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Shock Waves

, 18:53 | Cite as

Experimental investigations on the effect of energy deposition in hypersonic blunt body flow field

  • K. Satheesh
  • G. JagadeeshEmail author
Original Article

Abstract

We describe here an experimental study on the effect of energy deposition in the flow field of a 120° blunt cone, carried out in a hypersonic shock tunnel. The energy deposition is realised using an electric arc discharge generated between two electrodes placed in the free stream, and various parameters influencing the effectiveness of this technique is studied. The experimental observations suggest that the location of energy deposition has a vital role in dictating the flow structure, with no noticeable effects being produced on the flow field when the discharge was located close to the body (0.416 times body diameter). In addition, the nature of the test gas and the free stream density are also identified as important parameters. In these experiments, a maximum drag reduction of ~50% and ~84% reduction in stagnation point heating rate has been observed as a result of energy addition. The experimental evidence also indicates that the relaxation of the internal degrees of freedom plays a major role in the alteration of the hypersonic blunt body flow structure and that under the specific conditions encountered in our experiments, the energy deposition is not strong enough to create a shock on its own, but the heated region behind the energy source interacts with the blunt body shock resulting in the flow field alteration.

Keywords

Energy deposition Flow field alteration Hypersonics 

PACS

47.40.ki 47.85.L- 

References

  1. 1.
    Bogdonoff S.M., Vas I.E.: Preliminary investigations of spiked bodies at hypersonic speeds. J Aero/Space Sci. 26(2), 65–74 (1959)zbMATHGoogle Scholar
  2. 2.
    Maull D.J.: Hypersonic flow over axially symmetric spiked bodies. J Fluid Mech. 8(4), 584–592 (1960)CrossRefMathSciNetGoogle Scholar
  3. 3.
    Finley P.J.: The flow of a jet from a body opposing a supersonic stream. J. Fluid Mech. 26(2), 337–368 (1966)CrossRefGoogle Scholar
  4. 4.
    Myrabo, L.N., Raizer, Yu.P.: Laser induced air spikes for advance trans atmospheric vehicles. In: 25th AIAA Plasma Dynamics and Lasers Conference, Reno, AIAA 94-2451 (1994)Google Scholar
  5. 5.
    Levin V.A., Terent’eva L.V.: Effect of a local energy supply region on 3-D flow around a cone. Fluid Dyn. 31(3), 388–394 (1999)Google Scholar
  6. 6.
    Riggins D., Nelson H.F., Johnson E.: Blunt-body wave drag reduction using focused energy deposition. AIAA J. 37(4), 460–467 (1999)Google Scholar
  7. 7.
    Macheret, S.O., Shneider, M.N., Miles, R.B.: Scramjet inlet control by Off-Body Energy Addition: A Virtual Cowl: In: 41st AIAA Aerospace Sciences Meeting and Exhibit, Reno, AIAA 2003-0032 (2003)Google Scholar
  8. 8.
    Adelgren, R.G., Hong, Y., Elliott, G.S., Knight, D.D., Beutner, T.J., Zheltovodov, A.A., Ivanov, M., Khotyanovsky, D.: Localised flow control by laser energy deposition applied to Edney IV shock impingement and intersecting shocks. In: 41st AIAA Aerospace Sciences Meeting and Exhibit, Reno, AIAA 2003-31 (2003)Google Scholar
  9. 9.
    Hartley, C.S., Portwood, T.W., Filippelli, M.V., Myrabo, L.N., Nagamatsu, H.T., Miles, R.B.: Experimental/ computational investigation of drag reduction by electric-arc air spikes at mach 10 In: 42nd AIAA Aerospace Sciences Meeting and Exhibit, Reno, AIAA 2004-0035 (2004)Google Scholar
  10. 10.
    Lashkov, V.A., Mashek, I.Ch., Anisimov, Yu.I., Ivanov, V.I., Kolesnichenko, Yu.F., Ryvkin, M.I., Gorynya, A.A.: Gas dynamic effect of microwave discharge on supersonic cone-shaped bodies. In: 42nd AIAA Aerospace Sciences Meeting and Exhibit, Reno, AIAA 2004-0671 (2004)Google Scholar
  11. 11.
    Satheesh K., Jagadeesh G.: Effect of concentrated energy deposition on the aerodynamic drag of a blunt body in hypersonic flow. Phys. Fluids 19, 031701 (2007). doi: 10.1063/1.2565663 CrossRefGoogle Scholar
  12. 12.
    Satheesh K., Jagadeesh G., Reddy K.P.J.: High speed schlieren facility for visualisation of flow fields in hypersonic shock tunnels. Curr. Sci. 92(1), 56–60 (2007)Google Scholar
  13. 13.
    Sahoo N., Suryavamshi K., Reddy K.P.J., Mee D.J.: Dynamic force balances for short-duration hypersonic testing facilities. Exp. Fluids 38, 606–614 (2005)CrossRefGoogle Scholar
  14. 14.
    Sanderson S.R., Simmons J.M.: Drag balance for hypersonic impulse facilities. AIAA J. 29, 2185–2191 (1991)CrossRefGoogle Scholar
  15. 15.
    Joarder R., Jagadeesh G.: A new free floating accelerometer balance system for force measurement in shock tunnels. Shock Waves 13(5), 409–412 (2003)CrossRefGoogle Scholar
  16. 16.
    Schultz, D.L., Jones, T.V.: Heat-transfer measurements in short-duration hypersonic facilities. AGARDograph, No. 163 (1973)Google Scholar
  17. 17.
    Cook W.J., Felderman E.J.: Reduction of data from thin-film heat-transfer gages: a concise numerical technique. AIAA J. 4(3), 561 (1966)CrossRefGoogle Scholar
  18. 18.
    Moffat R.J.: Describing the uncertainties in experimental results. Exp. Thermal Fluid Sci. 1(1), 3–17 (1988)CrossRefGoogle Scholar
  19. 19.
    Kolesnichenko, Yu.F., Brovkin, V.G., Azarova, O.A., Grudnitsky, V.G., Lashkov, V.A., Mashek, I.Ch.: Microwave energy release regimes for drag reduction in supersonic flows. In: 40th AIAA Aerospace Sciences Meeting and Exhibit, Reno, AIAA 2002-0353 (2002)Google Scholar
  20. 20.
    Ionikh, Y.Z., Naira, V., Chernysheva, Y.A.P., Macheret, S.O., Martinelli, L., Miles, R.B.: Shock wave propagation through glow discharge plasmas: evidence of thermal mechanism of shock dispersion. In: 38th AIAA Aerospace Sciences Meeting and Exhibit, Reno, AIAA 2000-0714 (2004)Google Scholar

Copyright information

© Springer-Verlag 2008

Authors and Affiliations

  1. 1.Department of Aerospace EngineeringIndian Institute of ScienceBangaloreIndia

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