Download The Scramjet Engine: Processes and Characteristics by Corin Segal PDF

By Corin Segal

The renewed curiosity in high-speed propulsion has ended in elevated job within the improvement of the supersonic combustion ramjet engine for hypersonic flight functions. within the hypersonic regime the scramjet engine's particular thrust exceeds that of different propulsion platforms. This booklet, written through a number one researcher, describes the techniques and features of the scramjet engine in a unified demeanour, reviewing either the theoretical and experimental examine. the focal point is at the phenomena that dictate the thermo-aerodynamic techniques encountered within the scramjet engine, together with part analyses and flowpath issues; basic theoretical themes concerning inner circulation with chemical reactions and non-equilibrium results, high-temperature fuel dynamics, and hypersonic results are integrated. Cycle and part analyses are extra defined, through flowpath exam. ultimately, the publication reports the present experimental and theoretical functions and describes flooring checking out amenities and computational fluid dynamics amenities constructed thus far for the research of time-accurate, high-temperature aerodynamics.

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Additional resources for The Scramjet Engine: Processes and Characteristics (Cambridge Aerospace Series)

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1995). “Approach to in situ analysis of scramjet combustor behavior,” J. Propul. Power 11, 943–949. Sabel’nikov, V. A. and Penzin, V. I. (2000). “Scramjet research and development in Russia,” in Scramjet Propulsion (E. T. Curran and S. N. B. ), Vol 189 of Progress in Astronautics and Aeronautics, AIAA, pp. 223–368. Vinogradov, V. , and Sheechman, J. (1990). “Experimental investigation of 2-D dual mode scramjet with hydrogen fuel at Mach 4 . . 6,” in Proceedings of the AIAA Second International Aerospace Planes Conference, AIAA.

Further, specific issues that distinguish the high-speed flows in the regime that is generically referred to as “hypersonic” are reviewed. Without any abrupt demarcations in the flow properties, the hypersonic regime is considered in general to exist when the flight Mach number exceeds a value of ∼ 5. For a more accurate definition, the hypersonic regime could be considered to manifest when the entropy layer close to a surface immersed in the fluid becomes significant (Anderson, 1989). Although the flows through a scramjet approach this limit toward only the upper limit of its operability (see the cycle analysis discussion in Chap.

1 Introduction As the air energy increases, molecular vibrational excitation, followed by dissociation and chemical reactions, accompanies flows at high speed; it occurs on both the external vehicle surface and in the scramjet flow path. The viscous layer generated on the vehicle forebody, following deceleration and interactions with shock waves, may exhibit temperatures in excess of thousands of degrees. At these temperatures, chemical effects are just as important as in combustion chambers, where chemical reactions are intentionally induced and controlled; the gas composition departs substantially from the simplifications made through the assumption of thermal or calorically perfect gas and has a substantial impact on the flow structure, energy distribution, and, finally, thrust generation.

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