Sustained Supersonic Combustion In The Laboratory Under Low Density Conditions
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Author | : Robert G. Dunn |
Publisher | : |
Total Pages | : 38 |
Release | : 1969 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Download Sustained Supersonic Combustion in the Laboratory Under Low Density Conditions Book in PDF, Epub and Kindle
An investigation of supersonic combustion simulating conditions anticipated in propulsive systems for high altitude, high Mach number flight is described. A unique test facility in operation at the Aerospace Research Laboratories has the capability of simulating supersonic combustion conditions for flight Mach numbers near 12. The facility is considered unique because of its capability of providing conditions under which supersonic combustion can occur at low desities (1-4 psia) with diffusive mixing and with combustion resulting from auto-ignition. Experiments have been conducted with injector/combustor configurations to evaluate the ignition mechanism for axisymmetric streams of hydrogen and air and to evolve a combustion chamber design suitable for experimental study of sustained supersonic combustion. In a parallel theoretical phase, a numberical analysis of the combustion chamber flow field has been made by high speed computer; a parametric study of supersonic combustion in the diffusive hydrogen-air flow field over an air-jet Mach number range of 1.5 to 2.5 and a static pressure range of 1 to 3 psia was accomplished. Experimental data to-date have conclusively established the occurrence of sustained supersonic combustion in the diffusive hydrogen-air flow field at combustor entrance static pressures near 2.5 psia. (Author).
Author | : James E. Drewry |
Publisher | : |
Total Pages | : 17 |
Release | : 1969 |
Genre | : Airplanes |
ISBN | : |
Download Supersonic Combustion Studies at Low Density Conditions Book in PDF, Epub and Kindle
An investigation of supersonic combustion as related to propulsive systems for high Mach number, high altitude flight is described. A method of laboratory simulation is employed which is considered to be suitable for fundamental studies of diffusional-controlled supersonic combustion under conditions approaching those of actual flight. A numerical analysis of the mixing and combustion processes for an axisymmetric hydrogen-air ducted flow system was carried out, using a computer code based upon boundary layer concepts and including the effects of finite-rate chemistry. A limited parametric study of the combustor flow field was made for a Mach number range of 1.5 to 2.5 for the injected air stream. Hydrogen injection is central and parallel to the air stream and is assumed to occur sonically. A matched pressure condition between the fuel and air streams is assumed to exist at the combustor inlet. Inlet static pressures in the range of 0.1 to 0.2 atmospheres were considered. Results of the parametric study indicated the inlet conditions required to achieve auto-ignition within a reasonable combustor length. Based on the numerical data obtained, a mixing and combustion chamber was designed and fabricated for the performance of experimental tests under conditions closely matching those of the numerical study. Experimental data from a number of laboratory tests in which supersonic combustion was obtained are presented and discussed. (Author).
Author | : |
Publisher | : |
Total Pages | : 670 |
Release | : |
Genre | : Aeronautics |
ISBN | : |
Download OAR Progress Book in PDF, Epub and Kindle
Author | : |
Publisher | : |
Total Pages | : 304 |
Release | : 1991 |
Genre | : Aeronautics |
ISBN | : |
Download Scientific and Technical Aerospace Reports Book in PDF, Epub and Kindle
Author | : |
Publisher | : |
Total Pages | : 240 |
Release | : 1967 |
Genre | : |
ISBN | : |
Download OAR Book in PDF, Epub and Kindle
Author | : James E. Drewry |
Publisher | : |
Total Pages | : 35 |
Release | : 1968 |
Genre | : |
ISBN | : |
Download Studies of Hydrogen-air Supersonic Combustion at Low Densities Book in PDF, Epub and Kindle
An investigation of supersonic combustion as related to propulsive systems for high Mach number, high altitude flight is described. A method of laboratory simulation is employed which is considered to be suitable for fundamental studies of diffusional-controlled supersonic combustion under conditions approaching those of actual flight. A numerical analysis of the mixing and chemical reaction processes in a hydrogen-air ducted flow system was carried out, using a computer code based upon boundary layer concepts and including the effects of finite-rate chemistry. Results of the numerical calculations have indicated the inlet conditions at which auto-ignition is expected to occur within a reasonable combustor length. Based on the numerical data obtained, a constant area-divergent area combustion chamber was designed and fabricated for the performance of experimental tests under conditions closely matching those of the numerical study. (Author).
Author | : |
Publisher | : |
Total Pages | : 666 |
Release | : 1970 |
Genre | : Science |
ISBN | : |
Download U.S. Government Research & Development Reports Book in PDF, Epub and Kindle
Author | : |
Publisher | : |
Total Pages | : 1214 |
Release | : 1969 |
Genre | : Science |
ISBN | : |
Download U. S. Government Research and Development Reports Book in PDF, Epub and Kindle
Author | : |
Publisher | : |
Total Pages | : 728 |
Release | : 1969 |
Genre | : Government publications |
ISBN | : |
Download U.S. Government Research and Development Reports Index Book in PDF, Epub and Kindle
Author | : |
Publisher | : |
Total Pages | : 1020 |
Release | : 1969 |
Genre | : Science |
ISBN | : |
Download Bibliography of Scientific and Industrial Reports Book in PDF, Epub and Kindle