The aerodynamic characteristics of a lifting body in a nonequilibrium stream are studied for a simple case, namely, the case of a nonequilibrium oncoming stream past a thin airfoil at a small angle of attack. Analytical solutions are obtained by the use of nonequilibrium linearized theory. Results show that when the relaxation length on the indward side of the airfoil is not appreciably different from that on the leeward side, a nonequilibrium ambient condition will normally induce a higher pressure and lower drag, but will not affect the lift, pitching moment, and the center of pressure. The local nonequilibrium condition behind the leading-edge shock, on the other hand, will affect all of the aerodynamic characteristics in general. When the relaxation length on the windward side is significantly different from that on the leeward side, on the other hand, the nonequilibrium ambient condition will also affect the lift, pitching moment, and the center of the pressure. In general, the higher the suction on the leeward side gives higher lift and larger pitching moment because the condition on the leeward side is closer to frozen.

Progress in Aeronautical Sciences, Volume 9 presents the vibrational characteristics of certain aircraft. This book supplements the comprehensive account of matrix methods of structural analysis. Organized into five chapters, this volume begins with an overview of the different schemes of the numerical method of characteristics for calculating three-dimensional steady supersonic gas flow about bodies moving at incidence. This text then examines the flow of a perfect gas and provides the generalization for the case of equilibrium and non-equilibrium flow of real gas. Other chapters consider the various aspects of the aerodynamic design of aircraft and discuss the application of modern computer methods to fluid mechanics. This book discusses as well the prospects for further development of the existing types and for the establishment of the as yet hypothetical types of aircraft. The final chapter shows how the evolution of the aerodynamic shape leads to a complete spectrum of major types of aircraft. This book is a valuable resource for engineers.

The High Temperature Aspects of Hypersonic Flow is a record of the proceedings of the AGARD-NATO Specialists' Meeting, held at the Technical Centre for Experimental Aerodynamics, Rhode-Saint-Genese, Belgium in April 1962. The book contains the papers presented during the meeting that tackled a broad range of topics in the aspects of hypersonic flow. The subjects covered during the meeting include pressure measurements, interference effects, the use of wind tunnels in aircraft development testing, high temperature gas characteristics, boundary layer research, stability and control and the use of rocket vehicles in flight research. Aerospace engineers and aeronautical engineers will find the book invaluable.