Books on the topic 'Supersonic combustion'

Sun, Mingbo, Hongbo Wang, Zun Cai, and Jiajian Zhu. Unsteady Supersonic Combustion. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-3595-6.

Timnat, Y. M. Diagnostics in supersonic combustion. New York: AIAA, 1987.

Gutmark, E. Noncircular jet dynamics in supersonic combustion. New York: American Institute of Aeronautics and Astronautics, 1987.

Don, Hoying, and Universities Space Research Association, eds. Supersonic combustion engine testbed: Heat lightning. Houston, Tex: Universities Space Research Association, 1990.

Northam, G. Burton. Supersonic combustion ramjet research at Langley. New York: AIAA, 1986.

McDaniel, James C. A laser-induced-fluorescence visualization study of transverse, sonic fuel injection in a nonreacting supersonic combustor. New York: AIAA, 1986.

Marble, Frank E. Progress toward shock enhancement of supersonic combustion processes. New York: AIAA, 1987.

Yip, T. Gary. Ignition delay and characteristic reaction length in shock induced supersonic combustion. New York: AIAA, 1989.

Rubins, Philip M. A review of supersonic combustion research at AEDC with hypersonic applications. Washington, D. C: American Institute of Aeronautics and Astronautics, 1993.

Drummond, J. Philip. Mixing enhancement in a supersonic combustor. Washington, D. C: American Institute of Aeronautics and Astronautics, 1989.

Champion, M., and B. Deshaies, eds. IUTAM Symposium on Combustion in Supersonic Flows. Dordrecht: Springer Netherlands, 1997. http://dx.doi.org/10.1007/978-94-011-5432-1.

Northam, G. Burton. Evaluation of parallel injector configurations for supersonic combustion. Washington, D. C: American Institute of Aeronautics and Astronautics, 1989.

A, Baurie R., Hassan H. A, and United States. National Aeronautics and Space Administration., eds. A k-[omega]-multivariate beta pdf for supersonic combustion. [Washington, DC: National Aeronautics and Space Administration, 1992.

A, Baurie R., Hassan H. A, and United States. National Aeronautics and Space Administration., eds. A k-[omega]-multivariate beta pdf for supersonic combustion. [Washington, DC: National Aeronautics and Space Administration, 1992.

Schetz, Joseph A. Analysis of external burning on inclined surfaces in supersonic flow. Washington, D. C: American Institute of Aeronautics and Astronautics, 1991.

Domel, N. D. A two-dimensional numerical simulation of shock-enhanced mixing in a rectangular scramjet flowfield with parallel hydrogen injection. Washington, D. C: American Institute of Aeronautics and Astronautics, 1991.

Carrier, G. Laser-initiated conical detonation wave for supersonic combustion. New York: AIAA, 1991.

Jacobs, P. A. Flow establishment in a generic scramjet combustor. Hampton, Va: Institute for Computer Applications in Science and Engineering, 1990.

Dash, Sanford M. Computational models for the analysis/design of hypersonic scramjet nozzles - Part 1: Combustor and nozzle models. New York: AIAA, 1986.

Jacobs, P. A. Preliminary calibration of a generic scramjet combustor. Hampton, Va: Institute for Computer Applications in Science and Engineering, 1991.

Rogers, R. Clayton. Scramjet mixing establishment times for a pulse facility. Washington, D. C: American Institute of Aeronautics and Astronautics, 1991.

Eklund, Dean R. A numerical and experimental study of a supersonic combustor employing swept ramp fuel injectors. Washington, D. C: American Institute of Aeronautics and Astronautics, 1994.

Planche, O. H. Heat release effects on mixing in supersonic reacting free shear-layers. Washington, D. C: American Institute of Aeronautics and Astronautics, 1992.

Bowman, C. T. Annual technical report on turbulent reacting flows and supersonic combustion. Stanford, Calif: Stanford University, High Temperature Gasdynamics Laboratory, 1991.

Morgan, R. G. Further shock tunnel studies of scramjet phenomena. St.Lucia, Australia: University of Queensland, 1986.

Riggins, David W. A comparative study of scramjet injection strategies for high Mach number flows. Washington, D. C: American Institute of Aeronautics and Astronautics, 1992.

Minucci, Marco A. S. Investigation of a 2-D scramjet inlet, M =8-25 and T =800-4, 100K. Washington, D. C: American Institute of Aeronautics and Astronautics, 1991.

Brescianini, C. P. An investigation of a wall-injected scramjet using a shock tunnel. Washington: AIAA, 1992.

Thomas, Scott R. Scramjet testing from Mach 4 to 20: Present capability and needs for the nineties. Washington, D. C: American Institute of Aeronautics and Astronautics, 1990.

Bement, David A. Measured operating characteristics of a rectangular combustor/inlet isolator. Washington: American Institute of Aeronautics and Astronautics, 1990.

Yang, Joseph. An analytical and computational investigation of shock-induced vortical flows with applications to supersonic combustion. Pasadena, Calif: California Institute of Technology, 1991.

Nguyen, Hung Lee. Analytical combustion/emissions research related to the NASA high-speed research program. [Washington, DC]: National Aeronautics and Space Administration, 1991.

Riggins, David W. Analysis of losses in supersonic mixing and reacting flows. Washington, D. C: American Institute of Aeronautics and Astronautics, 1991.

Walton, James T. Aerothermodynamic flow phenomena of the airframe-integrated supersonic combustion ramjet. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992.

Cambier, Jean-Luc. Mixing and combustion enhancement from unsteady shock-fuel layer interactions. Washington, D. C: American Institute of Aeronautics and Astronautics, 1994.

Riggins, David W. A numerical study of mixing enhancement in a supersonic combustor. Washington, D. C: American Institute of Aeronautics and Astronautics, 1990.

Rizkalla, Oussama F. Calculated chemical and vibrational nonequilibrium effects in NASP-type nozzles. New York: AIAA, 1988.

Holland, Scott D. Schlieren photographs and internal pressure distributions for three-dimensional sidewall-compression scramjet inlets at a Mach number of 6 in CF4. Hampton, Va: Langley Research Center, 1993.

Drummond, J. Philip. Mixing enhancement of reacting parallel fuel jets in a supersonic combustor. Washington, D. C: American Institute of Aeronautics and Astronautics, 1991.

Waitz, Ian A. Vorticity generation by contoured wall injectors. Washington, D. C: American Institute of Aeronautics and Astronautics, 1992.

Carpenter, Mark H. Three-dimensional computations of cross-flow injection and combustion in a supersonic flow. Washington, D. C: American Institute of Aeronautics and Astronautics, 1989.

Kumar, Ajay. A mixing augmentation technique for hypervelocity scramjets. Washington: American Institute of Aeronautics and Astronautics, 1987.

Ryerson Polytechnical Institute. Dept. of Mechanical Engineering. Investigations in the fluid dynamics of scramjet inlets. Toronto: Ryerson Polytechnical Institute ; University of Toronto, 1992.

Anderson, Griffin Y. An outlook on hypersonic flight. New York: AIAA, 1987.

Menon, S. Shock-wave-induced mixing enhancement in scramjet combustors. Washington, D. C: American Institute of Aeronautics and Astronautics, 1989.

O'Neill, Mary Kae L. Optimized scramjet integration on a waverider. Washington, D. C: American Institute of Aeronautics and Astronautics, 1991.

L, Semenov Vyacheslav, Hicks John W, Hugh L. Dryden Flight Research Center., and United States. National Aeronautics and Space Administration., eds. Recent flight test results of the joint CIAM-NASA Mach 6.5 Scramjet Flight Program. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1998.

L, Semenov Vyacheslav, Hicks John W, and Hugh L. Dryden Flight Research Center., eds. Recent flight test results of the joint CIAM-NASA Mach 6.5 Scramjet Flight Program. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1998.

T, Schwab S., Harlowe W. W, and Langley Research Center, eds. Ignition delays, heats of combustion, and reaction rates of aluminum alkyl derivatives used as ignition and combustion enhancers for supersonic combustion. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1992.

Brabbs, Theodore A. Fuel-rich catalytic combustion of a high density fuel. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.