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Investigation of the supersonic flow around a pointed elliptical cone at an angle of attack

  • V. N. Vetlutskii
  • V. L. Ganimedov
Article

Abstract

The picture of ideal gas flow around cones at zero and low angles of attack has been well studied by using approximate methods [1], and results for high angles of attack have been obtained mainly numerically [2–7]. At high angles of attack it is sensible to examine inviscid flow only up to some generator on the downwind side of the cone at which boundary-layer separation occurs. Hence, the domain where the flow can be considered inviscid yields the main contribution to the magnitude of the aerodynamic forces and the heat fluxes [5, 9]. A picture of the supersonic flow around a pointed elliptical cone is obtained in this paper by the numerical solution of the gasdynamics equations. The whole flow domain is computed at low angles of attack while the solution at high angles is obtained in a domain bounded by some surface of three-dimensional type [10]. The dependence of the flow parameters on the angle of attack is studied when the shock is attached to the cone apex. In contrast to a circular cone, at low angles of attack two spreading lines occur on the surface of an elliptical cone, to which the maximum pressure corresponds. As the angle of attack increases, these lines come together and merge at a certain time. At high angles of attack the flow picture is analogous to a circular cone with a pressure maximum in the plane of symmetry.

Keywords

Heat Flux High Angle Supersonic Flow Flow Parameter Aerodynamic Force 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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Literature cited

  1. 1.
    B. M. Bulakh, Nonlinear Conical Gas Flows [in Russian], Nauka, Moscow (1970).Google Scholar
  2. 2.
    K. I. Babenko, G. P. Voskresenskii, A. N. Lyubimov, and V. V. Rusanov, Three-Dimensional Ideal Gas Flow around Smooth Bodies [in Russian], Nauka, Moscow (1964).Google Scholar
  3. 3.
    G. P. Voskresenskii, “Numerical solution of the problem of supersonic gas flow around the upper surface of a delta wing in the expansion region,” Zh. Prikl. Mekhan. i Tek. Fiz., No. 6 (1973).Google Scholar
  4. 4.
    P. I. Chushkin, “Supersonic flow around a cone at an angle of attack,” in: Collection of Theoretical Papers on Hydromechanics [in Russian], Izv. VTS Akad. Nauk SSSR, Moscow (1970).Google Scholar
  5. 5.
    A. P. Bazzhin, O. N. Trusova, and N. F. Chelysheva, “Computation of the perfect gas flow around elliptical, cones at large angles of attack,” Izv. Akad. Nauk SSSR, Mekhan. Zhid. i Gaza, No. 4 (1968); Tr. Tg AGI, No. 1144 (1969).Google Scholar
  6. 6.
    N. S. Bachmanova, V. I. Lapygin, and Yu. M. Lipnitskii, “Investigation of the supersonic flow around circular cones at large angles of attack,” Izv. Akad. Nauk SSSR, Mekhan. Zhid. i Gaza, No. 6 (1973).Google Scholar
  7. 7.
    M. Ya. Ivanov and A. N. Kraiko, “On the analysis of supersonic flow around conical bodies,” Zh. Vychisl. Matem. i Matem. Fiz.,13, No. 6 (1973).Google Scholar
  8. 8.
    V. S. Avduevskii and K. I. Medvedev, “Investigation of laminar boundary-layer separation on a cone at an angle of attack,” Izv. Akad. Nauk SSSR, Mekhan. Zhid. i Gaza, No. 3 (1966).Google Scholar
  9. 9.
    G. V. Smygina and A. Ya. Yushin, “Experimental investigation of heat transfer to delta wing models comprised of two elliptical half-cones with different values of the ellipticity coefficient, in a shock tube at Mt8 = 13.6,” Tr. TsAGI, No. 1106 (1968).Google Scholar
  10. 10.
    V. V. Rusanov, “Three-dimensional supersonic gas flow around a blunt body,” Zh. Vychisl. Matem. i Matem. Fiz.,8, No. 3 (1968).Google Scholar
  11. 11.
    A. N. Lyubimov and V. V. Rusanov, Gas Flow around Blunt Bodies [in Russian], Nauka, Moscow (1970).Google Scholar
  12. 12.
    V. N. Vetlutskii and V. L. Ganimedov, “On the solution of the problem of supersonic flow around a conical body by the buildup method,” Numerical Methods in the Mechanics of a Continuous Medium [in Russian], Vol. 4 No. 3 (1973).Google Scholar
  13. 13.
    A. Ferri, “Supersonic flow around circular cones at angles of attack,” NACA Report No. 1045 (1951).Google Scholar
  14. 14.
    A. P. Bazzhin, “Analysis of perfect gas flow around plane delta wings at large angles of attack,” Tr. TsAGI, No. 1034 (1966).Google Scholar
  15. 15.
    V. V. Sychev, “Three-dimensional hypersonic gas flow around slender bodies at high angles of attack,” Prikl. Matem. i Mekhan.,24, No. 2 (1960).Google Scholar
  16. 16.
    A. Martellucci, “An extension of the linearized characteristics method for calculating the supersonic flow around elliptic cones,” J. Aero. Sci.,27, No. 9 (1960).Google Scholar
  17. 17.
    A. I. Shvets, “Investigation of the flow around elliptic cones,” Izv. Akad. Nauk SSSR, Mekhan. Zhid. i Gaza, No. 1 (1966).Google Scholar
  18. 18.
    G. G. Chernyi, “Hypersonic flow around wings at high angles of attack,” Dokl. Akad. Nauk SSSR,155, No. 2 (1964).Google Scholar

Copyright information

© Plenum Publishing Corporation 1976

Authors and Affiliations

  • V. N. Vetlutskii
    • 1
  • V. L. Ganimedov
    • 1
  1. 1.Novosibirsk

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