Supersonic Inviscid Corner Flows with Regular and Irregular Shock Interaction

Gun'ko, Yu. P.; Kudryavtsev, A. N.; Rakhimov, R. D.

doi:10.1023/b:flui.0000030314.27337.6c

Cited by 18 publications

(10 citation statements)

References 18 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…In the same figure curves (1)(2)(3)(4) corresponding to the boundaries of the parameter ranges with different wing flow regimes are plotted for M = 3. Curve 1 corresponds to transition from the shock to the shockless flow in the layer above the right wing panel, 2 to transition from the attached shock to a centered expansion wave on the leading edge of the left panel, 3 to unconditional transition from the regular to the Mach-type interaction between the shocks proceeding from the leading edges, and 4 to the shock detachment from the leading edge of the right panel [6].…”

Section: Results Of the Calculations Of Flow Around A Yawed Wing At Mmentioning

confidence: 99%

“…This concerns with the treatment of the flow structure on the axis of symmetry in the shock layer which was made on the basis of the pressure distributions along the axis of symmetry and over the wing surface and the constantentropy contours (streamlines) which, owing to an inadequate accuracy of the calculations, did not allow one to determine the flow direction in the vicinity of the central chord of the wing. New possibilities of the computational technologies in connection with the problem under consideration were demonstrated with reference to a certain succession of the regimes of flow around V-wings, in particular, in [3] but the authors of that study did not made a necessary analysis of the flow structure and the factors generating it. Below, on the basis of the developed second-order computational code, we present certain results [4] of the calculations of symmetric and nonsymmetric flows around V-wings of different geometry at the Mach number M = 3 and moderate yaw angles and compare the results with the experimental data obtained using direct-shadow optical method for visualizing supersonic conical flows [5].…”

mentioning

confidence: 99%

See 1 more Smart Citation

Distinctive features of the shock layer flow structure in conical gas flows

2014

View full text Add to dashboard Cite

The results of a numerical and experimental investigation of the flow structure in symmetric and nonsymmetric flows around V-wings with attached shocks on the leading edges are presented. Emphasis is placed on the appearance of new critical points, including vortex Ferri singularities, in the shock layer and transformations in the flow structure with increase in the angles of attack and yaw. In particular, it is established that the flow structure in the plane of symmetry of the flow around V-wings without yaw, which involves the Mach-type shock configuration, undergoes a jumpwise variation with increase in the angle of attack. Additionally to one Ferri singularity of the node type located at the corner point of the transverse wing contour in the plane of symmetry of the flow, there arise two more critical points, those of flow divergence and convergence. The latter point is the second Ferri singularity; it is located nearer to the bridge-shaped shock of the Mach-type shock system and can be of both the node and the saddle type. In the latter case there appear two vortex Ferri singularities located at the vertices of the contact discontinuities proceeding from this critical point on both sides of the plane of symmetry. Certain data on the position of the critical points relative to the wing contour bend are presented as functions of the wing geometry, together with the transformation of the topological shock-layer flow pattern in the presence of yaw. The comparison of the results calculated within the framework of the Euler model with the experimental data on the shock-layer flow structure obtained using a special optical method for visualizing conical flows showed their good agreement.In Eqs. (1.2) the primes denote the dimensional quantities, while the subscript ∞ refers to the values of the corresponding parameters in the freestream. Here L ′ is the scale length, X = (x, y, z), and V = (u, v, w).

show abstract

Section: Results Of the Calculations Of Flow Around A Yawed Wing At Mmentioning

confidence: 99%

mentioning

confidence: 99%

Distinctive features of the shock layer flow structure in conical gas flows

2014

View full text Add to dashboard Cite

show abstract

“…2) [13,14]. The basic idea of spatial dimension reduction is that 3-D steady SSI can be transformed into a 2-D moving SSI problem with time evolution by reducing one characteristic spatial dimension to a temporal dimension.…”

Section: A Spatial Dimension Reduction Approachmentioning

confidence: 99%

“…Marconi used a second-order, finite difference marching technique to predict the inviscid supersonic/hypersonic flowfield of conical internal corners [12], and several numerical and analytical studies on corner flows formed by intersecting wedges have been conducted by Goonko et al, who discussed the effects of angles of inclination, sweep angles of the leading edges, dihedral angles, and corner ribs [13,14]. Skews et al [15], Naidoo [16], and Naidoo and Skews [17] conducted extensive research on corner flows and discovered that the flow is no longer self-similar if the sharp corner is replaced by a camber.…”

mentioning

confidence: 99%

Investigations of Three-Dimensional Shock/Shock Interactions over Symmetrical Intersecting Wedges

et al. 2016

View full text Add to dashboard Cite

This study explored inviscid supersonic corner flows induced by three-dimensional symmetrical intersecting compression wedges by introducing the spatial dimension reduction theoretical approach to transform the threedimensional steady shock/shock interaction problem into a two-dimensional pseudosteady problem; this method allows not only wave configurations, which include regular reflection and Mach reflection, to be determined accurately, but also flowfield characteristics, which include density, temperature, pressure, and total pressure recovery coefficient near the regular reflection point (or in the vicinity of the Mach reflection triple point), as well as the location and the strength of the Mach stem. Theoretical results were compared to numerical simulation (performed by solving three-dimensional inviscid Euler equations with an non-oscillatory and non-free-parameters dissipative finite difference scheme) and analyzed thoroughly. The effects of inflow Mach number, sweep angle, and wedge angle on flowfield parameters and wave configurations were also considered. The influence of sweep angle is negligible, but the effects of Mach number and wedge angle are significant.

show abstract

“…For this reason, their three-dimensional interaction was considered under the assumption that flow past the configuration is inviscid and the interacting shocks are plane. Downstream of the point C of intersection of the leading edges of the swept compression wedges the flow is equivalent to flows in the corner configurations considered in [7], where the possible types of the three-dimensional, either regular or irregular, interaction between plane shocks reflected from the plane of symmetry are determined as functions of the V and sweep angles of the dihedral-forming wedges.…”

Section: General Flow Patternmentioning

confidence: 99%

Supersonic flow past a system of two swept wedges mounted on a preliminary compression surface

Gun'ko¹,

Mazhul²

2013

Fluid Dyn

View full text Add to dashboard Cite

The results of a numerical modeling of flow past a configuration consisting of two wedges with swept leading edges, so mounted on a preliminary compression surface that the beveled wedge surfaces deflect the wedge-compressed flows counter to each other, are presented. The calculations are performed on the basis of the averaged Navier-Stokes equations, together with the SST k-ω turbulence model, at the freestream Mach number M = 6. For the configuration geometry chosen the flow pattern is characterized by an irregular interaction between the wedge-induced shocks in the plane of symmetry. These shocks also induce three-dimensional, quasi-conical separations of a turbulent boundary layer on the preliminary compression wedge. In the separation zones the flows are directed toward the plane of symmetry of the configuration and interact with one another with the formation of a typical central "bulged" separation flow zone.

show abstract

Supersonic Inviscid Corner Flows with Regular and Irregular Shock Interaction

Cited by 18 publications

References 18 publications

Distinctive features of the shock layer flow structure in conical gas flows

Distinctive features of the shock layer flow structure in conical gas flows

Investigations of Three-Dimensional Shock/Shock Interactions over Symmetrical Intersecting Wedges

Supersonic flow past a system of two swept wedges mounted on a preliminary compression surface

Contact Info

Product

Resources

About