Recent government and commercial efforts to develop orbital and suborbital passenger and transport aircraft have resulted in a burgeoning of new research. The articles in this book, translated from Russian, were contributed by the world's leading authorities on supersonic and hypersonic flows and heat transfer. This superb book addresses the physics and engineering aspects of ultra high-speed aerodynamic problems. Thorough coverage is given to an array of specific problem-solving equations. Super- and Hypersonic Aerodynamics and Heat Transfer will be essential reading for all aeronautical engineers, mechanical engineers, mathematicians, and physicists involved in this exciting field of research.

Heat-transfer rates were measured on large-angle conical bodies with large half-angles between 50 degrees and 90 degrees, at angles of attack from 0 degrees. The results at 0 degree angle of attack were predicted with Lees' similarity theory, using calculated flow properties at the boundary-layer edge. The calculated flow properties were obtained from Newtonian theory for the 50 degree cone and from a one- or two-strip solution using the method of integral relations for other cones. At 0 degree angle of attack, an increase in cone angle resulted in a decrease in the heating rate over much of the body. However, high heating rates occurred at the shoulder of the both the half-angle = 80 degree and half-angle =90 degree shapes because of local pressure gradients. On the windward side of the cones, the heating rate increased with angle of attack.