Accession Number:

ADA014246

Title:

Experiments on the Interaction with a Turbulent Boundary Layer of a Skewed Shock Wave of Variable Strength at Mach 2.5.

Descriptive Note:

Final rept. Feb 73-May 75,

Corporate Author:

AEROSPACE RESEARCH LABS WRIGHT-PATTERSON AFB OHIO

Report Date:

1975-06-01

Pagination or Media Count:

26.0

Abstract:

This report covers an experimental study of the interaction of a skewed shock wave of variable strength with a turbulent boundary layer at a working Mach number of 2.5. The skewed shock wave was generated by a vertical wedge whose angle was varied in increments of 1 degree or less between 6 and 18 degrees in order to cover the spectrum of interaction from below incipient to widespread separation. Measurements include pressure distributions and oil flow photographs. The incipient separation angle was found to be between 712 and 8 degrees. For large wedge angles there is the appearance in the oil flow photographs of an inflection within the separated region, suggesting the possible approach to a secondary separation. The extent of separation is relatively small for angles up to 10 degrees, but grows more rapidly for larger angles. Author

Subject Categories:

  • Aircraft
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE