Accession Number:

ADA456817

Title:

Quiet Tunnel Experiments of Shock/Boundary Layer Interactions

Descriptive Note:

Final technical rept. Jan-Dec 2005

Corporate Author:

DUKE UNIV DURHAM NC OFFICE OF SPONSORED PROGRAMS

Personal Author(s):

Report Date:

2006-03-03

Pagination or Media Count:

92.0

Abstract:

The effect of freestream noise on the shockwaveturbulent boundary layer interaction on a compression ramp is experimentally examined. The experiments are conducted in a supersonic low-disturbance tunnel under both low-level quiet and high-level noisyconventional freestream noise levels. A large-scale, low-frequency oscillation of the shock, that is comparable to that measured In previous conventional tunnel experiments is observed. The intermittent length of the interaction is comparable to that of previous experiments, but larger than that predicted in numerical simulations. Thus the freestream noise levels do not appear to be the source of the previously reported discrepancies between conventional tunnel experiments and simulations.

Subject Categories:

  • Aerodynamics
  • Statistics and Probability
  • Acoustics
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE