The Transverse Curvature Effect In Compressible Axially Symmetric Laminar Boundary Layer Flow Including The Effects Of Pressure Gradient
Download The Transverse Curvature Effect In Compressible Axially Symmetric Laminar Boundary Layer Flow Including The Effects Of Pressure Gradient PDF/ePub or read online books in Mobi eBooks. Click Download or Read Online button to get The Transverse Curvature Effect In Compressible Axially Symmetric Laminar Boundary Layer Flow Including The Effects Of Pressure Gradient book now. This website allows unlimited access to, at the time of writing, more than 1.5 million titles, including hundreds of thousands of titles in various foreign languages.
An Approximate Solution for Compressible Axisymmetric Laminar Boundary Layers Including the Effects of Transverse Curvature
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).
AFOSR.
Author: United States. Air Force. Office of Scientific Research
language: en
Publisher:
Release Date: 1950