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Study Of Injection Of Helium Into Supersonic Air Flow Using Rayleigh Scattering
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Book Synopsis Study of Injection of Helium Into Supersonic Air Flow Using Rayleigh Scattering by :
Download or read book Study of Injection of Helium Into Supersonic Air Flow Using Rayleigh Scattering written by and published by . This book was released on 1997 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Study of injection of helium into supersonic air flow using Rayleigh scattering by : Richard G. Seasholtz
Download or read book Study of injection of helium into supersonic air flow using Rayleigh scattering written by Richard G. Seasholtz and published by . This book was released on 1997 with total page 12 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Study of Injection of Helium Intor Supersonic Air Flow Using Rayleigh Scattering by : R. G. Seasholtz
Download or read book Study of Injection of Helium Intor Supersonic Air Flow Using Rayleigh Scattering written by R. G. Seasholtz and published by . This book was released on 1997 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Analytical and Experimental Studies on Mixing in Supersonic Flows by : Vijay Gopal
Download or read book Analytical and Experimental Studies on Mixing in Supersonic Flows written by Vijay Gopal and published by . This book was released on 2021 with total page 175 pages. Available in PDF, EPUB and Kindle. Book excerpt: Mixing enhancement in supersonic flow is an important domain of research for enabling the realization of efficient and scalable high speed air-breathing engines (scramjet).Introducing streamwise vorticies in supersonic flow and tailoring their interactions for mixing enhancement is the primary motivation for the present research study. Leveraging the research performed in the group at the Aerodynamics Research Center (ARC), systematic experimental studies on mixing enhancement is carried out in supersonic flows by tailoring the selected modes of stream wise vortex interactions with the aid of in-house developed reduced order method VorTX. This method utilizes the lifting line-vortex theory in supersonic flow to perform rapid simulations of streamwise vortex-interactions that serves as a guide to design the mixing experiments. One of the difficulties associated with scaling the simulations to higher Mach numbers (M > 4) arise from the strong influence of the singularities along the Mach cones emanating from the lifting line-vortex that results in physically inconsistent solution. In this work a fundamental study on vorticity distribution in linearized supersonic flow is carried out. The origin of the aforementioned singularities on the Mach cone is discussed in detail, and the potential candidates for vorticity distribution are proposed to eliminate the singularities and to provide a physically consistent solution of the flow field in supersonic flow. This study presents the successful solution for the elimination of the singularities that has allowed to extend the capability of VorTX to simulate vortex-interactions at higher Mach numbers. Experimental studies on supersonic mixing were carried out using a strut injection platform with vortex generating ramps to introduce streamwise voriticies in supersonic flow. The geometrical configuration of the ramps are chosen using the upgraded VorTX simulations to target the experimental study of two selected modes of vortex interactions. One is the merging of two co-rotating vorticies and the other is the non-merging case where the vorticies interact but do not merge. Mixing measurements in supersonic flow were carried out using the Filtered Rayleigh Scattering (FRS)technique. The measurement yields the mole-fraction of helium (injectant) in a binary mixture of air and helium in supersonic flow. The distributions of helium mole-fraction in the cross flow planes are used to draw conclusions on the level of mixing in the two modes of vortex-interaction. The FRS technique requires two independent experiments. One with helium injection in supersonic air flow and the other with air injection in an identical supersonic air flow. At a given cross-flow plane, to obtain the helium mole-fraction distribution using the FRS signals it is assumed that the total number density is matched in both the experiments. To enhance the reliability of the FRS measurement technique, it is important to minimize and quantify the systematic errors that arise from the assumptions made, particularly, the assumption on matching the total number density. In this work, a method to reduce the systematic errors in FRS experiments is proposed for a canonical case study of a rectangular jet in supersonic flow. To do this, a reduced order model for a rectangular jet in supersonic air flow is successfully developed in order to guide the selection of appropriate injector's plenum conditions to minimize the systematic errors in the future FRS experiments and to retrospectively evaluate and correct the FRS measurements for systematic errors in previously available FRS data on parallel strut injection in supersonic flow.
Book Synopsis Investigation of Ramp Injectors for Supersonic Mixing Enhancement by : Y. Haimovitch
Download or read book Investigation of Ramp Injectors for Supersonic Mixing Enhancement written by Y. Haimovitch and published by . This book was released on 1994 with total page 260 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of Ramp Injectors for Supersonic Mixing Enhancement by : Y. Haimovitch
Download or read book Investigation of Ramp Injectors for Supersonic Mixing Enhancement written by Y. Haimovitch and published by . This book was released on 1994 with total page 246 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Analytical and Experimental Investigation of the Annular Injection of Helium Into a Supersonic Air Core by : Clarence Albert Kemper
Download or read book An Analytical and Experimental Investigation of the Annular Injection of Helium Into a Supersonic Air Core written by Clarence Albert Kemper and published by . This book was released on 1962 with total page 208 pages. Available in PDF, EPUB and Kindle. Book excerpt: When a lightweight gas is injected into the boundary layer of a high-speed air flow, the adiabatic wall temperature is reduced by means of a change in properties of the gas in the region where viscous dissipation occurs. The paper summarizes some of the results of a controlled experiment in which helium was injected through an annular slot and along the impermeable surface of a 1.46 inch diameter tube in which a supersonic air stream was flowing at a Mach number of about 4.8. A discussion of some of the analytical results which were obtained is also given. The experimental portion of the investigation included the development of miniaturized boundary layer instrumentation capable of measuring velocity, temperature, and concentration profiles of the flow.
Book Synopsis Normal Injection of Helium from Swept Struts Into Ducted Supersonic Flow by :
Download or read book Normal Injection of Helium from Swept Struts Into Ducted Supersonic Flow written by and published by . This book was released on 1975 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Improved Optical Techniques for Studying Sonic and Supersonic Injection Into Mach 3 Flow by :
Download or read book Improved Optical Techniques for Studying Sonic and Supersonic Injection Into Mach 3 Flow written by and published by . This book was released on 1997 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 702 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Monthly Catalog of United States Government Publications by :
Download or read book Monthly Catalog of United States Government Publications written by and published by . This book was released on 1998 with total page 148 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Optical Techniques in Fluid, Thermal and Combustion Flow by :
Download or read book Optical Techniques in Fluid, Thermal and Combustion Flow written by and published by . This book was released on 1997 with total page 786 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Optical Technology in Fluid, Thermal, and Combustion Flow III by : Soyoung S. Cha
Download or read book Optical Technology in Fluid, Thermal, and Combustion Flow III written by Soyoung S. Cha and published by SPIE-International Society for Optical Engineering. This book was released on 1997 with total page 746 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scramjet Propulsion by : E. T. Curran
Download or read book Scramjet Propulsion written by E. T. Curran and published by AIAA. This book was released on 2001 with total page 1354 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Study of Secondary Injection of Gases Into a Supersonic Flow by : R. Rosen
Download or read book A Study of Secondary Injection of Gases Into a Supersonic Flow written by R. Rosen and published by . This book was released on 1966 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Design and Evaluation of a Facility to Study Two-Dimensional Supersonic Air-Helium Mixing by : John D. Carlile
Download or read book Design and Evaluation of a Facility to Study Two-Dimensional Supersonic Air-Helium Mixing written by John D. Carlile and published by . This book was released on 1978 with total page 47 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).
Book Synopsis International Aerospace Abstracts by :
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1999 with total page 934 pages. Available in PDF, EPUB and Kindle. Book excerpt: