Книги з теми "Scramjet engine"
Оформте джерело за APA, MLA, Chicago, Harvard та іншими стилями
Ознайомтеся з топ-50 книг для дослідження на тему "Scramjet engine".
Біля кожної праці в переліку літератури доступна кнопка «Додати до бібліографії». Скористайтеся нею – і ми автоматично оформимо бібліографічне посилання на обрану працю в потрібному вам стилі цитування: APA, MLA, «Гарвард», «Чикаго», «Ванкувер» тощо.
Також ви можете завантажити повний текст наукової публікації у форматі «.pdf» та прочитати онлайн анотацію до роботи, якщо відповідні параметри наявні в метаданих.
Переглядайте книги для різних дисциплін та оформлюйте правильно вашу бібліографію.
The scramjet engine: Processes and characteristics. Cambridge: Cambridge University Press, 2009.
Знайти повний текст джерелаBurkardt, Leo A. RAMSCRAM: A flexible ramjet/scramjet engine simulation program. [Washington, DC]: National Aeronautics and Space Administration, 1990.
Знайти повний текст джерелаCenter, 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.
Знайти повний текст джерелаCenter, Langley Research, ed. Mach 10 experimental database of a three-dimensional scramjet inlet flow field. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.
Знайти повний текст джерелаHolland, 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.
Знайти повний текст джерелаCenter, Langley Research, ed. 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.
Знайти повний текст джерелаCenter, Langley Research, ed. 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.
Знайти повний текст джерелаCenter, Langley Research, ed. 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.
Знайти повний текст джерелаT, Curran E., and Murthy S. N. B, eds. Scramjet propulsion. Reston, Va: American Institute of Aeronautics and Astronautics, 2000.
Знайти повний текст джерелаSchetz, Joseph A. Studies in scramjet flowfields. [S.l.]: American Institute of Aeronautics and Astronautics, 1987.
Знайти повний текст джерелаUnited States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, ed. Heat pipe cooling for scramjet engines. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.
Знайти повний текст джерелаSilverstein, Calvin C. Heat pipe cooling for scramjet engines. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.
Знайти повний текст джерелаUnited 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.
Знайти повний текст джерелаSislian, Jean Pascal. Inviscid on-design propulsive characteristics of hypersonic shock-induced combustion ramjets. North York, Ont: Institute for Aerospace Studies, University of Toronto, 1997.
Знайти повний текст джерелаUnited 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.
Знайти повний текст джерелаWittenberg, H. Some fundamentals on the performance of ramjets with subsonic and supersonic combustion. Rijswijk, The Netherlands: TNO Prins Maurits Laboratory, 2000.
Знайти повний текст джерелаCenter, Langley Research, ed. HYPULSE combustor analysis. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1993.
Знайти повний текст джерелаCenter, Langley Research, ed. HYPULSE combustor analysis. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1993.
Знайти повний текст джерелаO'Neill, Mary Kae L. Optimized scramjet integration on a waverider. Washington, D. C: American Institute of Aeronautics and Astronautics, 1991.
Знайти повний текст джерелаUnited States. National Aeronautics and Space Administration., ed. A first scramjet study. [Washington, DC: National Aeronautics and Space Administration, 1989.
Знайти повний текст джерелаIshiguro, Tomiko. Numerical calculation of scramjet inlet flow. Tokyo, Japan: National Aerospace Laboratory, 1992.
Знайти повний текст джерелаJacobs, P. A. Preliminary calibration of a generic scramjet combustor. Hampton, Va: Institute for Computer Applications in Science and Engineering, 1991.
Знайти повний текст джерелаMorgan, R. G. Further shock tunnel studies of scramjet phenomena. St.Lucia, Australia: University of Queensland, 1986.
Знайти повний текст джерелаParent, Bernard. Computational study of fuel injection in a shcramjet inlet. [Downsview, Ont.]: University of Toronto, Institute for Aerospace Studies, 2002.
Знайти повний текст джерелаRogers, R. Clayton. Scramjet mixing establishment times for a pulse facility. Washington, D. C: American Institute of Aeronautics and Astronautics, 1991.
Знайти повний текст джерелаJacobs, P. A. Flow establishment in a generic scramjet combustor. Hampton, Va: Institute for Computer Applications in Science and Engineering, 1990.
Знайти повний текст джерелаRyerson Polytechnical Institute. Dept. of Mechanical Engineering. Investigations in the fluid dynamics of scramjet inlets. Toronto: Ryerson Polytechnical Institute ; University of Toronto, 1992.
Знайти повний текст джерелаMenon, S. Shock-wave-induced mixing enhancement in scramjet combustors. Washington, D. C: American Institute of Aeronautics and Astronautics, 1989.
Знайти повний текст джерелаScotti, Stephen J. Active cooling design for scramjet engines using optimization methods. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1988.
Знайти повний текст джерелаJ, Martin Carl, Lucas Stephen H, and Langley Research Center, eds. Active cooling design for scramjet engines using optimization methods. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1988.
Знайти повний текст джерелаJ, 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.
Знайти повний текст джерелаMorgan, R. G. Shock tunnel studies of scramjet phenomena 1994. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.
Знайти повний текст джерелаJ, 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.
Знайти повний текст джерелаKumar, Ajay. A mixing augmentation technique for hypervelocity scramjets. Washington: American Institute of Aeronautics and Astronautics, 1987.
Знайти повний текст джерелаSteffen, Christopher J. Fuel injector design optimization for an annular scramjet geometry. [Cleveland, Ohio: NASA Glenn Research Center, 2003.
Знайти повний текст джерелаBrescianini, C. P. An investigation of a wall-injected scramjet using a shock tunnel. Washington: AIAA, 1992.
Знайти повний текст джерелаUnited States. National Aeronautics and Space Administration. Scientific and Technical Information Program., ed. 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.
Знайти повний текст джерелаTimnat, Y. M. Advanced airbreathing propulsion. Malabar, Fla: Krieger Pub. Co., 1996.
Знайти повний текст джерелаSkyring, R. Experimental determination of hydrogen-air detonation pressure limit and scramjet application. Washington: American Institute of Aeronautics and Astronautics, 1996.
Знайти повний текст джерелаEdwards, 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.
Знайти повний текст джерелаMekkes, 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.
Знайти повний текст джерелаThomas, 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.
Знайти повний текст джерелаMinucci, 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.
Знайти повний текст джерелаBaysal, 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.
Знайти повний текст джерелаHartley, T. T. A hierarchy for modeling high speed propulsion systems. [Washington, DC: National Aeronautics and Space Administration, 1991.
Знайти повний текст джерелаDash, Sanford M. Computational models for the analysis/design of hypersonic scramjet nozzles - Part 1: Combustor and nozzle models. New York: AIAA, 1986.
Знайти повний текст джерелаBaysal, Oktay. Viscous computations of cold air/air flow around scramjet nozzle afterbody. Hampton, Va: Langley Research Center, 1991.
Знайти повний текст джерелаHeiser, William H. Hypersonic airbreathing propulsion: With Daniel H. Daley and Unmeel B. Mehta. Washington, D.C: American Institute of Aeronautics and Astronautics, 1994.
Знайти повний текст джерелаUnited 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.
Знайти повний текст джерелаCenter, 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.
Знайти повний текст джерела