Shock wave-boundary-layer interaction (SBLI) is a fundamental phenomenon in gas dynamics that is observed in many practical situations, ranging from transonic aircraft wings to hypersonic vehicles and engines. SBLIs have the potential to pose serious problems in a flowfield; hence they often prove to be a critical - or even design limiting - issue for many aerospace applications. This is the first book devoted solely to a comprehensive, state-of-the-art explanation of this phenomenon. It includes a description of the basic fluid mechanics of SBLIs plus contributions from leading international experts who share their insight into their physics and the impact they have in practical flow situations. This book is for practitioners and graduate students in aerodynamics who wish to familiarize themselves with all aspects of SBLI flows. It is a valuable resource for specialists because it compiles experimental, computational and theoretical knowledge in one place.

Part 2. : This investigation was undertaken with two primary objectives. The first objective was to see if chemical reaction rates can be determined to about the same accuracy behind combustion driven shock waves as that previously attained behind shock waves generated by high pressure hydrogen or helium. The second was to obtain chemical rate data for nitrogen.

Six experiments were conducted to measure the transient character of the airloads induced by the interaction of blast generated shock waves on a moving airfoil. The tests were conducted on a rigid (airloads) model of swept planform, similar in type to a B47/B52 aircraft. Airfoil motion was simulated by the shock tube which produced a jet flow of Mach 0.7. Shock waves were generated by explosive charges which were varied in sized and proximity to obtain airloads on the wing that changed both the angle of attack and blast duration through a range from small to large. The wing specimens were heavily instrumented with pressure transducers to measure the time history of the variation in the airloads. Response of the wing to the airloads was measured by strain gages and accelerometers. Pressure instrumentation was also used to measure the character of the blast environment. Blast parameters were varied to obtain induced airloads with nominal values for the angle of attack of 8, 20 and 30 degrees. At each of these angles of attack, an experiment was run with a short and long duration shock wave to study the effect of decay rate on the airloads. (Author).