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Shock Waves pp 239-244 | Cite as

Effect of gas injection on drag and surface heat transfer rates for a 30° semi-apex angle blunt body flying at Mach 5.75

  • N. Sahoo
  • V. Kulkarni
  • G. Jagadeesh
  • K. P. J. Reddy
Conference paper

Abstract

Effect of coolant gas injection in the stagnation region on the surface heat transfer rates and aerodynamic drag for a large angle blunt body flying at hypersonic Mach number is reported for two stagnation enthalpies. A 60° apex-angle blunt cone model is employed for this purpose with air injection at the nose through a hole of 2mm diameter. The convective surface heating rates and aerodynamic drag are measured simultaneously using surface mounted platinum thin film sensors and internally mounted accelerometer balance system, respectively. About 35–40% reduction in surface heating rates is observed in the vicinity of stagnation region whereas 15–25% reduction in surface heating rates is felt beyond the stagnation region at stagnation enthalpy of 1.6MJ/kg. The aerodynamic drag expressed in terms of drag coefficient is found to increase by 20% due to the air injection.

Keywords

Aerodynamic Drag Film Cool Stagnation Region Stanton Number Shock Tunnel 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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Copyright information

© Tsinghua University Press and Springer-Verlag Berlin Heidelberg 2005

Authors and Affiliations

  • N. Sahoo
    • 1
  • V. Kulkarni
    • 1
  • G. Jagadeesh
    • 1
  • K. P. J. Reddy
    • 1
  1. 1.Indian Institute of ScienceBangaloreIndia

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