Boundary-Layer Transition on a Cooled 20 deg. Cone at Mach Numbers of 1.5 and 2.0
Abstract
The laminar boundary layer on a cooled 200 cone was investigated at Mach numbers of l.% and 2.0 to determine the variation of the posftion of transition with surface temperature for both constant surface temperatures and surface temperatures that increased toward the rear of the cone. Small circumferential grooves at the tip were necessary to cause transition near the center of the cone at the condition of zero heat transfer. The results obtained at all test conditions indicate that removing heat from the boundary layer delays transition from laminar to turbulent flow. The theory of laminar boundary-layer stability developed by Lees in NACA TN 1360, l9%%, is in qualitative agreement with this result. At the test conditions of the present investigation, the increase in the extent of the laminar bound- ary layer was found to be a linear function of the rate of heat transfer.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1950
- Accession Number
- ADA380428
Entities
People
- Richard Scherrer
Organizations
- National Aeronautics and Space Administration