Review of shock-induced supersonic combustion research and hypersonic applications

This article focuses on research in supersonic combustion and combustion 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 shock-induced combustion 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 combustion 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 shock-induced combustion and "detonation" 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 shock-induced combustion.

[1]  Raymond J. Stalker,et al.  Hydrogen combustion in a hypersonic airstream , 1992 .

[2]  R. Stalker,et al.  Technical Note— Hydrogen combustion in a hypersonic airstream , 1992, The Aeronautical Journal (1968).

[3]  F. Billig.  Research on supersonic combustion , 1992 .

[4]  Joseph W. Humphrey,et al.  Morphology of standing oblique detonation waves , 1991 .

[5]  M. Minucci,et al.  Experimental investigation of a 2-D scramjet inlet at Mach numbers of 8 to 18 and stagnation temperatures of 4,100K , 1991 .

[6]  C. J. Jachimowski,et al.  An analytical study of the hydrogen-air reaction mechanism with application to scramjet combustion , 1988 .

[7]  H. Adelman,et al.  Numerical simulations of an oblique detonation wave engine , 1988 .

[8]  Paul J. Waltrup,et al.  Liquid-fueled supersonic combustion ramjets - A research perspective , 1987 .

[9]  J. Hyde,et al.  Standing oblique detonation wave engine performance , 1987 .

[10]  Richard G. Morgan,et al.  Supersonic Hydrogen Combustion with a Short Thrust Nozzle , 1984 .

[11]  R. Strehlow,et al.  Experimental and analytical study of H sub 2-air reaction kinetics using a standing-wave normal shock. , 1969 .

[12]  C. E. Willbanks,et al.  Sensitivity of premixed compression-initiated supersonic combustion to small perturbations in inlet flow variables , 1968 .

[13]  R. Bauer,et al.  A hypersonic ramjet analysis with premixed fuel combustion , 1966 .

[14]  P. Rubins.  Comparison of chemical history and rates for the H sub 2 -air reaction. , 1966 .

[15]  J. Panesci.  Experimental standing-wave shock-induced combustion for determining reaction kinetic histories , 1965 .

[16]  P. Rubins,et al.  Shock-induced supersonic combustion in a constant-area duct , 1965 .

[17]  Antonio Ferri,et al.  Review of Problems in Application of Supersonic Combustion , 1964, The Journal of the Royal Aeronautical Society.

[18]  T. Cunningham.  Shock-induced combustion in a controlled area duct by means of oblique shocks , 1964 .

[19]  Harold Pergament,et al.  A THEORETICAL ANALYSIS OF NON-EQUILIBRIUM HYDROGEN-AIR REACTIONS IN FLOW SYSTEMS , 1963 .

[20]  R. P. Rhodes,et al.  Shock-induced combustion with oblique shocks- comparison of experiment and kinetic calculations , 1963 .

[21]  R. P. Rhodes,et al.  THE EFFECT OF HEAT RELEASE ON THE FLOW PARAMETERS IN SHOCK-INDUCED COMBUSTION , 1962 .

[22]  R. Gross,et al.  A Study of Supersonic Combustion , 1960 .

[23]  A. Shapiro.  The dynamics and thermodynamics of compressible fluid flow. , 1953 .

[24]  G. Y. Anderson.  AIA A-87-2074 An Outlook on Hypersonic Flight , 1987 .

[25]  J. Swithenbank.  Hypersonic air-breathing propulsion , 1967 .

[26]  R. Strehlow,et al.  Transverse wave structure in detonations , 1967 .

[27]  R. L. Phillips,et al.  An experimental and theoretical study of stationary gaseous detonation waves , 1961 .