interaction is also presented.

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Section: Supersonic Corner Flowsmentioning

confidence: 51%

“…2. Early experimental work was done on these geometries by Charwat and Redekopp [1]. A Mach stem surface (m) develops between the two incident shocks (I) and the reflected shocks propagate back to the airfoil surface.…”

Section: Supersonic Corner Flowsmentioning

confidence: 99%

Supersonic viscous corner flows

Naidoo

Skews

2011

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Experimental evidence from Mach 3 in air 1 and Mach 20 in helium 2 indicates the corner shock pattern shown in Fig. 1.…”

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confidence: 85%

“…This flow structure was deduced from pitot surveys. 1 ' 2 It has been shown theoretically that under certain conditions the wedge shocks can intersect without a fillet shock, 2 while for other conditions, intersection is impossible. Presumably the flow pattern for all impossible intersections is that described in the preceeding paragraphs.…”

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Corner pressures and fillet shock locations for symmetrical corners by an approximate method.

Watson

1973

Journal of Spacecraft and Rockets

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Nomenclature K = supersonic-hypersonic parameter, M 2 (sina)/(M 2 -1) 1/2 M = Mach number p = pressure x = stream aligned coordinate, Fig. 1 y, z = offset coordinates, Fig. 1 a = flow deflection angle, wedge angle a/ = interference angle creating internal shock y = ratio of specific heats 4> = wedge intersection angle, Fig. 1 0 =90°-0/2 '• Subscripts c = value in the corner 1 = freestream value 2 = wedge valueA J approximate method for predicting the pressure in the immediate corner region, and the shock structure oh stream aligned, sharp leading edge, symmetrical corner configurations is presented. The method is basically the 2-shock method, 1 with the additional assumption that the corner fillet shock can be located from the calculated pressure in the comer. Corner pressures are correlated over a wide range of Mach numbers in air and helium for different corner wedge angles. The shock structure calculated by this method is compared with supersonic and hypersonic data.Experimental evidence from Mach 3 in air 1 and Mach 20 in helium 2 indicates the corner shock pattern shown in Fig. 1. Figure la is a three-dimensional view of the flow pattern including the coordinate system and a base plane perpendicular to the x-axis. Figure ib shows details of the shock structure and the internal flowfield projected on a base plane. For equal wedge angles the flow is symmetrical about a midplane containing the freestream flow vector and the juncture line of the wedge surface. The angle, $, is measured in the base plane. For simplicity, details of the shock structure on only one side of the bisector line will be considered since the flowfield is symmetrical. Either wedge, of course, could be considered the base or interference wedge.The wedge shocks do not intersect near the corner, but instead are joined by a fillet shock which intersects the base wedge shock at point B in Fig. Ib. From point B an internal shock extends to the base wedge surface at point A, and slip lines extend from the .triple shock points inward toward the corner. Flow regions in the base plane are: 1) the freestream flow, 2) undisturbed wedge flow, 3) flow behind a shock within the wedge flowfield, and 4) the conical corner flow region. This flow structure was deduced from pitot surveys. 1 ' 2 It has been shown theoretically that under certain conditions the wedge shocks can intersect without a fillet shock, 2 while for other conditions, intersection is impossible. Presumably the flow pattern for all impossible intersections is that described in the preceeding paragraphs. Figure 2 shows limit lines, functions of M, y, arid 0, for which wedge shocks can intersect according to calculations made by R. D. Wagner of Langley Research Center. Above a line of constant 0, intersection is not possible. a) Sketch of configuration with coordinate system. Base wedge © Freestream flow (2) Undisturbed wedge flow (3) Flow behind internal shock © Corner flow b) Shock structure in base plane.Fig. 1 Corner shock pattern.Unfortunately the only shock structure data taken where ...

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Multi-dimensional limiting for high-order schemes including turbulence and combustion

Gerlinger

2012

Journal of Computational Physics

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In the present paper a fourth/fifth order upwind biased limiting strategy is presented for the simulation of turbulent flows and combustion. Because high order numerical schemes usually suffer from stability problems and TVD approaches often prevent convergence to machine accuracy the multi-dimensional limiting process (MLP) [1] is employed. MLP uses information from diagonal volumes of a discretization stencil. It interacts with the TVD limiter in such a way, that local extrema at the corner points of the volume are avoided. This stabilizes the numerical scheme and enables convergence in cases, where standard limiters fail to converge. Up to now MLP has been used for inviscid and laminar flows only. In the present paper this technique is applied to fully turbulent sub-and supersonic flows simulated with a low Reynolds-number turbulence closure. Additionally, combustion based on finite-rate chemistry is investigated. An improved MLP version (MLP ld , low diffusion) as well as an analysis of its capabilities and limitations are given. It is demonstrated, that the scheme offers high accuracy and robustness while keeping the computational cost low. Both steady and unsteady test cases are investigated.

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Supersonic interference flow along the corner of intersecting wedges

Cited by 8 publications

References 0 publications

Supersonic viscous corner flows

Supersonic viscous corner flows

Corner pressures and fillet shock locations for symmetrical corners by an approximate method.

Multi-dimensional limiting for high-order schemes including turbulence and combustion

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