Specific Features of the Flow in the Shock Layer near a Semicone on a Flat Plate

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Abstract

We present the results of experimental and numerical investigations of the structure of the supersonic M = 3 flow past an arrangement of a semicone on a flat plate, where the cone vertex coincides with the supersonic leading edge of the plate. Using a specially developed optical method for visualizing supersonic conical flows it is established that in the flow past the arrangement at zero or nonzero angle of attack the separation region arising on interaction of either the conical bow shock or the inner shock wave with the plate boundary layer is situated totally on the plate. The appearance of additional singular lines on the semicone surface and vortex structures of inviscid origin in the shock layer is due to the occurrence of contact discontinuities proceeding from the triple points of either the λ-configuration of shock waves accompanying the separation region on the plate or the bow shock wave arising in the flow past the arrangement with or without an angle of attack. Numerical codes for calculating the flow in the conical approximation are developed basing on the viscous and inviscid gas models. The comparison of the calculated results with experimental data shows their satisfactory agreement and possible usage domains of any of these approaches.

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About the authors

M. A. Zubin

Lomonosov Moscow State University

Author for correspondence.
Email: zubinma@mail.ru
Russian Federation, Moscow

F. A. Maksimov

Lomonosov Moscow State University

Email: f_a_maximov@mail.ru
Russian Federation, Moscow

References

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Supplementary files

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2. Fig. 1. Experimental model and coordinate system.

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3. Fig. 2. Mesh near V-shaped wing with a cone-shaped centre body.

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4. Fig. 3. Shadow flow patterns (a, b) in the plane of the cone normal and comparison with calculation data (isobars and current lines) for ideal (c, d) and viscous gas (e, f) models at angle of attack α = 0° and ϑ = 25 (a, c, e) and 30° (b, d, f). Symbols I and II are the positions of the special flowing and flowing lines taken from the pictures of the limiting current lines.

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5. Fig. 4. Picture of current lines on the model surface: angle of attack α = 0°, cone opening semi-angle ϑ = 25°.

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6. Fig. 5. Pressure distribution over the model surface at α = 0° and ϑ = 30°: symbol I - experiment, curves I, II - non-viscous and viscous calculations; line segments 1-4 - position of special lines on the model surface.

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7. Fig. 6. Contact rupture intensity ∆K (a) and Mach number Mn (b) of the velocity component normal to the beam passing through the triple point of the λ-configuration of shock waves.

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8. Fig. 7. Flow diagrams when the plate is streamlined at the angle of attack α = 0°.

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9. Fig. 8. Shadow flow patterns (a) in the plane of the cone normal moulding and comparison with calculation data (isobars and current lines) for ideal (b) and viscous gas models (c) at angles of attack α = 10° and ϑ = 25°. Symbols I and II are the positions of the special flow and flow lines taken from the pictures of the limiting current lines.

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10. Fig. 9. Contact rupture intensity ∆K (a) and Mach number Mn (b) of the velocity component normal to the beam passing through the branching point on the head shock.

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11. Fig. 10. Pressure distribution over the model surface at α = 10° and ϑ = 25°: symbol I - experiment, curves I, II - non-viscous and viscous calculations; line segments 1-4 - location of special lines on the model surface.

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12. Fig. 11. Schemes of the flow when the plate is streamlined at the angle of attack α.

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