Direct measurements of skin friction in complex supersonic flows Conference Paper uri icon


  • 1997, American Institute of Aeronautics and Astronautics, Inc. Experimental studies of the direct measurement of skin friction in complex supersonic and hypersonic flows were conducted. A wall-mounted, miniature, cantilever sensor with semiconductor strain gages at the beam base was used to measure the small tangential shear force on a non-intrusive floating element. The use of a double-base silicon rubber compound in the sensing gap reduced maintenance requirements with a small increase in manufacturing and calibration complexity. Measurements were made in a scramjet model at the GASL HYPULSE facility under harsh flow conditions simulating Mach 14 enthalpy with a run time of under half a millisecond. Cold flow tests were performed in the Virginia Tech Supersonic Tunnel at Mach 2.4 to further verify the concept and establish pressure gradient sensitivity in the case of a shock wave impacting directly on the gage head. Measured wall shear values agreed well with theoretical and numerical predictions.

published proceedings

  • 35th Aerospace Sciences Meeting and Exhibit

author list (cited authors)

  • Novean, M. G., Schetz, J. A., & Bowersox, R.

complete list of authors

  • Novean, MG||Schetz, JA||Bowersox, RDW

publication date

  • January 1997