Experiments in Fluids

, Volume 10, Issue 2, pp 175–177

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

Authors

  • C. Raju
    • Dept. of Aerospace EngineeringIndian Institute of Science
  • N. M. Reddy
    • Dept. of Aerospace EngineeringIndian Institute of Science
Technical Notes

DOI: 10.1007/BF00215027

Cite this article as:
Raju, C. & Reddy, N.M. Experiments in Fluids (1990) 10: 175. doi:10.1007/BF00215027

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.

Copyright information

© Springer-Verlag 1990