Author: James E. Drewry Publisher: ISBN: Category : Airplanes Languages : en Pages : 17
Book Description
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: Robert G. Dunn Publisher: ISBN: Category : Aerodynamics, Supersonic Languages : en Pages : 38
Book Description
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: ISBN: Category : Languages : en Pages : 35
Book Description
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: Mingbo Sun Publisher: Springer Nature ISBN: 9811535957 Category : Technology & Engineering Languages : en Pages : 380
Book Description
This book describes the unsteady phenomena needed to understand supersonic combustion. Following an initial chapter that introduces readers to the basic concepts in and classical studies on unsteady supersonic combustion, the book highlights recent studies on unsteady phenomena, which offer insights on e.g. interactions between acoustic waves and flames, flow dominating instability, ignition instability, flame flashback, and near-blowout-limit combustion. In turn, the book discusses in detail the fundamental mechanisms of these phenomena, and puts forward practical suggestions for future scramjet design.
Author: Publisher: ISBN: Category : Aeronautics Languages : en Pages : 880
Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Author: Anthony Michael Valenti Publisher: ISBN: Category : Languages : en Pages :
Book Description
"An experimental study of supersonic combustion bas been performed using the McGill University pebble bed heated wind tunnel. Supersonic combustion was achieved in a stainless steel combustion tube and in a free jet issuing from the tube. Due to fuel mixing delay time, the combustion efficiency was very low. The total heat addition was limited to a small value by friction in the combustion tube. Computer programmes were written for the I.B.M. 650 digital computer to calculate test conditions and to compute Mach Number and total pressure profiles in the tube, with and without combustion. Because of the low combustion efficiency, the calculated profiles do not agree with the experimental values for cases with combustion." --
Author: N. Abuaf Publisher: ISBN: Category : Languages : en Pages : 30
Book Description
Measurements of axial and radial velocity distributions in axisymmetric free jets of pure gases and binary gas mixtures are reported. Results are compared with extensions of the kinetic theory approach developed by Hamel and Willis and by Edwards and Cheng. The use of binary gas mixtures to produce molecular beams in the 1-10 ev range is described. Measurements of diffusive separation of mixtures in free jets are reported and compared with the theoretical predictions of Zigan and Sherman for nearly continuum flow. (Author).
Author: James E. Drewry
Author: Robert G. Dunn
Author: James E. Drewry
Author: Mingbo Sun
Author: 
Author: 
Author: 
Author: Anthony Michael Valenti
Author: N. Abuaf
Author: Roy A. Cookson