Heat-transfer and skin-friction parameters obtained from exact solutions to the laminar compressible boundary-layer equations for infinite cylinders in yaw are presented. The effects of transpiration cooling, Prandtl number, pressure gradient, wall temperature, and viscosity relation were investigated. It is shown that as the Mach number is increased for a given large yaw angle the effects of pressure gradient become larger and the quantity of coolant required to maintain a given wall temperature is also increased. The use of a linear viscosity-temperature relation gives approximately the same results as the Sutherland viscosity-temperature relation except for very high aerodynamic heating rates.
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.