Transition, Minimum Critical, Minimum Transition, and Roughness Reynolds Numbers for Seven Blunt Bodies of Revolution in Flight between Mach Numbers of 1.72 and 15.1
Abstract
Results of the stability theory for laminar flow were compared with transition locations determined from heat-transfer distributions obtained by previous investigators for 7 blunt bodies of revolution in supersonic flight. The comparison shows that when transition occurred it took place even though the boundary layer was calculated to be very stable with respect to small disturbances for the entire region between the stagnation point and the transition location. In every case transition occurred at a larger boundary- layer Reynolds number than the estimated minimum Reynolds number for transition. The boundary-layer transition Reynolds number was influenced much more strongly by the maximum roughness Reynolds number ahead of the transition point than by the local wall temperature ratio at the transition point.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 16, 1962
- Accession Number
- AD0333238
Entities
People
- Neal Tetervin
Organizations
- Naval Ordnance Laboratory