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Experimental investigation of drag reduction by forward facing high speed gas jet for a large angle blunt cone at Mach 8

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Abstract

Substantial aerodynamic drag, while flying at hypersonic Mach number, due to the presence of strong standing shock wave ahead of a large-angle bluntcone configuration, is a matter of great design concern. Preliminary experimental results for the drag reduction by a forward-facing supersonic air jet for a 60° apexangle blunt cone at a flow Mach number of 8 are presented in this paper. The measurements are carried out using an accelerometer-based balance system in the hypersonic shock tunnel HST2 of the Indian Institute of Science, Bangalore. About 29% reduction in the drag coefficient has been observed with the injection of a supersonic gas jet.

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References

  • Balla Venukumar, Jagadeesh G, Reddy K P J 2006 Counterflow drag reduction by supersonic jet for a blunt body in hypersonic flow. Phys. Fluids 18: Art. No. 118104

  • Josyula E, Pinney M, Blake W M 2001 Application of a counterflow drag reduction technique in high speed systems. AIAA Paper 01-2437.

  • Hayashi K, Asoy S 2003 Effect of pressure ratio on aerodynamic heating reduction due to opposing jet. AIAA Paper 03-4041

  • Menezes V, Saravanan S, Jagadeesh G, Reddy K P J 2003 Experimental investigations of hypersonic flow over highly blunted cones with aerospikes. AIAA J. 41: 1955–1966

    Article  Google Scholar 

  • Menezes V, Kumar S, Maruta K, Reddy K P J, Takayama K 2005 Hypersonic flow over a multi-step afterbody, Shock Waves 14: 421–424

    Article  Google Scholar 

  • Peter F I, Donn B K 1987 High-speed aerodynamics of several blunt-cone configurations. J. Spacecr. Rockets 24: 127–132

    Article  Google Scholar 

  • Reddy K P J, Jagadeesh G, Menezes V, Sahoo N 2006 Experimental investigations of aerodynamic drag management for hypersonic vehicle configurations. In Proc. 11th Asian Congress of Fluid Mechanics, Kuala Lumpur, Malaysia

  • Reddy N M, Nagashetty K, Jagadeesh G, Reddy K P J 1996 Review of research investigations during 1975–1995 in IISc hypersonic shock tunnel (HST1) at hypersonic Mach numbers. Sādhanā 21: 741–773

    Google Scholar 

  • Sahoo N, Kulkarni V, Saravanan S, Jagadeesh G, Reddy K P J 2005 Film cooling effectiveness on a large angle blunt cone flying at hypersonic speed. Phys. Fluids 17(3): 1–11

    Article  Google Scholar 

  • Satheesh K, Jagadeesh G 2005 An experimental study of the effect of plasma injection on the wave drag on a blunt body in a hypersonic flow. Shock Waves — Proc. 25th Int. Symp. on Shock Waves, Bangalore (eds) G Jagadeesh, E Arunan, K P J Reddy, pp 89–93

  • Srinivasan G R, Chamberlain R R 2004 Drag reduction of spiked missile by heat addition. AIAA J. paper 04-4714

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Authors and Affiliations

  1. Department of Aerospace Engineering, Indian Institute of Science, Bangalore, 560 012, India

    Balla Venukumar & K. P. J. Reddy

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  1. Balla Venukumar
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  2. K. P. J. Reddy
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Venukumar, B., Reddy, K.P.J. Experimental investigation of drag reduction by forward facing high speed gas jet for a large angle blunt cone at Mach 8. Sadhana 32, 123–131 (2007). https://doi.org/10.1007/s12046-007-0011-0

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  • DOI: https://doi.org/10.1007/s12046-007-0011-0

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