Analysis of turbulent skin friction in thick axisymmetric boundary layers

Document Type

Article

Date of Original Version

1-1-1973

Abstract

An analysis is developed for turbulent flow over arbitrary bodies of revolution. The theory leads to a single, first-order, ordinary differential equation for the skin-friction coefficient. Arbitrary distributions of Mach number, pressure gradient, and body shape are allowable. Transverse curvature is accounted for and the boundary layer may be arbitrarily thick. Application is made to supersonic flow past long cylinders, thin cones, and a pointed body of revolution. Agreement with experiment is good in all cases. Boundary-layer shape factors are avoided entirely in this theory, and integral thicknesses are eliminated from the final differential equation. © 1973 American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

Publication Title, e.g., Journal

AIAA Journal

Volume

11

Issue

6

Link to Full Text

Share

COinS