THE TURBULENT NEAR-WAKE OF AN AXISYMMETRIC BODY AT SUBSONIC SPEEDS.
Abstract
The subsonic near wake of a blunt based, right circular cylinder immersed in a uniform subsonic flow was studied. A special open circuit steady flow wind tunnel with a closed jet test section was utilized for the experimental program. A model support system contained entirely within the tunnel settling chamber eliminated the usual downstream support stings. The boundary layer prior to the base was turbulent and the test section Reynolds number was 100,000/ft. Detailed pressure measurements were made in all regions of the wake as well as in the approaching flow and on the body surfaces. The rear stagnation point was located using the intersection of the centerline static and total pressure distributions. Complete shear layer and recirculation region velocity profiles were obtained. The flow was found to be quite insensitive to changes in free stream velocity with respect to the base pressure coefficient and the location of the rear stagnation point. The influence of the separation corner was found to extend approximately two base diameters upstream on the body. The dividing streamline, found by graphical integration of the shear layer and recirculation region velocity profiles, was nearly elliptical in shape. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1970
- Accession Number
- AD0705687
Entities
People
- Christian E. G. Przirembel
- Donald P. Mcerlean
Organizations
- Rutgers University Department of Mechanical and Aerospace Engineering