Approximate Turbulent Boundary Layer Development In Plane Compressible Flow Along Thermally Insulated Surfaces With Application To Supersonic Tunnel Contour Correction

Approximate Turbulent Boundary-layer Development in Plane Compressible Flow Along Thermally Insulated Surfaces with Application to Supersonic-tunnel Contour Correction

As an application of the method, the contour correction of supersonic nozzles for the effects of boundary-layer development is discussed from the requirement of continuity of mass flow and from the requirement of expansion- and shock-wave elimination.

Technical Note - National Advisory Committee for Aeronautics

Turbulent Flows and Heat Transfer

Volume V of the High Speed Aerodynamics and Jet Propulsion series. Topics include transition from laminar to turbulent flow; turbulent flow; statistical theories of turbulence; conduction of heat; convective heat transfer and friction in flow of liquids; convective heat transfer in gases; cooling by protective fluid films; physical basis of thermal radiation; and engineering calculations of radiant heat exchange. Originally published in 1959. The Princeton Legacy Library uses the latest print-on-demand technology to again make available previously out-of-print books from the distinguished backlist of Princeton University Press. These editions preserve the original texts of these important books while presenting them in durable paperback and hardcover editions. The goal of the Princeton Legacy Library is to vastly increase access to the rich scholarly heritage found in the thousands of books published by Princeton University Press since its founding in 1905.