E., Morphology of a Standing Oblique Detonation Wave, Washington D. Kenneth, K., Principles of Combustion, New York: John Wiley, 1986. L., The interaction of shock waves and heat addition in the design of supersonic combustors, 12th Symposium (International) on Combustion, Poitiers France, 1968, 1125–1134. Yuan, S., Huang, Z., Optimality of C-J Oblique Detonation as Supersonic Combustion Modes, Washington D. A., Combustion Fundamentals, New York: McGraw-Hill Book Company, 1984. H., Dynamics and Thermodynamics of Compressible Fluid Flow, New York: Ronald Press Company, 1953, 231. H., On the Thermodynamic Spectrum of Airbreathing Propulsion, Washington D. It consists of a converging section with minimum area occurring at a specific location called the throat. A CD Nozzle is a variable area passage which is used to accelerate gases to higher supersonic speeds. W., Position paper on chemical kinetics of combustion processes, Major Research Topics in Combustion (ed. Intro In this lesson we will analyze the flow in a converging-diverging (CD) Nozzle. Liu Ling, Supersonic Combustion and Scramjets (in Chinese), Xi’an: North West Tech. C.: AIAA Inc., 1994.īeach, H., Lee, Jr., Supersonic combustion status and issues, Major Research Topics in Combustion (ed. In fact, the figure indicates that, for subsonic flow ( ), a decreasing cross-sectional area of the nozzle in the direction of the gas flow leads to an increasing flow speed, and decreasing pressure, density, and temperature. T., Hypersonic Airbreathing Propulsion, Washington D.
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