Determination of Transition Reynolds Number in the Transonic Mach Number Range
Abstract
The report presents the results of an investigation to determine the transition Reynolds number characteristics of the Propulsion Wind Tunnel (16T) and the Aerodynamic Wind Tunnel (4T) by measuring the location of boundary-layer transition on a 10-deg total-angle cone. Boundary-layer thickness on the test section walls and test section noise levels were measured in an attempt to determine their influence on boundary-layer transition location. Transition Reynolds number decreased with increasing Mach number in both tunnels with a higher rate of change in Tunnel 4T. Transition Reynolds number decreased with increasing unit Reynolds number for free-stream Mach numbers < or = 1.0 and alternated between decreasing and increasing with increasing unit Reynolds number for free-stream Mach numbers > 1.0. Test results indicated that boundary- layer transition on the cone surface was affected by test section wall angle, wall porosity, and the noise radiating from the test section walls. The boundary-layer acoustic level, as measured on the cone surface, was relatively unaffected by transition location for subsonic Mach numbers.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1970
- Accession Number
- AD0875995
Entities
People
- O. P. Credle
- W. E. Carleton
Organizations
- Arnold Engineering Development Complex