ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025)最新文献_第4页

LIF imaging of species and temperature in technical combustion at elevated pressures 高压下技术燃烧中物质和温度的LIF成像

ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025) Pub Date : 1999-06-14 DOI: 10.1109/ICIASF.1999.827146

U. Meier, D. Wolff-Gassmann, J. Heinze, M. Frodermann, I. Magnusson, G. Josefsson

{"title":"LIF imaging of species and temperature in technical combustion at elevated pressures","authors":"U. Meier, D. Wolff-Gassmann, J. Heinze, M. Frodermann, I. Magnusson, G. Josefsson","doi":"10.1109/ICIASF.1999.827146","DOIUrl":"https://doi.org/10.1109/ICIASF.1999.827146","url":null,"abstract":"Planar laser-induced fluorescence (PLIF) has been used to measure time-resolved spatial distributions of temperature, fuel and OH in an SI engine, modified for optical access, and a jet engine combustion chamber segment. For temperature measurements, a two-line PLIF scheme was used: Two different rotational lines of the OH radical, which served as indicator molecule, were excited successively using nanosecond pulses from two laser systems operating on different wavelengths. The resulting fluorescence intensity is proportional to the population of the initial rotational state; the ratio of the two fluorescence signals is therefore proportional to the ratio of the populations, which in turn depends on the temperature. The fluorescence signal resulting from excitation by one of the two lasers is proportional to the OH density and provides thus information on flame structure. If the laser is tuned away from an OH resonance, fluorescence resulting from kerosene can be observed. The measurements presented here provide information on flame structure, heat release and mixing properties, which can serve as design aids, as well as for CFD code validation purposes.","PeriodicalId":291132,"journal":{"name":"ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025)","volume":"25 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1999-06-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127010392","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 7

A new generation traversing rig with minimum disturbances for a closed test section of subsonic wind tunnels 新一代亚声速风洞封闭试验段最小扰动穿越装置

ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025) Pub Date : 1999-06-14 DOI: 10.1109/ICIASF.1999.827171

T. Seung

{"title":"A new generation traversing rig with minimum disturbances for a closed test section of subsonic wind tunnels","authors":"T. Seung","doi":"10.1109/ICIASF.1999.827171","DOIUrl":"https://doi.org/10.1109/ICIASF.1999.827171","url":null,"abstract":"A probe traversing system developed for efficient operations in low speed wind tunnels has been developed. This traversing system of a new generation allows automatic scans of the entire test section with a wide variety of probes. The design of the rig considered both its stiffness and the aerodynamic interference. Special beam modules made of carbon fiber composite were developed for the main arm of the rig. When the rig is not in use, the beam modules can be easily dismantled from the base carriage and the entire system can move to a park position outside of the test section. The system exhibits high stability in positioning accuracy, eliminating the need for re-calibration before each application. The attainable positioning accuracy and the adjustable speed of traverse meet the demands of modern measuring instruments. The operating software 'AOSTA' (Advanced Operating System for the Traversing Appliance) controls not only the drive units of the system but also has an editor to generate the measuring grids. Grid generation is supported by graphic functions and a 'Teach-In' function to reduce the risk of collision between the probe and the model. 'AOSTA' runs in a Windows 98/NT environment and can communicate with a hierarchical computer via an IEEE488 interface, if required.","PeriodicalId":291132,"journal":{"name":"ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025)","volume":"78 8","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1999-06-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131614019","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Development and applications of a rapid flight test prototyping system for unmanned air vehicles 无人飞行器快速飞行试验样机系统的研制与应用

ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025) Pub Date : 1999-06-14 DOI: 10.1109/ICIASF.1999.827166

E. Hallberg, J. Komlosy, T. Rivers, M. Watson, D. Meeks, J. Lentz, I. Kaminer, O. Yakimenko

引用次数: 7

Investigations on a dynamic forebody flow control system 动态前体流动控制系统的研究

ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025) Pub Date : 1999-06-14 DOI: 10.1109/ICIASF.1999.827168

E. Hanff, R. Lee, R. Kind

引用次数: 30

3-component-Doppler-laser-2-focus: a new kind of three component velocimeter 三分量多普勒激光双聚焦:一种新型三分量测速仪

ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025) Pub Date : 1999-06-14 DOI: 10.1109/ICIASF.1999.827152

I. Roehle, G. Karpinsky, R. Schodl

引用次数: 3

A re-evaluation of a pulsed laser technique for measuring surface heat transfer coefficients 测量表面传热系数的脉冲激光技术的再评价

ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025) Pub Date : 1999-06-14 DOI: 10.1109/ICIASF.1999.827179

W. Carscallen, W. Turnbull

{"title":"A re-evaluation of a pulsed laser technique for measuring surface heat transfer coefficients","authors":"W. Carscallen, W. Turnbull","doi":"10.1109/ICIASF.1999.827179","DOIUrl":"https://doi.org/10.1109/ICIASF.1999.827179","url":null,"abstract":"Data from a previously reported experimental technique, for measuring wall shear stress using a pulsed laser, is re-evaluated using a new numerically based data reduction technique in order to determine surface heat transfer coefficients. This new technique was suggested by recent experimental studies into the use of uncalibrated liquid crystals and periodic heat fluxes to measure absolute values of the local heat transfer coefficient and wall shear stress. These studies, which were initially based upon a one-dimensional analytical conduction model, demonstrated that the shape of the temperature-time response, to an instantaneous deposition of energy on a surface, is a function of the thermophysical properties of the surface and the value of the local heat transfer coefficient. In order to account for situations where two-dimensional effects are important a new numerical model has been developed. It is possible, using this new model, to extend the previous phase delay technique to measure heat transfer coefficients to the case whereby a pulsed laser is used to initiate a temperature transient. The new results using the old data show reasonable agreement with those predicted by a standard correlation. Suggestions are made on how the technique can be significantly improved.","PeriodicalId":291132,"journal":{"name":"ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025)","volume":"9 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1999-06-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114567944","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Status of pressure sensitive paint technology at National Aerospace Laboratory 国家航空航天实验室压敏涂料技术现状

ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025) Pub Date : 1999-06-14 DOI: 10.1109/ICIASF.1999.827155

K. Asai

引用次数: 13

Application of 3 component laser-Doppler velocimetry in transonic flow over a delta wing 三分量激光多普勒测速在三角翼跨声速流动中的应用

ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025) Pub Date : 1999-06-14 DOI: 10.1109/ICIASF.1999.827153

T.J. Moller, A. Wiedemann, K. Butefisch, F. Micheli, D. Scholz, K. Sjors

{"title":"Application of 3 component laser-Doppler velocimetry in transonic flow over a delta wing","authors":"T.J. Moller, A. Wiedemann, K. Butefisch, F. Micheli, D. Scholz, K. Sjors","doi":"10.1109/ICIASF.1999.827153","DOIUrl":"https://doi.org/10.1109/ICIASF.1999.827153","url":null,"abstract":"In the development of numerical codes for the prediction of aerodynamic flows is a strong need to obtain reliable flow field data which is suited to validate turbulence models used in numerical calculations. In three dimensional boundary layers Laser-Doppler Velocimetry (LDV) is the appropriate technique usually applied to obtain this kind of data. Since LDV, being a single point measurement technique, is a time consuming method, it is desirable to have the ability to make use of data from different experiments and research groups. Therefore it is necessary to have a standard to compare experimental results obtained by different LDV processors and to define a consistent mathematical algorithm to process data from the different LDV experiments. This is the objective of the present paper. In an European activity four different research groups have conducted common experiments in industrial wind tunnels and finally compared the results to qualify LDV for the application in industrial wind tunnel and to define a standard to compare LDV data coming from different sources.","PeriodicalId":291132,"journal":{"name":"ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025)","volume":"107 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1999-06-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132410432","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 1

Experimental investigations on vortex breakdown over delta wings with Doppler global velocimetry 基于多普勒全局测速的三角翼涡击穿实验研究

ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025) Pub Date : 1999-06-14 DOI: 10.1109/ICIASF.1999.827149

M. Forstermann, K. Butefisch

{"title":"Experimental investigations on vortex breakdown over delta wings with Doppler global velocimetry","authors":"M. Forstermann, K. Butefisch","doi":"10.1109/ICIASF.1999.827149","DOIUrl":"https://doi.org/10.1109/ICIASF.1999.827149","url":null,"abstract":"The fluid dynamic properties of the flow over a delta wing are still not yet fully understood. Recent numerical simulations have shown that the stability of the vortices could be best judged and observed by resolving the unsteady velocity distributions of the axial velocity vector component in the vortex core region. For an experimental validation of these numerical results it is necessary to obtain the three dimensional velocity distribution in the vortex core. Obtaining the velocity distribution should work without influencing the flow because the stability property is very sensitive against any disturbance in the flow. A non intrusive optical technique is chosen as adequate to measure the velocity distribution: Doppler Global Velocimetry. It is based on the Doppler shift of laser light due to scattering at moving particles. By extensively seeding the flow with these particles it was possible to determine the unsteady three dimensional velocity distribution in the vortex core. The experiment shows a good agreement with the numerically predicted flow structures.","PeriodicalId":291132,"journal":{"name":"ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025)","volume":"31 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1999-06-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130137695","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 2

Electronically scanned pressure measurement scanner for cryogenic wind tunnel applications 低温风洞应用的电子扫描压力测量扫描仪

ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025) Pub Date : 1999-06-14 DOI: 10.1109/ICIASF.1999.827176

Q. Shams, A.J. Zuckerwar

{"title":"Electronically scanned pressure measurement scanner for cryogenic wind tunnel applications","authors":"Q. Shams, A.J. Zuckerwar","doi":"10.1109/ICIASF.1999.827176","DOIUrl":"https://doi.org/10.1109/ICIASF.1999.827176","url":null,"abstract":"Electronically scanned pressure (ESP) measurement modules are used in wind tunnels to measure surface pressures on models. Measurement channels are connected to pressure ports through small diameter tubing. Use of current state-of-the art ESP scanners in cryogenic wind tunnels has led to several practical problems which contribute to additional expense and loss of data quality. First current use of ESP scanners in cryogenic wind tunnels (at room temperature to below -25/spl deg/ C) dictates the need for protection against the thermal environment. The current solution is the use of a heater box which causes a number of operational problems. The installation of the heater box is time-consuming and labor-intensive. Its size reduces the amount of space available for scanner installation. Secondly, a wind tunnel test must be interrupted for on-line calibration which consumes as much as 15% of the total test time. Finally, the pressure and balance measurements are taken in separate runs because of an \"apparent strain\" problem. An electronically scanned pressure measurement module capable of operating directly in a cryogenic environment has been developed and tested over an extended temperature span. Total uncertainty, which is measured at less than 0.1% of FSO at 1 atmospheric reference pressure will be discussed.","PeriodicalId":291132,"journal":{"name":"ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025)","volume":"37 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1999-06-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132550602","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 3