Chapter

Shock Waves

pp 613-617

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

  • S. SaravananAffiliated withDepartment of Aerospace Engineering, Indian Institute of science
  • , K. NagashettyAffiliated withDepartment of Aerospace Engineering, Indian Institute of science
  • , G. JagadeeshAffiliated withDepartment of Aerospace Engineering, Indian Institute of science
  • , K.P.J. ReddyAffiliated withDepartment of Aerospace Engineering, Indian Institute of science

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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.