Books on the topic 'Scramjet combustor'

Center, Langley Research, ed. HYPULSE combustor analysis. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1993.

Center, Langley Research, ed. HYPULSE combustor analysis. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1993.

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

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

A, Jacobs Peter, and Langley Research Center, eds. Flow establishment in a generic scramjet combustor. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1990.

A, Jacobs Peter, and Langley Research Center, eds. Preliminary calibration of a generic scramjet combustor. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, [1991], 1991.

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

1934-, Hoffman Joe D., and United States. National Aeronautics and Space Administration., eds. Hypervelocity scramjet combustor-nozzle, analysis and design: Final report for NASA grant NAG-1-854 for the period 15 February 1988 to 31 December 1991. [Washington, DC: National Aeronautics and Space Administration, 1992.

T, Curran E., and Murthy S. N. B, eds. Scramjet propulsion. Reston, Va: American Institute of Aeronautics and Astronautics, 2000.

Schetz, Joseph A. Studies in scramjet flowfields. [S.l.]: American Institute of Aeronautics and Astronautics, 1987.

Sislian, Jean Pascal. Inviscid on-design propulsive characteristics of hypersonic shock-induced combustion ramjets. North York, Ont: Institute for Aerospace Studies, University of Toronto, 1997.

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

United States. National Aeronautics and Space Administration., ed. An extended supersonic combustion model for the dynamic analysis of hypersonic vehicles. [Washington, DC]: National Aeronautics and Space Administration, 1993.

United States. National Aeronautics and Space Administration., ed. An extended supersonic combustion model for the dynamic analysis of hypersonic vehicles. [Washington, DC]: National Aeronautics and Space Administration, 1993.

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

United States. National Aeronautics and Space Administration., ed. A first scramjet study. [Washington, DC: National Aeronautics and Space Administration, 1989.

Ishiguro, Tomiko. Numerical calculation of scramjet inlet flow. Tokyo, Japan: National Aerospace Laboratory, 1992.

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

Parent, Bernard. Computational study of fuel injection in a shcramjet inlet. [Downsview, Ont.]: University of Toronto, Institute for Aerospace Studies, 2002.

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

Silverstein, Calvin C. Heat pipe cooling for scramjet engines. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

Wittenberg, H. Some fundamentals on the performance of ramjets with subsonic and supersonic combustion. Rijswijk, The Netherlands: TNO Prins Maurits Laboratory, 2000.

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

The scramjet engine: Processes and characteristics. Cambridge: Cambridge University Press, 2009.

J, Stalker R., Paull Alvord, and Langley Research Center, eds. Shock tunnel studies of scramjet phenomena 1994. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

Morgan, R. G. Shock tunnel studies of scramjet phenomena 1994. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

J, Stalker R., Paull A, and Langley Research Center, eds. Shock tunnel studies of scramjet phenomena 1995. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

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

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

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.

Skyring, R. Experimental determination of hydrogen-air detonation pressure limit and scramjet application. Washington: American Institute of Aeronautics and Astronautics, 1996.

Center, Langley Research, ed. A two-line absorption instrument for scramjet temperature and water vapor concentration measurement in HYPULSE. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1998.

Center, Langley Research, ed. A two-line absorption instrument for scramjet temperature and water vapor concentration measurement in HYPULSE. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1998.

Center, Langley Research, ed. A two-line absorption instrument for scramjet temperature and water vapor concentration measurement in HYPULSE. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1998.

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.

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.

Baysal, Oktay. Viscous computations of cold air/airflow around scramjet nozzle afterbody. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 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.

Steffen, Christopher J. Fuel injector design optimization for an annular scramjet geometry. [Cleveland, Ohio: NASA Glenn Research Center, 2003.

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.

Baysal, Oktay. Viscous computations of cold air/air flow around scramjet nozzle afterbody. Hampton, Va: Langley Research Center, 1991.

United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., ed. An analytical study of the hydrogen-air reaction mechanism with application to scramjet combustion. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988.

United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., ed. An analytical study of the hydrogen-air reaction mechanism with application to scramjet combustion. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988.

United States. National Aeronautics and Space Administration., ed. Shock tunnel studies of scramjet phenomena: Final technical report, NAGW-674. [Washington, DC: National Aeronautics and Space Administration, 1996.

Edwards, Thomas A. The effect of exhaust plume/afterbody interaction on installed scramjet performance. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 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.

Center, Langley Research, ed. Internal aerodynamics of a generic three-dimensional scramjet inlet at Mach 10. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

W, Kniskern Marc, Monta William J, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., eds. Assessment of a flow-through balance for hypersonic wind tunnel models with scramjet exhaust flow simulation. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

Huebner, Lawrence D. Assessment of a flow-through balance for hypersonic wind tunnel models with scramjet exhaust flow simulation. Hampton, Va: Langley Research Center, 1993.