EXPERIMENTAL INVESTIGATION OF TURBULENT STEP-INDUCED BOUNDARY-LAYER SEPARATION AT MACH NUMBERS 2.5, 3, AND 4
Final rept. 29 Apr-25 Sep 1968
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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An experimental investigation of turbulent separated boundary-layer flow was conducted using high forward-facing steps with side plates mounted on a flat plate at zero angle of attack. The tests were made at Mach numbers of 2. 5, 3.0, and 4.0 for Reynolds numbers, based on the boundary-layer total thickness at the separation location, from 100,000 to 150,000. The effects of Mach number, step height and span, end plates, and step-face fairings were investigated. Data are presented graphically and in tabulations and include model surface pressures on the flat plate and on the face and top of selected steps, boundary-layer Mach number profiles, and selected oil dot photographs.
- Fluid Mechanics