Pub Date : 2003-08-25DOI: 10.1109/ICIASF.2003.1274873
T. J. Hicks, Joshua K. Schwannecke, M. J. Norconk, A. Hellum, John Foss
The evolved 100 kHz PWM-CTA extends the technology of the previous generation (50 kHz PWM-CTA) by doubling the sample frequency to 100 kHz, thereby improving the pulse width time resolution by a factor of 2:1. Substantial design changes serve to reduce the noise level in comparison with the previous generation 50 kHz PWM-CTA. An enhanced computer-based user interface has been implemented to simplify system operation.
{"title":"The evolved 100 kHz PWM-CTA","authors":"T. J. Hicks, Joshua K. Schwannecke, M. J. Norconk, A. Hellum, John Foss","doi":"10.1109/ICIASF.2003.1274873","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274873","url":null,"abstract":"The evolved 100 kHz PWM-CTA extends the technology of the previous generation (50 kHz PWM-CTA) by doubling the sample frequency to 100 kHz, thereby improving the pulse width time resolution by a factor of 2:1. Substantial design changes serve to reduce the noise level in comparison with the previous generation 50 kHz PWM-CTA. An enhanced computer-based user interface has been implemented to simplify system operation.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"9 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2003-08-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123747593","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 : 2003-08-25DOI: 10.1109/ICIASF.2003.1274872
S. de Ponte, S. Malavasi, C. Svelto, G. Matteazzi
In the last ICIASF conference a novel particle image velocimetry (PIV) system using two different time intervals by means of three colour flashes was presented. The system was jointly developed for the aerospace, hydraulics and electronic departments of "Politecnico di Milano", for the study of water flow and for the water tunnel simulation of aerodynamic phenomena. Here an improved three colour PIV system version is tested on a fundamental physical model. In this test we study the flow field around an obstacle normal to the free-stream direction. The phenomenon modelled is a water stream flowing over a sill, were we have both upstream and downstream recirculation and large velocity gradient. By using two different time intervals three velocity fields were obtained by applying the cross-correlation algorithm on the same image. This information was used to solve the whole velocity field with a more uniform distribution of the uncertainty of velocity measurement. The latter is mainly due to the displacement of the particles, therefore it was possible to choose the best one, having three different possibilities. Moreover different and close time delay allowed the evaluation of local rate of change of velocity which was computed using a first-order differencing scheme.
{"title":"A recirculating flow studied by three colour particle image velocimetry","authors":"S. de Ponte, S. Malavasi, C. Svelto, G. Matteazzi","doi":"10.1109/ICIASF.2003.1274872","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274872","url":null,"abstract":"In the last ICIASF conference a novel particle image velocimetry (PIV) system using two different time intervals by means of three colour flashes was presented. The system was jointly developed for the aerospace, hydraulics and electronic departments of \"Politecnico di Milano\", for the study of water flow and for the water tunnel simulation of aerodynamic phenomena. Here an improved three colour PIV system version is tested on a fundamental physical model. In this test we study the flow field around an obstacle normal to the free-stream direction. The phenomenon modelled is a water stream flowing over a sill, were we have both upstream and downstream recirculation and large velocity gradient. By using two different time intervals three velocity fields were obtained by applying the cross-correlation algorithm on the same image. This information was used to solve the whole velocity field with a more uniform distribution of the uncertainty of velocity measurement. The latter is mainly due to the displacement of the particles, therefore it was possible to choose the best one, having three different possibilities. Moreover different and close time delay allowed the evaluation of local rate of change of velocity which was computed using a first-order differencing scheme.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"54 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2003-08-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123320316","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 : 2003-08-25DOI: 10.1109/ICIASF.2003.1274874
R. Miles, S. Zaidi, Lipeng Qian, L. Vasilyak
Recent work has shown that imaging Rayleigh scattering through atomic and molecular filters provides a very attractive method for flow field diagnostics, including the imaging of temperature, density, and in some cases, velocity fields. The extension of atomic filter technologies to imaging Raman scattering is also of interest. Both Rayleigh and Raman scattering are dramatically stronger in the ultraviolet due to both resonance enhancement and to the frequency to the fourth scaling of the cross section. The development of a high-power, narrow linewidth source in the ultraviolet is, therefore, of significant interest. Mercury absorption cells operating at 254 nm are well suited for these diagnostics. This paper demonstrates that a short pulse-driven, high efficiency mercury lamp can be used to generate ultra-narrow linewidth radiation at 254 nm. The lamp is driven at 9 kHz with high voltage (30 kV), 2 nsec pulses and the spectrum of the radiation seen after several hundred nsec is almost purely the 254 nm line. The linewidth of this mercury lamp is narrow enough so it can be used in conjunction with the mercury vapor filter for both Rayleigh and Raman diagnostics.
{"title":"High brightness, ultra-narrow linewidth Hg source for diagnostics","authors":"R. Miles, S. Zaidi, Lipeng Qian, L. Vasilyak","doi":"10.1109/ICIASF.2003.1274874","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274874","url":null,"abstract":"Recent work has shown that imaging Rayleigh scattering through atomic and molecular filters provides a very attractive method for flow field diagnostics, including the imaging of temperature, density, and in some cases, velocity fields. The extension of atomic filter technologies to imaging Raman scattering is also of interest. Both Rayleigh and Raman scattering are dramatically stronger in the ultraviolet due to both resonance enhancement and to the frequency to the fourth scaling of the cross section. The development of a high-power, narrow linewidth source in the ultraviolet is, therefore, of significant interest. Mercury absorption cells operating at 254 nm are well suited for these diagnostics. This paper demonstrates that a short pulse-driven, high efficiency mercury lamp can be used to generate ultra-narrow linewidth radiation at 254 nm. The lamp is driven at 9 kHz with high voltage (30 kV), 2 nsec pulses and the spectrum of the radiation seen after several hundred nsec is almost purely the 254 nm line. The linewidth of this mercury lamp is narrow enough so it can be used in conjunction with the mercury vapor filter for both Rayleigh and Raman diagnostics.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"54 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2003-08-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115068405","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 : 2003-08-25DOI: 10.1109/ICIASF.2003.1274889
A. Watkins, J. D. Jordan, B. Leighty, J. L. Ingram, D. M. Oglesby
This paper describes a lifetime PSP system that has recently been developed using pulsed light-emitting diode (LED) lamps and a new interline transfer CCD camera technology. This system alleviates noise sources associated with lifetime PSP systems that use either flash-lamp or laser excitation sources and intensified CCD cameras for detection. Calibration curves have been acquired for a variety of PSP formulations using this system, and a validation test was recently completed in the subsonic aerodynamic research laboratory (SARL) at Wright-Patterson air force base (WPAFB). In this test, global surface pressure distributions were recovered using both a standard intensity-based method and the new lifetime system. Results from the lifetime system agree both qualitatively and quantitatively with those measured using the intensity-based method. Finally, an advanced lifetime imaging technique capable of measuring temperature and pressure simultaneously is introduced and initial results are presented.
{"title":"Development of next generation lifetime PSP imaging systems","authors":"A. Watkins, J. D. Jordan, B. Leighty, J. L. Ingram, D. M. Oglesby","doi":"10.1109/ICIASF.2003.1274889","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274889","url":null,"abstract":"This paper describes a lifetime PSP system that has recently been developed using pulsed light-emitting diode (LED) lamps and a new interline transfer CCD camera technology. This system alleviates noise sources associated with lifetime PSP systems that use either flash-lamp or laser excitation sources and intensified CCD cameras for detection. Calibration curves have been acquired for a variety of PSP formulations using this system, and a validation test was recently completed in the subsonic aerodynamic research laboratory (SARL) at Wright-Patterson air force base (WPAFB). In this test, global surface pressure distributions were recovered using both a standard intensity-based method and the new lifetime system. Results from the lifetime system agree both qualitatively and quantitatively with those measured using the intensity-based method. Finally, an advanced lifetime imaging technique capable of measuring temperature and pressure simultaneously is introduced and initial results are presented.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"121 3 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2003-08-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123177552","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 : 2003-08-25DOI: 10.1109/ICIASF.2003.1274886
V. Mosharov, A. Orlov, V. Radchenko
This paper presents an application of temperature sensitive paint (TSP) technique to measure full-field surface heat transfer rates in short-duration wind tunnel. Tests were performed on blunt-nose cone model (nose radius 10 mm, cone half-angle 10/spl deg/) in shock wind tunnel UT-1 (TsAGI) operated on Ludwig scheme at Mach number M=6 with flow duration 40 msec. Reynolds numbers calculated by nose radius were ranged between 60000 and 210000. Two type of TSP were used: monochromatic and two-color. Two-color paint contains additional temperature insensitive dye to compensate excitation light intensity variation. Experimental results have shown good repeatability but heat flux on the model nose was lower than CFD prediction and thermocouple measurement.
{"title":"Temperature sensitive paint (TSP) for heat transfer measurement in short duration wind tunnels","authors":"V. Mosharov, A. Orlov, V. Radchenko","doi":"10.1109/ICIASF.2003.1274886","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274886","url":null,"abstract":"This paper presents an application of temperature sensitive paint (TSP) technique to measure full-field surface heat transfer rates in short-duration wind tunnel. Tests were performed on blunt-nose cone model (nose radius 10 mm, cone half-angle 10/spl deg/) in shock wind tunnel UT-1 (TsAGI) operated on Ludwig scheme at Mach number M=6 with flow duration 40 msec. Reynolds numbers calculated by nose radius were ranged between 60000 and 210000. Two type of TSP were used: monochromatic and two-color. Two-color paint contains additional temperature insensitive dye to compensate excitation light intensity variation. Experimental results have shown good repeatability but heat flux on the model nose was lower than CFD prediction and thermocouple measurement.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"139 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2003-08-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126305535","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 : 2003-08-25DOI: 10.1109/ICIASF.2003.1274875
F. Leopold, F. Jagusinski, C. Demeautis
The interaction of a concentrated vortex and a shock wave may occur in many cases in the operational environment of supersonic aircraft and missiles. The interaction may be the result of vortices created by the forward components of a supersonic vehicle (for example canards, wings, etc) convecting downstream and interacting, for example, with shock waves present in front of air intakes or other wings. The objective of the present work is to conduct an experimental studies simulating the interaction of streamwise wing-tip vortices with shock waves in supersonic flows. Flow-field visualizations show the different behavior (for example: unsteady vortex breakdown). To elucidate the complex flow containing shock waves, backflow and large-scale fluctuations, measurements using a laser Doppler velocimeter (LDV) were carried out.
{"title":"Experimental investigation of shock/vortex interaction for slender canard configurations at supersonic speed","authors":"F. Leopold, F. Jagusinski, C. Demeautis","doi":"10.1109/ICIASF.2003.1274875","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274875","url":null,"abstract":"The interaction of a concentrated vortex and a shock wave may occur in many cases in the operational environment of supersonic aircraft and missiles. The interaction may be the result of vortices created by the forward components of a supersonic vehicle (for example canards, wings, etc) convecting downstream and interacting, for example, with shock waves present in front of air intakes or other wings. The objective of the present work is to conduct an experimental studies simulating the interaction of streamwise wing-tip vortices with shock waves in supersonic flows. Flow-field visualizations show the different behavior (for example: unsteady vortex breakdown). To elucidate the complex flow containing shock waves, backflow and large-scale fluctuations, measurements using a laser Doppler velocimeter (LDV) were carried out.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"726 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2003-08-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123849040","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 : 2003-08-25DOI: 10.1109/ICIASF.2003.1274849
S. Beresh, J. Henfling, R. J. Erven
A particle image velocimetry instrument has been constructed for a transonic wind tunnel and applied to study the interaction created by a supersonic axisymmetric jet exhausting from a flat plate into a subsonic compressible crossflow. Data have been acquired in two configurations; one is a two-dimensional measurement on the streamwise plane along the wind tunnel centerline, and the other is a stereoscopic measurement in the crossplane of the interaction. The presence of the induced counter-rotating vortex pair is clearly visible in both data sets. The streamwise-plane data determined the strength and location of the vortices using the vertical velocity component while the crossplane data directly provided a measurement of the vortical motion. A comparison of the vertical velocity component measured using each configuration showed reasonable agreement.
{"title":"Particle image velocimetry in the crossplane of a supersonic jet in subsonic compressible crossflow","authors":"S. Beresh, J. Henfling, R. J. Erven","doi":"10.1109/ICIASF.2003.1274849","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274849","url":null,"abstract":"A particle image velocimetry instrument has been constructed for a transonic wind tunnel and applied to study the interaction created by a supersonic axisymmetric jet exhausting from a flat plate into a subsonic compressible crossflow. Data have been acquired in two configurations; one is a two-dimensional measurement on the streamwise plane along the wind tunnel centerline, and the other is a stereoscopic measurement in the crossplane of the interaction. The presence of the induced counter-rotating vortex pair is clearly visible in both data sets. The streamwise-plane data determined the strength and location of the vortices using the vertical velocity component while the crossplane data directly provided a measurement of the vortical motion. A comparison of the vertical velocity component measured using each configuration showed reasonable agreement.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"6 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2003-08-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124997755","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 : 2003-08-25DOI: 10.1109/ICIASF.2003.1274870
F. Bao, H. Vollmers, H. Mattner
An experimental study was carried out to establish a self-destructing vortex wake. Sets of horizontal tail plains were employed to generate additional vortex sheet interacting with the wing vortex sheet of a rectangular wing. The study was made in the water towing tank in Gottingen (WSG), which was instrumented with 2D/3C PIV system, balance and flow visualisation devices. The tailoring of 4 vortices wake systems was achieved by varying horizontal tail plains with different aspect ratios with various incidences, generating various destabilising effects. The study exhibited that the interaction of tail vortices with tip vortices may result in a promising self-destructive mechanism within the wake system in the sense that the vortex core experiences an instability and decay abruptly. Typically, the wake vortex cores could be destabilised by as early as in 30 wing spans downstream with suitable tail settings, instead of more than 100 wing spans for that of a "clean model". The possible influence from the finite movement in the water tank due to transient processes of the model (end-effect) was investigated. The influence of the bottom and side wall effects was estimated from comparison of results from a larger water towing tank (HSVA).
{"title":"Experimental study on controlling wake vortex in water towing tank","authors":"F. Bao, H. Vollmers, H. Mattner","doi":"10.1109/ICIASF.2003.1274870","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274870","url":null,"abstract":"An experimental study was carried out to establish a self-destructing vortex wake. Sets of horizontal tail plains were employed to generate additional vortex sheet interacting with the wing vortex sheet of a rectangular wing. The study was made in the water towing tank in Gottingen (WSG), which was instrumented with 2D/3C PIV system, balance and flow visualisation devices. The tailoring of 4 vortices wake systems was achieved by varying horizontal tail plains with different aspect ratios with various incidences, generating various destabilising effects. The study exhibited that the interaction of tail vortices with tip vortices may result in a promising self-destructive mechanism within the wake system in the sense that the vortex core experiences an instability and decay abruptly. Typically, the wake vortex cores could be destabilised by as early as in 30 wing spans downstream with suitable tail settings, instead of more than 100 wing spans for that of a \"clean model\". The possible influence from the finite movement in the water tank due to transient processes of the model (end-effect) was investigated. The influence of the bottom and side wall effects was estimated from comparison of results from a larger water towing tank (HSVA).","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"25 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2003-08-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116774154","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 : 2003-08-25DOI: 10.1109/ICIASF.2003.1274856
K. Asai, I. Okura, H. Mizushima
The MOSAIC project is an interdisciplinary R&D project supported by the special coordination funds of the science and technology agency, Japanese Government. Specialists from four different fields (chemistry, optical measurement, image processing, and aero-thermodynamics) have been participating in this project to develop novel optical sensing technology using chemical molecules that enables us to visualize complex aero-thermodynamic flow field that was difficult to measure with conventional electric sensors. In this paper, the R&D activities of the MOSAIC project phase one program conducted from Japanese fiscal year 1999 to 2001 are overviewed. From the outcome of this program, the prospect to the future molecular sensor technology development is discussed.
{"title":"MOSAIC project - summary of phase one program","authors":"K. Asai, I. Okura, H. Mizushima","doi":"10.1109/ICIASF.2003.1274856","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274856","url":null,"abstract":"The MOSAIC project is an interdisciplinary R&D project supported by the special coordination funds of the science and technology agency, Japanese Government. Specialists from four different fields (chemistry, optical measurement, image processing, and aero-thermodynamics) have been participating in this project to develop novel optical sensing technology using chemical molecules that enables us to visualize complex aero-thermodynamic flow field that was difficult to measure with conventional electric sensors. In this paper, the R&D activities of the MOSAIC project phase one program conducted from Japanese fiscal year 1999 to 2001 are overviewed. From the outcome of this program, the prospect to the future molecular sensor technology development is discussed.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"5 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2003-08-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126282652","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 : 2003-08-25DOI: 10.1109/ICIASF.2003.1274844
J. Heineck, S. M. Walker, D.M. Yaste
A three-component particle image velocimetry (3C-PIV) system was designed installed in the 12-foot (3.7 m) pressure tunnel at NASA Ames Research Center. The system was designed for the testing of a 1/8/sup th/ scale tractor-trailer model called the generic conventional model (GCM). The 12-foot PWT can be pressurized to 6 atmospheres to enable the testing of Reynolds number effects. The data requirements forced a complex system design. Furthermore, the system had to reside inside the plenum where components sensitive to high pressure had to be isolated. Data were obtained in the gap between the tractor and the trailer where Reynolds number effects were suspected to occur. Sample data from this experiment are presented in this paper.
{"title":"The development of a 3C-PIV system for the 12-foot pressure tunnel at NASA Ames Research Center","authors":"J. Heineck, S. M. Walker, D.M. Yaste","doi":"10.1109/ICIASF.2003.1274844","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274844","url":null,"abstract":"A three-component particle image velocimetry (3C-PIV) system was designed installed in the 12-foot (3.7 m) pressure tunnel at NASA Ames Research Center. The system was designed for the testing of a 1/8/sup th/ scale tractor-trailer model called the generic conventional model (GCM). The 12-foot PWT can be pressurized to 6 atmospheres to enable the testing of Reynolds number effects. The data requirements forced a complex system design. Furthermore, the system had to reside inside the plenum where components sensitive to high pressure had to be isolated. Data were obtained in the gap between the tractor and the trailer where Reynolds number effects were suspected to occur. Sample data from this experiment are presented in this paper.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"6 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2003-08-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131695614","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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