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

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Shock Waves

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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References

  1. Reinecke WG and Sherman M 7(1993) The survivability and performance on hypervelocity projectiles, In Proc. of the 14th Intl Symposium on Ballistics.

    Google Scholar 

  2. Reinecke WG and Guillot MJ (1995) Full scale ablation testing of candidate hypervelocity nose tip materials, In Proc. of the 15th Intl Symposium on Ballistics.

    Google Scholar 

  3. Johnson RH 7(1959), Instability in hypersonic flow about blunt bodies, Phys. of Fluid, 2, p.526-532

    Article  MATH  Google Scholar 

  4. Engblom WA, Goldstein DB, Ladoon D, Schneider SP (1997) Fluid dynamics of hypersonic forward-facing cavity flow. AIAA Journal of Spacecraft and Rockets, 33 (3), 353-359

    Article  Google Scholar 

  5. Ladoon DW, Schneider SP, Schmisseur JD (1998) Physics of resonance in a supersonic forward-facing cavity. Journal of Spacecraft and Rockets, 33 (5), 626-632.

    Article  Google Scholar 

  6. Silton SI, Goldstein DB (2005) Use of an axial nose-tip cavity for delaying ablation onset in hypersonic flow. Journal of Fluid Mechanics, 528, 297-321

    Article  MATH  Google Scholar 

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Author information

Authors and Affiliations

  1. Department of Aerospace Engineering, Indian Institute of science, Bangalore, India

    S. Saravanan, K. Nagashetty, G. Jagadeesh & K.P.J. Reddy

Authors
  1. S. Saravanan
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  2. K. Nagashetty
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  3. G. Jagadeesh
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  4. K.P.J. Reddy
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Editor information

Editors and Affiliations

  1. German Aerospace Center, DLR, Bunsenstraße 10, 37073 Göttingen, Germany

    Klaus Hannemann

  2. French-German Research Institute of Saint Louis, ISL, 5 rue du Général Cassagnou, 68301 Saint-Louis, France

    Friedrich Seiler

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© 2009 Springer-Verlag Berlin Heidelberg

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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. https://doi.org/10.1007/978-3-540-85168-4_98

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  • DOI: https://doi.org/10.1007/978-3-540-85168-4_98

  • Publisher Name: Springer, Berlin, Heidelberg

  • Print ISBN: 978-3-540-85167-7

  • Online ISBN: 978-3-540-85168-4

  • eBook Packages: EngineeringEngineering (R0)

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