Experiments in Fluids

, Volume 10, Issue 2–3, pp 175–177 | Cite as

Aerodynamic force measurements over missile configurations in IISc shock tunnel at M =3.85 and 9.15

  • C. Raju
  • N. M. Reddy
Technical Notes

Conclusions

Three most commonly used missile configurations are tested in a shock tunnel, and a new set of aerodynamic data is obtained at M = 3.85 and 9.15 by using an accelerometer balance system. The agreement between theory and experiment is generally good for all the cases. Noticeable decreases in measured CLand Cmvalues are obtained at M=9.15, compared to those at M = 3.85. The dependence of CDon M seems to be insignificant.

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References

  1. Channa Raju 1989: Aerodynamic force measurements over missile shaped bodies. M. E. Thesis, Dept. of Aerospace Engineering, IISc, Bangalore, IndiaGoogle Scholar
  2. Joshi, M. V.; Reddy, N. M. 1986: Aerodynamic force measurements over missile configurations in IISc shock tunnel at M = 5.5 Exp. Fluids 4, 338–340Google Scholar
  3. Reddy, N. M. 1983: Aerodynamic force measurements in the IISc shock, tunnel. In: Proc. XIV. Int. Symp. Shock Tubes and Shock Waves, Sydney, Australia, pp 358–362Google Scholar
  4. Truitt, R. W. 1959: Hypersonic Aero dynamics, New York: Ronald PressGoogle Scholar

Copyright information

© Springer-Verlag 1990

Authors and Affiliations

  • C. Raju
    • 1
  • N. M. Reddy
    • 1
  1. 1.Dept. of Aerospace EngineeringIndian Institute of ScienceBangaloreIndia

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