Certificate of Registration Media number Эл #ФС77-53688 of 17 April 2013. ISSN 2308-6033. DOI 10.18698/2308-6033
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V-shaped wings and a central body in a supersonic flow

Published: 21.05.2018

Authors: Zubin M.A., Maksimov F.A., Ostapenko N.A.

Published in issue: #5(77)/2018

DOI: 10.18698/2308-6033-2018-5-1763

Category: Aviation and Rocket-Space Engineering | Chapter: Aerodynamics and Heat Transfer Processes in Aircrafts

We present results of a numerical investigation of flow structure aroundV-shaped wings featuring a central body in the form of a truncated cone. The investigation assumed the ideal gas model, with a shock wave attached at the leading edges. We determined the cone half-angle for the case when inviscid vortex structures arise in the shock layer when the flow around the body is symmetrical. These structures are known as Ferri vortex singularities. We found that their appearance and existence are in good agreement with criteria derived previously. These criteria are related to the intensity of the contact discontinuity originating in branching points of the leading shock wave and to the Mach number of that component of the undisturbed flow velocity vector that is perpendicular to the conical coordinate system ray passing through the same branching point.

For a wing featuring a 180° aperture angle and a 90° angle between cantilevers (half-cone on a plate) we determine the angles of the half-cone, attack and yaw that cause inviscid vortex structures to appear. We confirm that it is possible to predict them using the criteria determined previously.

We investigated the way the cone affects the aerodynamic fineness of its composition with the V-shaped wing when the Mach number М = 6. We found that optimum body geometry depends heavily on the value the lift coefficient takes. When this value increases, the composition may comprise a central body and feature the aperture angle of the V-shaped wing γ > π; it may be a flat triangular wing and a V-shaped wing with the angle γ < π

[1] Krayko A.N., Pudovikov D.E., Yakunina G.E. Teoriya aerodinamicheskikh form, blizkikh k optimalnym [Theory of nearly optimum aerodynamic shapes]. Moscow, Yanus-K Publ., 2001, 132 p.
[2] Lapygin V.I., Yakunina G.E. PMM — J. Appl. Math. Mech., 2009, vol. 73, no. 5, pp. 717–730.
[3] Küchemann D. Aerodynamic design of aircraft. Oxford, Pergamon Press, 574 p. [In Russ.: Küchemann D. Aerodinamicheskoe proektirovanie samoletov. Moscow, Mashinostroenie Publ., 1983, 655 p.].
[4] Maykapar G.I., Pyatnova A.I. Uchenye zapiski TsAGI — TsAGI Science Journal, 1984, vol. XV, no. 1, pp. 104–109.
[5] Maykapar G.I. Uchenye zapiski TsAGI — TsAGI Science Journal, 2005, vol. XXXVI, no. 3–4, pp. 59–67.
[6] Nonweiler T.R.F. Journal of the Royal Aeronautical Society, 1963, vol. 67, pp. 39–40.
[7] Gonor A.L. PMM — J. Appl. Math. Mech., 1963, no.1, pp. 25–30.
[8] Golubinskiy A.I., Keldysh V.V., Neyland V.Ya. Nekotorye novye rezultaty v sverkhzvukovoy i giperzvukovoy gazovoy dinamike [Certain new results in supersonic and hypersonic gas dynamics] Sovremennye problemy gazovoy dinamiki. Sb. trudov [Contemporary problems of gas dynamics]. Moscow, Mir Publ., 1971.
[9] Zubin M.A., Maksimov F.A., Ostapenko N.A. Dokl. Phys., 2014, vol. 434, no. 3, pp. 282–288.
[10] Maximov F.A., Ostapenko N.A., Zubin M.A. Conical flows near V-shaped wings with attached shock waves on leading edges. Progress in flight physics. EUCAAS advances in aerospace sciences book series. Москва, TORUS PRESS, 2015, vol. 7, pp. 453–474.
[11] Zubin M.A., Maksimov F.A., Ostapenko N.A. Izv. RAN, MZhG — Fluid Dynamics. A Journal of Russian Academy of Sciences, 2015, no. 1, pp. 113–134.
[12] Avduevskiy V.S., Gretsov V.K. Izv. AN SSSR, MZhG — Fluid Dynamics, 1970, no. 6, pp. 112–115.