Optical Study of Supersonic Flow over a Rearward Facing Step
Abstract
The supersonic flow field over a rearward facing step was studied with a schlieren system. The effect of Mach number variation, step height variation, and total pressure variation on the expansion fan angle, lip shock angle, flow turning angle, reattachment point, and reattachment shock angle was determined. Schlieren photographs of the flow at Mach number 2.7 to 3.1, step heights of 1/4 to 3/4 in, and total pressures of 60 to 95 psia are presented. It was found that the relatively small changes in Mach number had the smallest effect on the flow field and that changing the step height had the greatest effect on the flow field. The flow turning angle was sensitive to all three variables.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1969
- Accession Number
- AD0853070
Entities
People
- Albert L. Waters
Organizations
- Air Force Institute of Technology