论文信息 - Hypersonic mixing and combustion studies in the hypulse facility

Hypersonic mixing and combustion studies in the hypulse facility

Hydrogen-air mixing and combustion experiments at air velocities approaching 17,000 ft/s have been conducted in the HYPULSE facility expansion tube. The results proved to be repeatable and indicated increasing extent of reaction as the fuel equivalence ratio was increased from one to three. Comparisons were made with the results of a one-dimensional, finite-rate chemistry code and one-dimensional cycle codes that assume equilibrium chemistry. These comparisons indicate that the magnitudes and trends of the measured longitudinal pressure distributions are predicted by the one-dimensional codes provided the relevant physical phenomena are accounted for in the computations.

[1] John I. Erdos,et al. Use of an Expansion Tube to Examine Scramjet Combustion at Hypersonic Velocities , 1989 .

[2] R. J. Cresci,et al. Compressible Turbulent Boundary Layer with Pressure Gradient and Heat Transfer , 1966 .

[3] Griffin Y. Anderson. An outlook on hypersonic flight , 1987 .

[4] C. G. Miller,et al. Development and performance of the NASA Langley Research Center expansion tube/tunnel, a hypersonic-hypervelocity real-gas facility , 1984 .

[5] J. Erdos,et al. Calculated chemical and vibrational nonequilibrium effects in hypersonic nozzles , 1990 .

[6] P. A. Gnoffo,et al. Laminar heat-transfer distributions on biconics at incidence in hypersonic-hypervelocity flows , 1984 .

[7] John I. Erdos,et al. Mixing and combustion studies using discrete orifice injection at hypervelocity flight conditions , 1992 .

[8] Hassan Hassan,et al. Calculation of supersonic turbulent reacting coaxial jets , 1990 .

[9] W. R. Davies,et al. Heat transfer and transition to turbulence in the shock-induced boundary layer on a semi-infinite flat plate , 1969, Journal of Fluid Mechanics.