Accession Number:

AD0683767

Title:

EXPERIMENTAL INVESTIGATION OF TURBULENT STEP-INDUCED BOUNDARY-LAYER SEPARATION AT MACH NUMBERS 2.5, 3, AND 4

Descriptive Note:

Final rept. 29 Apr-25 Sep 1968

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Personal Author(s):

Report Date:

1969-03-01

Pagination or Media Count:

39.0

Abstract:

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.

Subject Categories:

  • Aerodynamics
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE