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An Approximate Solution for Compressible Axisymmetric Laminar Boundary Layers Including the Effects of Transverse Curvature
Jay M. Solomon
Bernard S. Loeb
出版
United States Naval Ordnance Laboratory
, 1967
URL
http://books.google.com.hk/books?id=ScQr27gNVuEC&hl=&source=gbs_api
EBook
FULL_PUBLIC_DOMAIN
註釋
An approximate momentum integral solution for the compressible axisymmetrix laminar boundary layer when transverse curvature effects are important is presented. Both finite and infinite inviscid Mach numbers are considered. Detailed comparisons with exact asymptotic solutions are given. The method is found, in many instances, to agree to leading order with the exact solutions as the transverse curvature becomes very large--a property that none of the existing approximate solutions for compressible flow possess. Some example calculations for a cone in supersonic and hypersonic flow are presented. Also, the method is applied to the hypersonic self-induced pressure problem for a cone. (Author).
