Author: Roy L. Bonney (CAPT, USAF., Jr)
Publisher:
ISBN:
Category : Jets
Languages : en
Pages :

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Author: Roy L. Bonney
Publisher:
ISBN:
Category :
Languages : en
Pages : 59

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This study investigated the mixing and flow field characteristics of helium and air using an array of two-dimensional Mach 3.0 nozzles. The study made use of schlieren photography, pressure measurements, and gas sampling for the analysis. Exit plane pressure ratios from 1.0 to 3.0 were investigated. Exit velocity ratios were assumed constant for all test conditions. Test equipment consisted of the nozzle array installed in a blow-down type system. Static pressure taps and total pressure probes were installed in the flow field downstream of the mixing nozzles to measure pressures. The probes were also used to capture gas samples. Pressure measurement results showed symmetry of the flow field. Gas samples and schlieren analysis indicated that mixing was a function of exit plane pressure ratio and distance from nozzle exit. (Author).

Author: John D. Carlile (CAPT, USAF.)
Publisher:
ISBN:
Category : Gasdynamic lasers
Languages : en
Pages :

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Author: Donald Edwin Johnson
Publisher:
ISBN:
Category :
Languages : en
Pages : 80

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The two-dimensional turbulent mixing region, resulting when a near sonic helium jet impinges at 30, 45 or 60 degrees on a supersonic air stream, was experimentally investigated utilizing an interferometer, a gas analyzer, and a total pressure rake. This type of mixing has a possible application in the supersonic combustion ramjet engine. Volumetric concentration profiles and a total pressure map of the mixing region were obtained for each injection angle. The mixing obtained for each injection angle was compared with that obtained with other injection systems. The techniques used for spark lamp photography are discussed. It was concluded that the interferometer cannot be focused so that fringes can be obtained throughout the mixing region at one interferometer setting. Many photographs at different interferometer settings would be required to determine the density distribution in the mixing region for gases having an extreme density difference. (Author).

Author: John D. Carlile
Publisher:
ISBN:
Category :
Languages : en
Pages : 47

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A facility to study two-dimensional supersonic air-helium mixing in a gas dynamic laser cavity was designed, constructed, and evaluated. The flow field may be analyzed via static and total pressure measurements, gas mixture samples, and schlieren photography. The multiple nozzle test section consisted of Mach 3.0 air nozzles alternated with Mach 3.0 helium nozzles exhausted into an instrumented test cavity. Pressure was maintained in the cavity by two alternate methods; simple diffusers exhausted to atmospheric conditions, and exhausting the cavity into a group of evaculated air tanks. Both methods gave similar cavity flow fields as indicated by schlieren photography and static pressure measurements. Gas samples and pressure measurements were taken with a series of small diameter probes and automatically timed solenoid valves. Gas samples were not analyzed in this study. Nozzle exit plane Mach numbers were calculated from pressure measurements and verified with schlieren photographs of a wedge inserted into the flow. The apparatus has low helium consumption and yields accurate, repeatable pressure measurements. The facility is to be used for a subsequent complete flow field analysis. (Author).

Author: Charlie Lee Yates
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 52

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Author: Charlie Lee Yates
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 52

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Author: Stephan P. Condon
Publisher:
ISBN:
Category :
Languages : en
Pages : 83

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An experimental investigation of the turbulent mixing of subsonic, sonic, and supersonic jets of helium discharging transversely into a supersonic jet of air was made using a two-dimensional mixing chamber. The investigation has a potential application in the field of the supersonic combustion ramjet engine. The Mach numbers of the helium jets were 0.75, 1.0, and 1.5, respectively, and the Mach number of the air jet was 1.5. Both the helium and air jets had stagnation temperatures of approximately 76F. The effects of combustion on the mixing were not considered. Volumetric concentration values and total pressure values were obtained at points in the mixing region, and helium volumetric concentration profiles were plotted. Schlieren photography was used to obtain a visualization of the flow structure. Sonic injection was found to be the most desirable method of injection due to depth of penetration and total pressure considerations. (Author).

Author: Joseph Johbu Nishikawa
Publisher:
ISBN:
Category : Jets
Languages : en
Pages : 104

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Author: Gilles L. Hamelin
Publisher:
ISBN:
Category :
Languages : en
Pages : 78

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An experimental investigation of the turbulent mixing of a sonic jet of helium discharging coaxially into a supersonic jet of air was made using a two dimensional mixing chamber. Volumetric concentration profiles were obtained and mass concentration and velocity along the jet centerline were plotted. The results indicated that both these vary inversely with the distance from the mixing origin raised to a four third power. Schlieren photography was applied in a semi-quantitative manner to confirm the validity of the above findings. This research project finds a potential application in the study and analysis of supersonic combustion ramjet engines. (Author).