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Hypersonic Airbreathing Propulsion

Author : William H. Heiser
ISBN : 1563470357
Genre : Science
File Size : 82.84 MB
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Winner of the Summerfield Book Award. The next great leap for jet propulsion will be to power-sustained, efficient flight through the atmosphere.
Category: Science

Hypersonic Airbreathing Propulsion Evolution And Opportunities

Author : P. J. Waltrup
ISBN : OCLC:228022257
Genre :
File Size : 38.1 MB
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A history of the evolution of airbreathing propulsion, with emphasis on the development of supersonic combustion ramjet (scramjet) engines, is presented. The current status of scramjet engines is discussed and deficiencies in fundamental and applied data and/or knowledge, which comprise opportunities for future work, are noted.

Scramjet Propulsion

Author : E. T. Curran
ISBN : 1600864414
Genre : Airplanes
File Size : 42.95 MB
Format : PDF
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Category: Airplanes

Thermodynamic Cycle Analysis Of Magnetohydrodynamic Bypass Hypersonic Airbreathing Engines

Author : R. J. Litchford
ISBN : NASA:31769000451503
Genre : Electric rocket engines
File Size : 85.11 MB
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The prospects for realizing a magnetohydrodynamic (MHD) bypass hypersonic airbreathing engine are examined from the standpoint of fundamental thermodynamic feasibility. The MHD-bypass engine, first proposed as part of the Russian AJAX vehicle concept, is based on the idea of redistributing energy between various stages of the propulsion system flow train. The system uses an MHD generator to extract a portion of the aerodynamic heating energy from the inlet and an MHD accelerator to reintroduce this power as kinetic energy in the exhaust stream. In this way, the combustor entrance Mach number can be limited to a specified value even as the flight Mach number increases. Thus, the fuel and air can be efficiently mixed and burned within a practical combustor length, and the flight Mach number operating envelope can be extended. In this paper, we quantitatively assess the performance potential and scientific feasibility of MHD-bypass engines using a simplified thermodynamic analysis. This cycle analysis, based on a thermally and calorically perfect gas, incoporates a coupled MHD generator-accelerator system and accounts for aerodynamic losses and thermodynamic process efficiencies in the various engine components. It is found that the flight Mach number range can be significantly extended; however, overall performance is hampered by non-isentropic losses in the MHD devices.
Category: Electric rocket engines