COMPRESSIBLE TURBULENT BOUNDARY LAYER WITH ARBITRARY PRESSURE GRADIENT AND HEAT TRANSFER.
Abstract
The compressible turbulent boundary layer is expressed in terms of the momentum integral and moment of momentum integral equations for arbitrary pressure gradient. Upon simplification of this equation set with a Mager type transformation, the two coupled differential equations are solved simulataneously to provide boundary layer momentum thickness, displacement thickness, skin friction coefficient and related quantities as a function of the body surface coordinate. The analysis includes surface heat-transfer effects. Results of the analysis are presented for adiabatic, non-adiabatic, twodimensional and axisymmetric flow fields in a Mach number range between 2 and 8. Flows with adverse pressure gradients are also examined. The present analysis is compared with available experimental and theoretical results. The analysis is found to yield satisfactory results for flows with and without heat transfer. In addition, for flows in the presence of large adverse pressure gradients in which the boundary layer is known to be well-behaved, spurious separation is not indicated; instead, rather good agreement with available experimental data is observed. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1965
- Accession Number
- AD0615608
Entities
People
- Philip K. Sasman
- Robert J. Cresci
Organizations
- New York University Tandon School of Engineering