This report covers analytic and experimental gasdynamic studies relevant to stability issues of the scramjet supersonic combustion chamber. Its intended purpose was to search for small amplitude very short time scale precurser signals which eventually grew into combustor flow instability, but at a much longer time scale than the signal itself, and consequently offer possibility of control before amplitudes got out of hand. The experiments were done in a basic 2.5 Mach number stream with an artificially thickened boundary layer corresponding to the ingested ramp boundary layer that occurs in the usual installation . A disturbance produced downstream by a small shock tube discharging normally to the gas flow successfully disgorged the shock structure; time resolved pressure and Schlieren image records were obtained. Because upstream signal propagation through the subsonic boundary layer of a supersonic flow is seen as an important issue in the phenomenon under investigation, a rudamentary analytic model was developed. It consists of an acoustically compact element, in which mixing and heat release may occur, with long constant area ducts upstream and downstream of this element. It employs a two stream one dimensional approximation, the main supersonic stream and a subsonic second stream representing the thick boundary layer. Conditions under which interfacial disturbances may be propagated upstream are examined through several examples.

This book describes the unsteady phenomena needed to understand supersonic combustion. Following an initial chapter that introduces readers to the basic concepts in and classical studies on unsteady supersonic combustion, the book highlights recent studies on unsteady phenomena, which offer insights on e.g. interactions between acoustic waves and flames, flow dominating instability, ignition instability, flame flashback, and near-blowout-limit combustion. In turn, the book discusses in detail the fundamental mechanisms of these phenomena, and puts forward practical suggestions for future scramjet design.

The establishment of a quasi-steady flow in a generic scramjet combustor was studied for the case of a time varying inflow to the combustor. Such transient flow is characteristic of the reflected shock tunnel and expansion tube test facilities. Several numerical simulations of hypervelocity flow through a straight duct combustor with either a side wall step fuel injector or a centrally located strut injector are presented. Comparisons were made between impulsively started but otherwise constant flow conditions (typical of the expansion tube or tailored operations of the reflected shock tunnel) and the relaxing flow produced by the 'undertailored' operations of the reflected shock tunnel. Generally the inviscid flow features, such as the shock pattern and pressure distribution, were unaffected by the time varying inlet conditions and approached steady state in approx. the times indicated by experimental correlations. However, viscous features, such as heat transfer and skin friction, were altered by the relaxing inlet flow conditions. Jacobs, P. A. and Rogers, R. C. and Weidner, E. H. and Bittner, R. D. Langley Research Center NAS1-18605...

An almost entirely self-contained engineering textbook primarily for use in undergraduate and graduate courses in airbreathing propulsion. It provides a broad and basic introduction to the elements needed to work in the field as it develops and grows. Homework problems are provided for almost every individual subject. An extensive array of PC-based user-friendly computer programs is provided in order to facilitate repetitious and/or complex calculations. Annotation copyright by Book News, Inc., Portland, OR