Calculated Performance of a Compression-ignition Engine-compressor-turbine Combination Based on Experimental Data PDF Download
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Author: Alexander Mendelson Publisher: ISBN: Category : Diesel motor Languages : en Pages : 28
Book Description
Comparison with a compression-ignition engine using a turbosupercharger showed that little could be gained by gearing the turbine to the engine, provided the turbosupercharger could be stably operated with a closed wast gate.
Author: Alexander Mendelson Publisher: ISBN: Category : Diesel motor Languages : en Pages : 28
Book Description
Comparison with a compression-ignition engine using a turbosupercharger showed that little could be gained by gearing the turbine to the engine, provided the turbosupercharger could be stably operated with a closed wast gate.
Author: J. C. Sanders Publisher: ISBN: Category : Airplanes Languages : en Pages : 28
Book Description
Small high-speed single-cylinder compression-ignition engines were tested to determine their performance characteristics under high supercharging. Calculations were made on the energy available in the exhaust gas of the compression-ignition engines. The maximum power at any given maximum cylinder pressure was obtained when the compression pressure was equal to the maximum cylinder pressure. Constant-pressure combustion was found possible at an engine speed of 2200 rpm. Exhaust pressures and temperatures were determined from an analysis of indicator cards. The analysis showed that, at rich mixtures with the exhaust back pressure equal to the inlet-air pressure, there is excess energy available for driving a turbine over that required for supercharging. The presence of this excess energy indicates that a highly supercharged compression-ignition engine might be desirable as a compressor and combustion chamber for a turbine.
Author: Max A. Heaslet Publisher: ISBN: Category : Aerodynamics, Supersonic Languages : en Pages : 656
Book Description
Under the assumptions of linearized theory, general methods of solutin are given for two- and three-dimensional steady-state and two-dimensional unsteady-state equations of compressible flow. The solutions depend in all cases on the use of Green's equivalent layer of sources, sinks, and doublets. Emphasis is placed on applications in supersonic wing theory, the singularities arising in the integrations being treated by Hadamard's finite part of the technique. Four examples of different character are discussed. In particular, the load distribution over a specific swept-back lifting surface is determined at a free-stream Mach number of one.
Author: Alexander Mendelson
Author: Alexander Mendelson
Author: J. C. Sanders
Author: Alexander Mendelson
Author: Alexander Mendelson
Author: 
Author: United States. National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Author: Max A. Heaslet
Author: 
Author: