Książki na temat „Scramjet combustor”

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

Center, Langley Research, red. 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, i Langley Research Center, red. Flow establishment in a generic scramjet combustor. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1990.

A, Jacobs Peter, i Langley Research Center, red. 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., i United States. National Aeronautics and Space Administration., red. 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., i Murthy S. N. B, red. 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., red. 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., red. 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., red. 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 i Langley Research Center, red. 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 i Langley Research Center, red. 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, red. 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, red. 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, red. 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. i United States. National Aeronautics and Space Administration., red. 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 i Hugh L. Dryden Flight Research Center., red. 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., red. 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., red. 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., red. 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, red. 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 i United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., red. 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.