Libros sobre el tema "Scramjet combustor"
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Center, Langley Research, ed. HYPULSE combustor analysis. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1993.
Buscar texto completoCenter, Langley Research, ed. HYPULSE combustor analysis. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1993.
Buscar texto completoJacobs, P. A. Preliminary calibration of a generic scramjet combustor. Hampton, Va: Institute for Computer Applications in Science and Engineering, 1991.
Buscar texto completoJacobs, P. A. Flow establishment in a generic scramjet combustor. Hampton, Va: Institute for Computer Applications in Science and Engineering, 1990.
Buscar texto completoA, Jacobs Peter y Langley Research Center, eds. Flow establishment in a generic scramjet combustor. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1990.
Buscar texto completoA, Jacobs Peter y Langley Research Center, eds. Preliminary calibration of a generic scramjet combustor. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, [1991], 1991.
Buscar texto completoDash, Sanford M. Computational models for the analysis/design of hypersonic scramjet nozzles - Part 1: Combustor and nozzle models. New York: AIAA, 1986.
Buscar texto completo1934-, Hoffman Joe D. y 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.
Buscar texto completoT, Curran E. y Murthy S. N. B, eds. Scramjet propulsion. Reston, Va: American Institute of Aeronautics and Astronautics, 2000.
Buscar texto completoSchetz, Joseph A. Studies in scramjet flowfields. [S.l.]: American Institute of Aeronautics and Astronautics, 1987.
Buscar texto completoSislian, Jean Pascal. Inviscid on-design propulsive characteristics of hypersonic shock-induced combustion ramjets. North York, Ont: Institute for Aerospace Studies, University of Toronto, 1997.
Buscar texto completoMenon, S. Shock-wave-induced mixing enhancement in scramjet combustors. Washington, D. C: American Institute of Aeronautics and Astronautics, 1989.
Buscar texto completoUnited 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.
Buscar texto completoUnited 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.
Buscar texto completoO'Neill, Mary Kae L. Optimized scramjet integration on a waverider. Washington, D. C: American Institute of Aeronautics and Astronautics, 1991.
Buscar texto completoUnited States. National Aeronautics and Space Administration., ed. A first scramjet study. [Washington, DC: National Aeronautics and Space Administration, 1989.
Buscar texto completoIshiguro, Tomiko. Numerical calculation of scramjet inlet flow. Tokyo, Japan: National Aerospace Laboratory, 1992.
Buscar texto completoMorgan, R. G. Further shock tunnel studies of scramjet phenomena. St.Lucia, Australia: University of Queensland, 1986.
Buscar texto completoParent, Bernard. Computational study of fuel injection in a shcramjet inlet. [Downsview, Ont.]: University of Toronto, Institute for Aerospace Studies, 2002.
Buscar texto completoRogers, R. Clayton. Scramjet mixing establishment times for a pulse facility. Washington, D. C: American Institute of Aeronautics and Astronautics, 1991.
Buscar texto completoSilverstein, Calvin C. Heat pipe cooling for scramjet engines. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.
Buscar texto completoWittenberg, H. Some fundamentals on the performance of ramjets with subsonic and supersonic combustion. Rijswijk, The Netherlands: TNO Prins Maurits Laboratory, 2000.
Buscar texto completoRyerson Polytechnical Institute. Dept. of Mechanical Engineering. Investigations in the fluid dynamics of scramjet inlets. Toronto: Ryerson Polytechnical Institute ; University of Toronto, 1992.
Buscar texto completoThe scramjet engine: Processes and characteristics. Cambridge: Cambridge University Press, 2009.
Buscar texto completoJ, Stalker R., Paull Alvord y Langley Research Center, eds. Shock tunnel studies of scramjet phenomena 1994. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.
Buscar texto completoMorgan, R. G. Shock tunnel studies of scramjet phenomena 1994. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.
Buscar texto completoJ, Stalker R., Paull A y Langley Research Center, eds. Shock tunnel studies of scramjet phenomena 1995. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.
Buscar texto completoKumar, Ajay. A mixing augmentation technique for hypervelocity scramjets. Washington: American Institute of Aeronautics and Astronautics, 1987.
Buscar texto completoBrescianini, C. P. An investigation of a wall-injected scramjet using a shock tunnel. Washington: AIAA, 1992.
Buscar texto completoRiggins, David W. A comparative study of scramjet injection strategies for high Mach number flows. Washington, D. C: American Institute of Aeronautics and Astronautics, 1992.
Buscar texto completoSkyring, R. Experimental determination of hydrogen-air detonation pressure limit and scramjet application. Washington: American Institute of Aeronautics and Astronautics, 1996.
Buscar texto completoCenter, 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.
Buscar texto completoCenter, 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.
Buscar texto completoCenter, 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.
Buscar texto completoThomas, 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.
Buscar texto completoMinucci, 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.
Buscar texto completoBaysal, 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.
Buscar texto completoL, Semenov Vyacheslav, Hicks John W, Hugh L. Dryden Flight Research Center. y 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.
Buscar texto completoL, Semenov Vyacheslav, Hicks John W y 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.
Buscar texto completoSteffen, Christopher J. Fuel injector design optimization for an annular scramjet geometry. [Cleveland, Ohio: NASA Glenn Research Center, 2003.
Buscar texto completoDomel, 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.
Buscar texto completoBaysal, Oktay. Viscous computations of cold air/air flow around scramjet nozzle afterbody. Hampton, Va: Langley Research Center, 1991.
Buscar texto completoUnited 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.
Buscar texto completoUnited 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.
Buscar texto completoUnited 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.
Buscar texto completoEdwards, 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.
Buscar texto completoHolland, 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.
Buscar texto completoCenter, 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.
Buscar texto completoW, Kniskern Marc, Monta William J y 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.
Buscar texto completoHuebner, Lawrence D. Assessment of a flow-through balance for hypersonic wind tunnel models with scramjet exhaust flow simulation. Hampton, Va: Langley Research Center, 1993.
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