Review of shock-induced supersonic combustion research and hypersonic applications

Abstract

This article focuses on research in supersonic and kinetics in high-speed flow between 1959-1968, and the application of the experimental results to hypersonic propulsion. The analysis discusses both advantages and problems for premixing the fuel and employing as an ignition method for a scramjet flying at a high Mach number. The experimental tests are discussed, including implications to the chemical kinetics of the high-velocity process. The conditions were confined to relatively low pressure, less than 2 atm (200 kPa). The results were considered to be mainly applicable for high-altitude scramjet flight, at low static pressure, where chemical reaction distances will be long. At these lower pressures, shock-induced combustion may be the predominant effect in a scramjet application, and it has some advantages that are discussed. The relation between and is also discussed. In addition, an attempt is made to resolve the conflicting experimental data published in the 1960s relating to standing detonation waves and combustion.