Livres sur le sujet « Scramjet combustor »
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Center, Langley Research, dir. HYPULSE combustor analysis. Hampton, Va : National Aeronautics and Space Administration, Langley Research Center, 1993.
Trouver le texte intégralCenter, Langley Research, dir. HYPULSE combustor analysis. Hampton, Va : National Aeronautics and Space Administration, Langley Research Center, 1993.
Trouver le texte intégralJacobs, P. A. Preliminary calibration of a generic scramjet combustor. Hampton, Va : Institute for Computer Applications in Science and Engineering, 1991.
Trouver le texte intégralJacobs, P. A. Flow establishment in a generic scramjet combustor. Hampton, Va : Institute for Computer Applications in Science and Engineering, 1990.
Trouver le texte intégralA, Jacobs Peter, et Langley Research Center, dir. Flow establishment in a generic scramjet combustor. Hampton, Va : National Aeronautics and Space Administration, Langley Research Center, 1990.
Trouver le texte intégralA, Jacobs Peter, et Langley Research Center, dir. Preliminary calibration of a generic scramjet combustor. Hampton, Va : National Aeronautics and Space Administration, Langley Research Center, [1991], 1991.
Trouver le texte intégralDash, Sanford M. Computational models for the analysis/design of hypersonic scramjet nozzles - Part 1 : Combustor and nozzle models. New York : AIAA, 1986.
Trouver le texte intégral1934-, Hoffman Joe D., et United States. National Aeronautics and Space Administration., dir. 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.
Trouver le texte intégralT, Curran E., et Murthy S. N. B, dir. Scramjet propulsion. Reston, Va : American Institute of Aeronautics and Astronautics, 2000.
Trouver le texte intégralSchetz, Joseph A. Studies in scramjet flowfields. [S.l.] : American Institute of Aeronautics and Astronautics, 1987.
Trouver le texte intégralSislian, Jean Pascal. Inviscid on-design propulsive characteristics of hypersonic shock-induced combustion ramjets. North York, Ont : Institute for Aerospace Studies, University of Toronto, 1997.
Trouver le texte intégralMenon, S. Shock-wave-induced mixing enhancement in scramjet combustors. Washington, D. C : American Institute of Aeronautics and Astronautics, 1989.
Trouver le texte intégralUnited States. National Aeronautics and Space Administration., dir. An extended supersonic combustion model for the dynamic analysis of hypersonic vehicles. [Washington, DC] : National Aeronautics and Space Administration, 1993.
Trouver le texte intégralUnited States. National Aeronautics and Space Administration., dir. An extended supersonic combustion model for the dynamic analysis of hypersonic vehicles. [Washington, DC] : National Aeronautics and Space Administration, 1993.
Trouver le texte intégralO'Neill, Mary Kae L. Optimized scramjet integration on a waverider. Washington, D. C : American Institute of Aeronautics and Astronautics, 1991.
Trouver le texte intégralUnited States. National Aeronautics and Space Administration., dir. A first scramjet study. [Washington, DC : National Aeronautics and Space Administration, 1989.
Trouver le texte intégralIshiguro, Tomiko. Numerical calculation of scramjet inlet flow. Tokyo, Japan : National Aerospace Laboratory, 1992.
Trouver le texte intégralMorgan, R. G. Further shock tunnel studies of scramjet phenomena. St.Lucia, Australia : University of Queensland, 1986.
Trouver le texte intégralParent, Bernard. Computational study of fuel injection in a shcramjet inlet. [Downsview, Ont.] : University of Toronto, Institute for Aerospace Studies, 2002.
Trouver le texte intégralRogers, R. Clayton. Scramjet mixing establishment times for a pulse facility. Washington, D. C : American Institute of Aeronautics and Astronautics, 1991.
Trouver le texte intégralSilverstein, Calvin C. Heat pipe cooling for scramjet engines. [Washington, DC] : National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.
Trouver le texte intégralWittenberg, H. Some fundamentals on the performance of ramjets with subsonic and supersonic combustion. Rijswijk, The Netherlands : TNO Prins Maurits Laboratory, 2000.
Trouver le texte intégralRyerson Polytechnical Institute. Dept. of Mechanical Engineering. Investigations in the fluid dynamics of scramjet inlets. Toronto : Ryerson Polytechnical Institute ; University of Toronto, 1992.
Trouver le texte intégralThe scramjet engine : Processes and characteristics. Cambridge : Cambridge University Press, 2009.
Trouver le texte intégralJ, Stalker R., Paull Alvord et Langley Research Center, dir. Shock tunnel studies of scramjet phenomena 1994. Hampton, Va : National Aeronautics and Space Administration, Langley Research Center, 1997.
Trouver le texte intégralMorgan, R. G. Shock tunnel studies of scramjet phenomena 1994. Hampton, Va : National Aeronautics and Space Administration, Langley Research Center, 1997.
Trouver le texte intégralJ, Stalker R., Paull A et Langley Research Center, dir. Shock tunnel studies of scramjet phenomena 1995. Hampton, Va : National Aeronautics and Space Administration, Langley Research Center, 1997.
Trouver le texte intégralKumar, Ajay. A mixing augmentation technique for hypervelocity scramjets. Washington : American Institute of Aeronautics and Astronautics, 1987.
Trouver le texte intégralBrescianini, C. P. An investigation of a wall-injected scramjet using a shock tunnel. Washington : AIAA, 1992.
Trouver le texte intégralRiggins, David W. A comparative study of scramjet injection strategies for high Mach number flows. Washington, D. C : American Institute of Aeronautics and Astronautics, 1992.
Trouver le texte intégralSkyring, R. Experimental determination of hydrogen-air detonation pressure limit and scramjet application. Washington : American Institute of Aeronautics and Astronautics, 1996.
Trouver le texte intégralCenter, Langley Research, dir. 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.
Trouver le texte intégralCenter, Langley Research, dir. 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.
Trouver le texte intégralCenter, Langley Research, dir. 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.
Trouver le texte intégralThomas, 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.
Trouver le texte intégralMinucci, 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.
Trouver le texte intégralBaysal, 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.
Trouver le texte intégralL, Semenov Vyacheslav, Hicks John W, Hugh L. Dryden Flight Research Center. et United States. National Aeronautics and Space Administration., dir. 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.
Trouver le texte intégralL, Semenov Vyacheslav, Hicks John W et Hugh L. Dryden Flight Research Center., dir. 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.
Trouver le texte intégralSteffen, Christopher J. Fuel injector design optimization for an annular scramjet geometry. [Cleveland, Ohio : NASA Glenn Research Center, 2003.
Trouver le texte intégralDomel, 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.
Trouver le texte intégralBaysal, Oktay. Viscous computations of cold air/air flow around scramjet nozzle afterbody. Hampton, Va : Langley Research Center, 1991.
Trouver le texte intégralUnited States. National Aeronautics and Space Administration. Scientific and Technical Information Division., dir. 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.
Trouver le texte intégralUnited States. National Aeronautics and Space Administration. Scientific and Technical Information Division., dir. 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.
Trouver le texte intégralUnited States. National Aeronautics and Space Administration., dir. Shock tunnel studies of scramjet phenomena : Final technical report, NAGW-674. [Washington, DC : National Aeronautics and Space Administration, 1996.
Trouver le texte intégralEdwards, 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.
Trouver le texte intégralHolland, 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.
Trouver le texte intégralCenter, Langley Research, dir. Internal aerodynamics of a generic three-dimensional scramjet inlet at Mach 10. Hampton, Va : National Aeronautics and Space Administration, Langley Research Center, 1995.
Trouver le texte intégralW, Kniskern Marc, Monta William J et United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., dir. 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.
Trouver le texte intégralHuebner, 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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