Author: Antonio Ferri
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 136
Book Description
A theoretical and experimental investigation of mixing and supersonic combustion is presented. A review of the problem under investigation is given. Then an analysis of inviscid flow fields with a finite rate chemistry for a hydrogen-air reaction is presented, an an analysis of a turbulent mixing for flows with large density gradients with no chemical reaction is presented. The analysis is compared wit the experimental results. Results of the experiments in upersonic combustion are presented. (Author).
Theoretical and Experimental Investigation of Supersonic Combustion
Author: Antonio Ferri
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 136
Book Description
A theoretical and experimental investigation of mixing and supersonic combustion is presented. A review of the problem under investigation is given. Then an analysis of inviscid flow fields with a finite rate chemistry for a hydrogen-air reaction is presented, an an analysis of a turbulent mixing for flows with large density gradients with no chemical reaction is presented. The analysis is compared wit the experimental results. Results of the experiments in upersonic combustion are presented. (Author).
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 136
Book Description
A theoretical and experimental investigation of mixing and supersonic combustion is presented. A review of the problem under investigation is given. Then an analysis of inviscid flow fields with a finite rate chemistry for a hydrogen-air reaction is presented, an an analysis of a turbulent mixing for flows with large density gradients with no chemical reaction is presented. The analysis is compared wit the experimental results. Results of the experiments in upersonic combustion are presented. (Author).
Experimental Investigation of Isolator for Supersonic Combustion
Author: G. Balu
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Theoretical and Experimental Performance of a Supersonic Combustion Boundary-layer Facility
Author: David Lewis Boyd
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 342
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 342
Book Description
Sustained Supersonic Combustion in the Laboratory Under Low Density Conditions
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).
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).
Experimental Investigation of a Supersonic Combustion Solid Fuel Ramjet
Author: Abraham Cohen
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Theoretical and Experimental Investigation of Supersonic Aerodynamic Characteristics of a Twin-fuselage Concept
Author: Peter L. Meitner
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
AFOSR.
Author: United States. Air Force. Office of Scientific Research
Publisher:
ISBN:
Category : Research
Languages : en
Pages : 968
Book Description
Publisher:
ISBN:
Category : Research
Languages : en
Pages : 968
Book Description
Experimental Investigation of Supersonic Combustion of Liquid Hydrocarbon Fuel Using Barbotage in the Aeroramp Configuration at M
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
Book Description
This report results from a contract tasking TsAGl as follows: The contractor will investigate combustion of kerosene using barbotage by hydrogen and air in the aeroramp configuration at M=2.5 as described in his proposal dated 1 Jun 98.
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
Book Description
This report results from a contract tasking TsAGl as follows: The contractor will investigate combustion of kerosene using barbotage by hydrogen and air in the aeroramp configuration at M=2.5 as described in his proposal dated 1 Jun 98.
Vaporizing and Endothermic Fuels for Advanced Engine Application: Part Iv. Preliminary Study of the Supersonic Combustion of Endothermic Hydrocarbon Fuels
Author: W. Chinitz
Publisher:
ISBN:
Category :
Languages : en
Pages : 101
Book Description
A theoretical and experimental investigation has been undertaken to define the supersonic combustion characteristics of endothermic hydrocarbon fuels which are of interest as a result of research carried out at Shell Development Company. In the program discussed herein, principal attention was focussed upon the propane and methylcyclohexane dehydrogenation fuel systems. The ultimate objective is to define the parameters that affect the combustion process and to establish the feasibility of burning these fuels in supersonic flows. (Author).
Publisher:
ISBN:
Category :
Languages : en
Pages : 101
Book Description
A theoretical and experimental investigation has been undertaken to define the supersonic combustion characteristics of endothermic hydrocarbon fuels which are of interest as a result of research carried out at Shell Development Company. In the program discussed herein, principal attention was focussed upon the propane and methylcyclohexane dehydrogenation fuel systems. The ultimate objective is to define the parameters that affect the combustion process and to establish the feasibility of burning these fuels in supersonic flows. (Author).
Experimental Investigation of a Supersonic Combustion Flowfield Employing Staged Transverse Injection Behind a Rearward-facing Step
Author: John D. Abbitt
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description