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Effects of exhaust plume temperature on vortex-wake/ground interaction

作者:科技文献资料网 时间:2018-10-19 11:01:04  浏览:8951   来源:科技文献资料网
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[唯一标识符]:CDSITC.AEROSPACE.A98-32425
[文献来源]:美国航空航天数据库(aerospace);美国航空航天学会会议(AIAA)
[资源原始索取号]:A1998-32425; Reference AN: A98-32425
[标题]:Effects of exhaust plume temperature on vortex-wake/ground interaction
[作者]:Kandil Osama A; Adam Ihab G
[书名]:IN: AIAA, Applied Aerodynamics Conference, 16th, Albuquerque, NM, June 15-18, 1998, Technical Papers (A98-32401 08-02), Reston, VA, American Institute of Aeronautics and Astronautics, 1998, p. 270-287
[文摘]:The effect of exhaust plume temperature on the vortex-wake descent, separation and rebound near the ground is investigated. The 3D, compressible Navier-Stokes (NS) equations are solved numerically. The implicit, upwind, Roe flux-differencing, finite volume scheme is used. The computations of vortex-wake/exhaust plume interaction with the ground are carried out using an overlapping zonal method for long distances downstream. Typical velocity profiles of a tip vortex for Boeing 757 and Boeing 747, with and without exhaust plume temperature profiles, are used for inflow boundary conditions. The vortex-wake is subjected to crosswind flow, and both upwind and downwind vortices are considered. Results of the vortex-wake descent, separation, and rebound with and without exhaust plume are compared. (Author)
[关键词]:EXHAUST GASES; WING TIP VORTICES; AIRCRAFT WAKES; INTERACTIONAL AERODYNAMICS; TEMPERATURE PROFILES; GROUND EFFECT AERODYNAMICS; PLUMES ; BOEING 757 AIRCRAFT; COMPRESSIBLE FLOW; NAVIER STOKES EQUATION; IMPLICIT METHODS; FLUX DIFFERENCE SPLITTING
[出版年份]:1998
[专业领域]:AERODYNAMICS
[馆藏索取号]:A9832425
[总页数]:18


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[唯一标识符]:CDSITC.AEROSPACE.A91-16003
[文献来源]:美国航空航天数据库(aerospace)
[资源原始索取号]:A1991-16003; Reference AN: A91-16003
[标题]:Spectral signature extraction from airborne imagery using the Geoscan MkII advanced airborne scanner in the Leonora, Western Australia gold district
[作者]:LYON R J P; HONEY F R
[书名]:IN: Quantitative remote sensing: An economic tool for the Nineties; Proceedings of IGARSS '89 and Canadian Symposium on Remote Sensing, 12th, Vancouver, Canada, July 10-14, 1989. Volume 5 (A1991-15476 04-43). New York, Institute of Electrical and Electro
[关键词]:AIRBORNE EQUIPMENT; IMAGING SPECTROMETERS; INFRARED DETECTORS; MULTISPECTRAL BAND SCANNERS; SPECTRAL SIGNATURES; AUSTRALIA ; GOLD ; REAL TIME OPERATION; REFLECTANCE
[出版年份]:1989
[专业领域]:EARTH RESOURCES AND REMOTE SENSING
[唯一标识符]:CDSTIC.AIAA 2009-4825
[文献来源]:美国航空航天学会会议(AIAA)
[文献类型]:科技会议
[标题]:Biannular Airbreathing Nozzle Rig Facility Development at Purdue University
[作者]:A. Sandroni, C. Cummings, Y. Matsutomi, S. Meyer, J. Sullivan, and S. Heister, Purdue University, West Lafayette, IN
[出版单位]:美国航空航天局
[文摘]:American Institute of Aeronautics and Astronautics 1 Biannular Airbreathing Nozzle Rig Facility Development at Purdue University Alexander M. Sandroni1 and Chase B. Cummings2 Purdue University, West Lafayette, Indiana, 47906 Yu Matsutomi3 and Scott Meyer4 Purdue University, West Lafayette, Indiana, 47906 and Dr. Stephen D. Heister5 Purdue University, West Lafayette, Indiana, 47906 The Biannular Airbreathing Nozzle Rig (BANR) facility has been developed at Purdue University for the purpose of evaluating the performance of airbreathing propulsion nozzle concepts. The facility has been made operational, and a plug nozzle designed for a supersonic business jet (SSBJ) mission has been extensively tested over a wide range of conditions. Diagnostic tools of the facility include a suite of pressure instrumentation, a traversing rake system for measuring temperatures and pressures in nozzle exhaust plumes, and a six-axis force measurement system. The facility has been demonstrated to operate reliably and consistently at all investigated test conditions, and conditions entering the test article were seen to be uniform in each stream for all tests. Performance data from the plug nozzle, including discharge and force coefficients have been obtained for a variety of cold flow and hot-fire conditions. Nomenclature A = nozzle exit area A8 = theoretical stream throat area Cd = nozzle discharge coefficient Cf = thrust coefficient F = thrust = mass flowrate MFP = mass flow parameter M8 = theoretical stream throat mach number NPR = nozzle pressure ratio P = static pressure Pt = total pressure R = specific gas constant Tt = total temperature Ve = nozzle jet exit velocity γ = ratio of specific heats η = thrust efficiency 1 Master’s graduate, School of Aeronautics and Astronautics, AIAA Student Member 2 Master’s student, School of Aeronautics and Astronautics, AIAA Student Member 3 Doctoral student, School of Aeronautics and Astronautics, AIAA Student Member 4 Senior Engineer, Purdue University Maurice J. Zucrow Laboratories, AIAA Senior Member 5 Professor, School of Aeronautics and Astronautics, Purdue University, 701 W. Stadium Ave., W. Lafayette, IN 47907, AIAA Associate Fellow
[出版时间]:2009
[出版年份]:2009
[会议名称]:45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit
[馆藏索取号]:AIAA2009-4825
[总页数]:12



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