Advertisement

Shock Waves pp 143-148 | Cite as

Aerodynamic characteristics of generic flight vehicle configuration from shock tunnel tests

  • A. G. Sarwade
  • A. S. Narayana
  • S. Panneerselvam
  • N. Sahoo
  • S. Saravanan
  • G. Jagadeesh
  • K. P. J. Reddy
Conference paper

Abstract

A generic flight vehicle configuration has been designed as a possible candidate for hypersonic flight. Aerodynamic force coefficients over the test model configuration for different angles of attack are measured using a three-component accelerometer force balance system. Experiments are conducted in HST2 shock tunnel facility of IISc at an enthalpy of 2 MJ/kg and nominal Mach number of 6. This data will be useful for validating numerical results obtained by CFD techniques.

Keywords

Aerodynamic Force Balance System Shock Tunnel Drive Section Short Test Time 
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.

Preview

Unable to display preview. Download preview PDF.

Unable to display preview. Download preview PDF.

References

  1. 1.
    J. D. Anderson: Hypersonic and High Temperature Gas Dynamics. (McGraw-Hill, New York, 1989)Google Scholar
  2. 2.
    W. H. Rae and A. Pope: Low Speed Wind Tunnel Testing. (Wiley Publishing: New York, 1984)Google Scholar
  3. 3.
    B. F. R. Ewald: Multi-component force balances for conventional and cryogenic wind tunnels. Measurement Science and Technology 11, 81 (2000)ADSCrossRefGoogle Scholar
  4. 4.
    D. J. Mee, W. J. T. Daniel and S. M. Simmons: Three-component force balance for flows of millisecond duration. AIAA Journal 34(1), 590 (1996)ADSCrossRefGoogle Scholar
  5. 5.
    Niranjan Sahoo, D. R. Mahapatra, G. Jagadesh, S. Gopalakrishnan and K. P. J. Reddy: Aerodynamic force measurements on 60° apex-angle blunt cones flying at Mach 5. 75 using a three-component accelerometer balance, AIAA Paper 2002-5204 (2002)Google Scholar
  6. 6.
    Niranjan Sahoo, D. R. Mahapatra, G. Jagadesh, S. Gopalakrishnan and K. P. J. Reddy: An accelerometer balance system for measurement of aerodynamic force co-efficients over blunt bodies in hypersonic shock tunnel. Measurement Science and Technology 14, 260 (2003)ADSCrossRefGoogle Scholar
  7. 7.
    R. J. Vidal: Model instrumentation techniques for heat transfer and force measurements in a hypersonic shock tunnel. Cornell Aeronautical Laboratory Report WADC TN 56-315, February (2003)Google Scholar
  8. 8.
    N. M. Reddy: ‘Aerodynamic force measurements in the hypersonic shock tunnel’. In: Shock Tubes and Waves, 14th International Symposium, Sydney, August 1983. (New South Wales Univ. press), pp. 358Google Scholar

Copyright information

© Tsinghua University Press and Springer-Verlag Berlin Heidelberg 2005

Authors and Affiliations

  • A. G. Sarwade
    • 1
  • A. S. Narayana
    • 1
  • S. Panneerselvam
    • 1
  • N. Sahoo
    • 2
  • S. Saravanan
    • 2
  • G. Jagadeesh
    • 2
  • K. P. J. Reddy
    • 2
  1. 1.Defence Research and Development LaboratoryHyderabadIndia
  2. 2.Department of Aerospace EngineeringIndian Institute of ScienceBangaloreIndia

Personalised recommendations