Shock Waves pp 613-617

Experimental investigation of heat transfer reduction using forward facing cavity for missile shaped bodies flying at hypersonic speed

  • S. Saravanan
  • K. Nagashetty
  • G. Jagadeesh
  • K.P.J. Reddy
Conference paper

DOI: 10.1007/978-3-540-85168-4_98

Cite this paper as:
Saravanan S., Nagashetty K., Jagadeesh G., Reddy K. (2009) Experimental investigation of heat transfer reduction using forward facing cavity for missile shaped bodies flying at hypersonic speed. In: Hannemann K., Seiler F. (eds) Shock Waves. Springer, Berlin, Heidelberg

Summary

Forward facing circular nose cavity of 6 mm diameter in the nose portion of a generic missile shaped bodies is proposed to reduce the stagnation zone heat transfer. About 25% reduction in stagnation zone heat transfer is measured using platinum thin film sensors at Mach 8 in the IISc hypersonic shock tunnel. The presence of nose cavity does not alter the fundamental aerodynamic coefficients of the slender body. The experimental results along with the numerically predicted results is also discussed in this paper.

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Copyright information

© Springer-Verlag Berlin Heidelberg 2009

Authors and Affiliations

  • S. Saravanan
    • 1
  • K. Nagashetty
    • 1
  • G. Jagadeesh
    • 1
  • K.P.J. Reddy
    • 1
  1. 1.Department of Aerospace EngineeringIndian Institute of scienceIndia

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