Conical gas flows with shock waves and turbulent boundary layer separation

Zubin, M. A.; Ostapenko, N. A.; Chulkov, A. A.

doi:10.1134/s0015462812020135

Cited by 8 publications

(12 citation statements)

References 4 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Thus, the results of the calculations within the framework of the Euler model quite adequately reproduce the salient features of the actual shock-layer flow structure in the regimes of transition from the symmetric to nonsymmetric flow around V-wings if only the intensity of the contact discontinuity generated by the λ shock configuration is not comparable with (or greater than) the intensity of the contact discontinuities proceeding from the branching points of the bow shock [6]. …”

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

confidence: 77%

“…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]. The grid of the other numbered curves corresponds to different intensities of the internal shock on the left panel wall.…”

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

confidence: 99%

“…The second-order approximation turned out to be necessary, since in the transitional regimes from the symmetric flow with several critical points in the shock layer to flow at yaw [6] the accuracy of the first-order schemes is insufficient. Here, we present certain results of the calculations of flows past wings at the freestream Mach number M = 3 and the geometrical parameters given in Table 1.…”

Section: Methods Of Solutionmentioning

confidence: 99%

“…Later, with increasing possibilities of the computational technologies, the vortex Ferri singularities were detected. Their appearance and disappearance was attributable to the intensity of the generating contact discontinuities [10,11], since on the boundary of the elliptic region of the conical inviscid-gas flow there are no singularities other than the contact discontinuities proceeding from the branching points on the bow shock.…”

Section: Condition Of the Existence Of The Vortex Ferri Singularitiesmentioning

confidence: 99%

“…In these cases, on the boundary of the elliptic region (internal relative to the shock waves and Mach cones) there appear new singularities due to the contact discontinuities generated by λ shock configurations above the boundary layer separation zone. Depending on the relation between the contact discontinuity intensities, on the boundary of the elliptic region of the conical flow new singularities in the shock-layer flow structure, as compared with those in an inviscid gas, can arise, including new vortex Ferri singularities [6].…”

Section: Condition Of the Existence Of The Vortex Ferri Singularitiesmentioning

confidence: 99%

See 4 more Smart Citations

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

2014

Self Cite

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: 77%

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

confidence: 99%

Section: Methods Of Solutionmentioning

confidence: 99%

Section: Condition Of the Existence Of The Vortex Ferri Singularitiesmentioning

confidence: 99%

Section: Condition Of the Existence Of The Vortex Ferri Singularitiesmentioning

confidence: 99%

See 3 more Smart Citations