Experiments in Fluids

, Volume 46, Issue 2, pp 343–353

Image-based force and moment measurement in hypersonic facilities

Research Article

Abstract

This article addresses the problem of force and moment measurement in short-duration hypersonic facilities. An image-based technique is described in which the motion of a free-flying model is tracked over a sequence of high-speed digital images. Force components are derived from the calculated trajectory by assuming constant acceleration during the test time. A linear version of the technique, appropriate for simple model geometries, is first outlined and the technique’s precision is estimated. A nonlinear version, suitable for more generalised body shapes, is then described in the context of a series of experiments to determine the aerodynamic characteristics of the NASA Orion vehicle in the T5 hypervelocity shock tunnel. The accuracy of these measurements was adversely affected by both the choice of light source and test-gas luminosity, but these experiments nevertheless show image-based measurements to be, at the very least, a promising supplement to standard accelerometer-based techniques.

References

  1. Hornung H, Sturtevant B, Bélanger J, Sanderson S, Brouillette M (1991) Performance of the new free-piston shock tunnel T5 at GALCIT. In: Proceedings of 18th International Symposium on Shock Waves, Sendai, Japan. Springer, BerlinGoogle Scholar
  2. Joarder R, Jagadeesh J (2004) A new free floating accelerometer balance system for force measurement in shock tunnels. Shock Waves 13:409–412CrossRefGoogle Scholar
  3. Laurence SJ, Deiterding R, Hornung H (2007) Proximal bodies in hypersonic flow. J Fluid Mech 590:209–237MATHCrossRefMathSciNetGoogle Scholar
  4. Lordi J, Mates R, Moselle J (1966) Computer program for the numerical solution of nonequilibrium expansions of reacting gas mixtures. Tech. Rep. NASA CR-472, NASAGoogle Scholar
  5. McIntosh M (1969) A computer program for the numerical calculation of equilibrium and perfect gas conditions in shock tunnels. Tech. Rep. CPD 169, Australian Defense Scientific ServiceGoogle Scholar
  6. Mee D (2003) Dynamic calibration of force balances for impulse hypersonic facilities. Shock Waves 12:443–455CrossRefGoogle Scholar
  7. Mee D, Daniel W, Simmons J (1996) Three-component force balance for flows of millisecond duration. AIAA J 34(3):590–595CrossRefGoogle Scholar
  8. Naumann K, Ende H, Mathieu G, George A (1993) Millisecond aerodynamic force measurement with side-jet model in the ISL shock tunnel. AIAA J 31(6):590–595CrossRefGoogle Scholar
  9. Robinson M, Mee D, Tsai C, Bakos R (2004) Three-component force measurements on a large scramjet in a shock tunnel. J Spacecraft Rockets 41(3):416–425CrossRefGoogle Scholar
  10. Sahoo N, Mahapatra D, Jagadesh G, Gopalakrishnan S, Reddy K (2003) An accelerometer balance system for measurement of aerodynamic force coefficients over blunt bodies in a hypersonic shock tunnel. Meas Sci Technol 14:260–272CrossRefGoogle Scholar
  11. Sanderson S, Simmons J (1991) Drag balance for hypervelocity impulse facilities. AIAA J 12:2185–2191Google Scholar
  12. Storkmann V, Olivier H, Gronig H (1998) Force measurement in hypersonic impulse facilities. AIAA J 36:342–348CrossRefGoogle Scholar
  13. Tanno H, Itoh K, Saito K, Abe A, Takayama K (2004) Shock wave interaction with a sphere in a shock tube. In: International symposium on interdisciplinary shock wave research, Interdisciplinary Shock Wave Research Center, pp 483–497Google Scholar
  14. Warren W, Kaegi E, Geiger R (1961) Shock tunnel experimental techniques for force and moment and surface flow direction measurements. ARS J 31(1):82–83Google Scholar

Copyright information

© Springer-Verlag 2008

Authors and Affiliations

  1. 1.Graduate Aeronautical LaboratoriesCalifornia Institute of TechnologyPasadenaUSA

Personalised recommendations