Pub Date : 1993-09-20DOI: 10.1109/ICIASF.1993.687679
V. Strunck, G. Grosche, D. Dopheide
Laser Doppler Anemometry (LDA) is a non-intrusive method to measure velocities in fluid flows, often with the aim to determine the velocity profile for a given fluid. As other methods common LDA techniques rely on measuring the velocity in a small probe volume and then varying its position in the test section. The spatial resolution of such velocity profile is limited in principal by the size of the probe volume (say 1 mm). The new methlod and its variations allow improvements of the spatial resolutiion by at least one order of magnitude and to measure a small scale velocity profile while leaving the measuring apparatus fixed
{"title":"New Laser Doppler Sensors for Spatial Velocity Information","authors":"V. Strunck, G. Grosche, D. Dopheide","doi":"10.1109/ICIASF.1993.687679","DOIUrl":"https://doi.org/10.1109/ICIASF.1993.687679","url":null,"abstract":"Laser Doppler Anemometry (LDA) is a non-intrusive method to measure velocities in fluid flows, often with the aim to determine the velocity profile for a given fluid. As other methods common LDA techniques rely on measuring the velocity in a small probe volume and then varying its position in the test section. The spatial resolution of such velocity profile is limited in principal by the size of the probe volume (say 1 mm). The new methlod and its variations allow improvements of the spatial resolutiion by at least one order of magnitude and to measure a small scale velocity profile while leaving the measuring apparatus fixed","PeriodicalId":398832,"journal":{"name":"International Congress on Instrumentation in Aerospace Simulation Facilities,","volume":"6 1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-09-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131310585","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}
Pub Date : 1993-09-20DOI: 10.1109/ICIASF.1993.687660
M. Swoboda, F. Haselbach, L. Wald, W. Nitsche
This paper describes applications of the surjace hot-film technique for determining wall shear stresses in either laminar or turbulent flows. Based on an integral heat balance, a ratio of conductive io convective heat loss from a flush mounted surface hot-film can be formulated in relationship to Reynolds number based on the friction velocity. This calibration procedure is valid for both, laminar and turbulent flows. To determine the temperature field of a su~ace hot#lm, hotwire measurementS were carried out in the vicinity of the hotfilm. Apart @om this experimental investigation, comparative numerical calculations of the temperature field around a surface hot-film are presented in this paper.
{"title":"On Surface Hot-Film Applications in Laminar-Turbulent Flows","authors":"M. Swoboda, F. Haselbach, L. Wald, W. Nitsche","doi":"10.1109/ICIASF.1993.687660","DOIUrl":"https://doi.org/10.1109/ICIASF.1993.687660","url":null,"abstract":"This paper describes applications of the surjace hot-film technique for determining wall shear stresses in either laminar or turbulent flows. Based on an integral heat balance, a ratio of conductive io convective heat loss from a flush mounted surface hot-film can be formulated in relationship to Reynolds number based on the friction velocity. This calibration procedure is valid for both, laminar and turbulent flows. To determine the temperature field of a su~ace hot#lm, hotwire measurementS were carried out in the vicinity of the hotfilm. Apart @om this experimental investigation, comparative numerical calculations of the temperature field around a surface hot-film are presented in this paper.","PeriodicalId":398832,"journal":{"name":"International Congress on Instrumentation in Aerospace Simulation Facilities,","volume":"2 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-09-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128183533","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}
Pub Date : 1993-09-20DOI: 10.1109/ICIASF.1993.687647
P. Gnemmi, J. Haertig, C. Johe, F. Albe
The French-German Research Institcite of Saint Louis (ISL) carries out researches i n aerodynaintcs and acoustics to predict the thickness and loading noise of helicopter rotors ISL has added experiinental studios to the theoretirat ones in order to compare theoretical aspects with iiieasureinents Then a model of a rotor ha5 been built. siniulattng the hovering flight, able to reach transonic speed a1 the blade tips This equipment allows to carry out force ineasurenienls on the rotor head and in the Matics ancl the driving toique A shadowgraph arrangement is tised lo v isua l i7~ the rotor model wake Around the rotor model wr also make acoustic nieasurenients in the blades plane l ip to a distance of one rotor diaineler lo validate the thickness noise calculation of a rotor in hover flight When we compare ralculattons with measureinents. we find thal the thickness i iotsr ir, wall predicted by ROTAC up to a t i p Mach iicimher of 0 86
{"title":"Measurements on the Isl Rotor Model","authors":"P. Gnemmi, J. Haertig, C. Johe, F. Albe","doi":"10.1109/ICIASF.1993.687647","DOIUrl":"https://doi.org/10.1109/ICIASF.1993.687647","url":null,"abstract":"The French-German Research Institcite of Saint Louis (ISL) carries out researches i n aerodynaintcs and acoustics to predict the thickness and loading noise of helicopter rotors ISL has added experiinental studios to the theoretirat ones in order to compare theoretical aspects with iiieasureinents Then a model of a rotor ha5 been built. siniulattng the hovering flight, able to reach transonic speed a1 the blade tips This equipment allows to carry out force ineasurenienls on the rotor head and in the Matics ancl the driving toique A shadowgraph arrangement is tised lo v isua l i7~ the rotor model wake Around the rotor model wr also make acoustic nieasurenients in the blades plane l ip to a distance of one rotor diaineler lo validate the thickness noise calculation of a rotor in hover flight When we compare ralculattons with measureinents. we find thal the thickness i iotsr ir, wall predicted by ROTAC up to a t i p Mach iicimher of 0 86","PeriodicalId":398832,"journal":{"name":"International Congress on Instrumentation in Aerospace Simulation Facilities,","volume":"119 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-09-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114600976","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}
Pub Date : 1993-09-20DOI: 10.1109/ICIASF.1993.687691
Y. Le Sant, J. Edy
Probative research is being conducted at ONERA on a new technique for measuring heat transfer in wind tunnels. This method is based on the heat sensitivity of a luminescent coating applied to the model. This coating emits visible light when it is excited by UV light, and the emission properties depend mainly on its temperature. Discrete measurements with a special photothermometer were made during preliminary blowdown wind tunnel tests. The results agreed well with other discrete measurements, such as thin-film measurements. The main advantage of this new technique is to provide thermographic measurements. This requires a video system, a digital image processing system, and a data reduction technique that is more sophisticated than the discrete data reduction technique. The thermographic system that was defined and calibrated is described in this paper. The first results obtained on a sphere are in satisfactory agreement with a prediction based on the Fay-Riddell theory. Consequently, this method is currently considered to be a valid heat flux meaurement technique.
{"title":"Phosphor Thermography Technique in Hypersonic Wind Tunnels: First Results","authors":"Y. Le Sant, J. Edy","doi":"10.1109/ICIASF.1993.687691","DOIUrl":"https://doi.org/10.1109/ICIASF.1993.687691","url":null,"abstract":"Probative research is being conducted at ONERA on a new technique for measuring heat transfer in wind tunnels. This method is based on the heat sensitivity of a luminescent coating applied to the model. This coating emits visible light when it is excited by UV light, and the emission properties depend mainly on its temperature. Discrete measurements with a special photothermometer were made during preliminary blowdown wind tunnel tests. The results agreed well with other discrete measurements, such as thin-film measurements. The main advantage of this new technique is to provide thermographic measurements. This requires a video system, a digital image processing system, and a data reduction technique that is more sophisticated than the discrete data reduction technique. The thermographic system that was defined and calibrated is described in this paper. The first results obtained on a sphere are in satisfactory agreement with a prediction based on the Fay-Riddell theory. Consequently, this method is currently considered to be a valid heat flux meaurement technique.","PeriodicalId":398832,"journal":{"name":"International Congress on Instrumentation in Aerospace Simulation Facilities,","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-09-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124397562","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}
Pub Date : 1993-09-20DOI: 10.1109/ICIASF.1993.687681
A. Heyes, J. Turner
{"title":"Application of Lda and Dgv to Complex High Speed Flows","authors":"A. Heyes, J. Turner","doi":"10.1109/ICIASF.1993.687681","DOIUrl":"https://doi.org/10.1109/ICIASF.1993.687681","url":null,"abstract":"","PeriodicalId":398832,"journal":{"name":"International Congress on Instrumentation in Aerospace Simulation Facilities,","volume":"14 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-09-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122947504","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}
Pub Date : 1993-09-20DOI: 10.1109/ICIASF.1993.687687
T.H. Stannov
A new calibrator for hot-wires has been developed to meet requirements for high efficiency, high accuracy and low turbulence calibrations. The calibrator is a free jet type and true differential pressure is measured across the exit nozzle and used with isentropic relations to estimate actual velocity. The calibrator itself is portable and can be installed in front of the hot-wire probe in many cases. It works with most noncorrosive gases at standard air tools pressure.
{"title":"A New Calibrator for Improved Performance of Hot-Wires","authors":"T.H. Stannov","doi":"10.1109/ICIASF.1993.687687","DOIUrl":"https://doi.org/10.1109/ICIASF.1993.687687","url":null,"abstract":"A new calibrator for hot-wires has been developed to meet requirements for high efficiency, high accuracy and low turbulence calibrations. The calibrator is a free jet type and true differential pressure is measured across the exit nozzle and used with isentropic relations to estimate actual velocity. The calibrator itself is portable and can be installed in front of the hot-wire probe in many cases. It works with most noncorrosive gases at standard air tools pressure.","PeriodicalId":398832,"journal":{"name":"International Congress on Instrumentation in Aerospace Simulation Facilities,","volume":"22 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-09-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126743142","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}
Pub Date : 1993-09-20DOI: 10.1109/ICIASF.1993.687646
L. de Luca, G. Cardone, G. Carlomagno
Abstrnef Heat transfer measurements performed by means of an Infrared Scanning Radiometer in a blowdown hypersonic wind tunnel are discussed In particular, the formation of Goertler-type vortices in the reattaching flow region over the flap following a flat plate is investigated, as well as its influence on the wall hezt transfer distribution Tests are carried out within the European Community Hermes space program to develop the first european space shuttle.
{"title":"Goertler Vortices in Hypersonic Flow Detected by IR Thermography","authors":"L. de Luca, G. Cardone, G. Carlomagno","doi":"10.1109/ICIASF.1993.687646","DOIUrl":"https://doi.org/10.1109/ICIASF.1993.687646","url":null,"abstract":"Abstrnef Heat transfer measurements performed by means of an Infrared Scanning Radiometer in a blowdown hypersonic wind tunnel are discussed In particular, the formation of Goertler-type vortices in the reattaching flow region over the flap following a flat plate is investigated, as well as its influence on the wall hezt transfer distribution Tests are carried out within the European Community Hermes space program to develop the first european space shuttle.","PeriodicalId":398832,"journal":{"name":"International Congress on Instrumentation in Aerospace Simulation Facilities,","volume":"25 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-09-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125104493","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}
Pub Date : 1993-09-20DOI: 10.1109/ICIASF.1993.687678
H. Schafer, E. Sommer
Laser Doppler velocimeter measurements have been camed out in a high-temperature circular jet produced by a smallscale turbojet propulsion engine. Using digital auitoand cross-correlation techniques, timedependent statistical characteristics of the jet turbulence, such as power spectral dcnsity, convection velocity, time and length scales were determined. In good agreement with previous measurements in isothermal jets, the present results suggest that there exists a coherent flow structure underlying the random jet turbulence. The effect of exit Mach number and jet temperature on the structural characteristics is examined.
{"title":"Laser Velocimeter Investigation of Coherent Structures in a Turbojet Exhaust","authors":"H. Schafer, E. Sommer","doi":"10.1109/ICIASF.1993.687678","DOIUrl":"https://doi.org/10.1109/ICIASF.1993.687678","url":null,"abstract":"Laser Doppler velocimeter measurements have been camed out in a high-temperature circular jet produced by a smallscale turbojet propulsion engine. Using digital auitoand cross-correlation techniques, timedependent statistical characteristics of the jet turbulence, such as power spectral dcnsity, convection velocity, time and length scales were determined. In good agreement with previous measurements in isothermal jets, the present results suggest that there exists a coherent flow structure underlying the random jet turbulence. The effect of exit Mach number and jet temperature on the structural characteristics is examined.","PeriodicalId":398832,"journal":{"name":"International Congress on Instrumentation in Aerospace Simulation Facilities,","volume":"52 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-09-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134215264","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}
Pub Date : 1993-09-20DOI: 10.1109/ICIASF.1993.687688
F. E. Jørgensen
{"title":"A New Concept for an Automated Hot-Wire Anemometer with Fully Integrated Experiment Management","authors":"F. E. Jørgensen","doi":"10.1109/ICIASF.1993.687688","DOIUrl":"https://doi.org/10.1109/ICIASF.1993.687688","url":null,"abstract":"","PeriodicalId":398832,"journal":{"name":"International Congress on Instrumentation in Aerospace Simulation Facilities,","volume":"159 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-09-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115579061","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}
Pub Date : 1993-09-20DOI: 10.1109/ICIASF.1993.687649
K. Naumann, H. Ende, G. Mathieu, A. George
{"title":"Technique for Millisecond Aerodynamic Force Measurement with Models Exhausting Jets","authors":"K. Naumann, H. Ende, G. Mathieu, A. George","doi":"10.1109/ICIASF.1993.687649","DOIUrl":"https://doi.org/10.1109/ICIASF.1993.687649","url":null,"abstract":"","PeriodicalId":398832,"journal":{"name":"International Congress on Instrumentation in Aerospace Simulation Facilities,","volume":"17 5","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-09-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"120843595","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}
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