Skip to main content
SpringerLink
Log in

Physical and numerical aspects of the high-speed unsteady flow around concave axisymmetric bodies

  • Original Paper
  • Published:
CEAS Space Journal Aims and scope Submit manuscript

Abstract

The axisymmetric concave body is a typical configuration about which shock/shock interactions appear. Various shapes of axisymmetric concave bodies are used in a variety of applications in aeronautics, for example, axisymmetric jet inlets with conical centerbody, ballistic missiles drag reduction by spike, plasma or hot gas injection, parachutes for pilot-ejection capsules. However, it is well known that two distinct modes of instability appear around a concave body in the high-speed flow regime for a certain range of geometric parameters. These instabilities can cause undesirable effects such as severe vibration of the structure, heating and pressure loads. According to the experimental evidence, the unsteady flow is characterised by periodic radial inflation and collapse of the conical separation bubble formed around the forebody (pulsation). Various explanations have been given for the driving mechanism of the instabilities. In the present, merging of the leading explanations is done, and basic rules for the passive suppression of the instabilities are applied, in order to enforce their proposed driving. In addition, the effect of the flow initialisation method on the flow structure predicted by numerical simulations is examined. For certain configurations, bifurcation of the time-dependent flow has been found. This behaviour is explained with recourse to the phenomenon of hysteresis, which is an inherent feature of the examined flows.

This is a preview of subscription content, log in via an institution to check access.

Access this article

Log in via an institution

Price excludes VAT (USA)
Tax calculation will be finalised during checkout.

Instant access to the full article PDF.

Institutional subscriptions

Fig. 1
Fig. 2
Fig. 3
Fig. 4
Fig. 5
Fig. 6
Fig. 7
Fig. 8
Fig. 9
Fig. 10
Fig. 11
Fig. 12

Similar content being viewed by others

References

  1. Edney, D.: Anomalous heat transfer and pressure distributions on blunt bodies at hypersonic speeds in the presence of an impinging shock. FFA Rept. 115 (1968)

  2. Feszty, D., Badcock, K.J., Richards, B.E.: Driving mechanisms of high-speed unsteady spiked body flows, Part 1: Pulsation mode. AIAA J. 42(1), 95–106 (2004)

    Article  Google Scholar 

  3. Holden, M.S., Wandhams, T.P., Harvey, J.K., Candler, G.V.: Comparisons between DSMC and NS solutions and measurements in regions of laminar shock wave boundary layer interaction in hypersonic flows. AIAA P-2002-0435 (2002)

  4. Panaras, A.: Pulsating flows about axisymmetric concave bodies. AIAA J. 9, 804–806 (1981)

    Article  Google Scholar 

  5. Yee, H.C.: Building block for reliable non-linear numerical simulations. In: Drikakis, D., Geurts, B. (eds.) Turbulent Flow Computation. Kluwer, Dordrecht (2001)

  6. Panaras, A., Drikakis, D.: High speed unsteady flows around concave axisymmetric bodies: flow instabilities and their suppression. In: 6th European Symposium on Aerothermodynamics for Space Vehicles, Versailles, ESA-SP-659 (2009)

  7. Panaras, A., Drikakis, D.: High speed unsteady flows around spiked blunt-bodies. JFM 632, 69–96 (2009)

    Article  MATH  Google Scholar 

  8. Wood, C.: Experimental flow over spiked flows. JFM 12, 614–624 (1962)

    Article  MATH  Google Scholar 

  9. Kabelitz, H.: Grenzschichtabloesegebiet an konischen Drehkoerpern bei Hyperschallstroemung. DLR FB 71-77, 1 (1971)

  10. Morrison, J.H.: A compressible Navier-Stokes solver with two-equation and Reynolds stress turbulence closure models. NASA CR-4440 (1992)

  11. Panaras, A.: The high speed unsteady separation around concave bodies can be explained by an inviscid flow mechanism. These Annexe, VKI-Free University of Brussels (1976)

  12. Feszty, D., Badcock, K.J., Richards, B.E.: Driving mechanisms of high-speed unsteady spiked body flows, Part 2: Oscillation mode. AIAA J. 42(1), 107–113 (2004)

    Article  Google Scholar 

  13. Candler, G.V., Nompelis, I.: Computational fluid dynamics for atmospheric entry. In: VKI, Lecture Series on Hypersonic Entry and Cruise Vehicles (2008)

  14. Panaras, A.: Pressure pulses generated by the interaction of discrete vortices with an edge. JFM 154, 445–462 (1985)

    Article  MATH  Google Scholar 

  15. Panaras, A.: Shear layer-edge interaction: simulation by finite area vortices. AIAA J. 28(9), 1557–1564 (1990)

    Article  Google Scholar 

  16. Ganiev, Y.C., Gordeev, V.P., Krasilnikov, A.V., Lagutin, V.I., Otmennikov, V.N., Panasenko, A.V.: Aerodynamic drag reduction by plasma and hot-gas injection. J. Thermophys. Heat Transf. 14(1), 10–17 (2000)

    Article  Google Scholar 

  17. Elias, P.-Q., Chanetz, B., Coponet, D., Benay, R.: Mach-3 shock wave unsteadiness alleviation using a negative corona discharge. AIAA P-2000-3570 (2000)

  18. Kenworthy, M.: A study of unstable axisymmetric separation in high speed flows. PhD dissertation, Department of Aerospace and Ocean Engineering, Virginia Polytechnic Institute and State University, Blacksburg (1978)

Download references

Author information

Authors and Affiliations

  1. Department of Aerospace Sciences, Cranfield University, Cranfield, MK43 0AL, UK

    Argyris Panaras & Dimitris Drikakis

Authors
  1. Argyris Panaras
    View author publications

    You can also search for this author in PubMed Google Scholar

  2. Dimitris Drikakis
    View author publications

    You can also search for this author in PubMed Google Scholar

Corresponding author

Correspondence to Argyris Panaras.

Rights and permissions

Reprints and permissions

About this article

Cite this article

Panaras, A., Drikakis, D. Physical and numerical aspects of the high-speed unsteady flow around concave axisymmetric bodies. CEAS Space J 1, 23–32 (2011). https://doi.org/10.1007/s12567-010-0001-7

Download citation

  • Received:

  • Revised:

  • Accepted:

  • Published:

  • Issue Date:

  • DOI: https://doi.org/10.1007/s12567-010-0001-7

Keywords

Search

Navigation