Książki na temat „Scramjet engine”

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

Burkardt, Leo A. RAMSCRAM: A flexible ramjet/scramjet engine simulation program. [Washington, DC]: National Aeronautics and Space Administration, 1990.

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.

Center, Langley Research, red. Mach 10 experimental database of a three-dimensional scramjet inlet flow field. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

Holland, Scott D. Mach 10 experimental database of a three-dimensional scramjet inlet flow field. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

Center, Langley Research, red. Wind-tunnel blockage and actuation systems test of a two-dimensional scramjet inlet unstart model at Mach 6. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1994.

Center, Langley Research, red. Wind-tunnel blockage and actuation systems test of a two-dimensional scramjet inlet unstart model at Mach 6. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1994.

Center, Langley Research, red. Wind-tunnel blockage and actuation systems test of a two-dimensional scramjet inlet unstart model at Mach 6. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1994.

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.

United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, red. Heat pipe cooling for scramjet engines. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

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

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.

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.

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.

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

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.

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.

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

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.

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

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

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

Scotti, Stephen J. Active cooling design for scramjet engines using optimization methods. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1988.

J, Martin Carl, Lucas Stephen H i Langley Research Center, red. Active cooling design for scramjet engines using optimization methods. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1988.

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.

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

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

United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., red. Computational parametric study of sidewall-compression scramjet inlet performance at mach 10. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

Timnat, Y. M. Advanced airbreathing propulsion. Malabar, Fla: Krieger Pub. Co., 1996.

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

Mekkes, Gregory L. Fuel plume image mixing analysis formulation with proper treatment of non-constant velocity flowfields. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 2000.

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.

Hartley, T. T. A hierarchy for modeling high speed propulsion systems. [Washington, DC: National Aeronautics and Space Administration, 1991.

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

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

Heiser, William H. Hypersonic airbreathing propulsion: With Daniel H. Daley and Unmeel B. Mehta. Washington, D.C: American Institute of Aeronautics and Astronautics, 1994.

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.

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.