Pub Date : 2003-08-25DOI: 10.1109/ICIASF.2003.1274846
C. Willert, G. Stockhausen, J. Klinner, M. Beversdorff, J. Quest, U. Jansen, M. Raffel
A specially designed Doppler global velocimetry system (DGV, planar Doppler velocimetry) was tested in a high-speed cryogenic facility at Mach 0.3 to Mach 0.8 and pressures between 1.2 and 2.5 bar. The necessary seeding was achieved by injecting a mixture of gaseous nitrogen and water vapor into the dry and cold tunnel flow which then immediately formed a large amount of small ice crystals. As operational and access conditions are quite restrictive with respect to other facilities, DGV is currently considered the best choice for the non-intrusive measurement of flow fields. A comparison of DGV to the more wide-spread particle image velocimetry technique (PIV) is also given.
{"title":"On the development of Doppler global velocimetry for cryogenic wind tunnels","authors":"C. Willert, G. Stockhausen, J. Klinner, M. Beversdorff, J. Quest, U. Jansen, M. Raffel","doi":"10.1109/ICIASF.2003.1274846","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274846","url":null,"abstract":"A specially designed Doppler global velocimetry system (DGV, planar Doppler velocimetry) was tested in a high-speed cryogenic facility at Mach 0.3 to Mach 0.8 and pressures between 1.2 and 2.5 bar. The necessary seeding was achieved by injecting a mixture of gaseous nitrogen and water vapor into the dry and cold tunnel flow which then immediately formed a large amount of small ice crystals. As operational and access conditions are quite restrictive with respect to other facilities, DGV is currently considered the best choice for the non-intrusive measurement of flow fields. A comparison of DGV to the more wide-spread particle image velocimetry technique (PIV) is also given.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"80 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":"114446068","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.2003.1274883
A. V. Mikheev, V. M. Zubtsov
Inherent or laser induced irradiation of individual solid/liquid tracer particles or distinguishable groups of molecules (e.g. injected into hot flow in the form of liquid evaporating droplets) is examined as an information source of both temperature and velocity fields in an assumption of accurately measurable radiation intensity, captured from individual tracer, associated with tracer's temperature. Feasibility, limitations and most attractive embodiments of the technique as applying primarily to high-temperature flows using commercially available visible and near-infrared CCD sensors are considered. Error analysis of the measurement system has been carried out using numerically simulated images for preferred embodiments. Numerical simulation experiments carried out verify feasibility and estimated features of proposed technique. This technique seems to be quite attractive alternative to more sophisticated technologies for a number of particular applications most of all due to much less expensive implementation and simple calibration providing acceptable accuracy with sub-pixel spatial resolution. Undergoing demonstration experiments are described.
{"title":"Simultaneous determination of temperature and velocity flow fields by enhanced two-color PTV technique","authors":"A. V. Mikheev, V. M. Zubtsov","doi":"10.1109/ICIASF.2003.1274883","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274883","url":null,"abstract":"Inherent or laser induced irradiation of individual solid/liquid tracer particles or distinguishable groups of molecules (e.g. injected into hot flow in the form of liquid evaporating droplets) is examined as an information source of both temperature and velocity fields in an assumption of accurately measurable radiation intensity, captured from individual tracer, associated with tracer's temperature. Feasibility, limitations and most attractive embodiments of the technique as applying primarily to high-temperature flows using commercially available visible and near-infrared CCD sensors are considered. Error analysis of the measurement system has been carried out using numerically simulated images for preferred embodiments. Numerical simulation experiments carried out verify feasibility and estimated features of proposed technique. This technique seems to be quite attractive alternative to more sophisticated technologies for a number of particular applications most of all due to much less expensive implementation and simple calibration providing acceptable accuracy with sub-pixel spatial resolution. Undergoing demonstration experiments are described.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"106 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":"124096711","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.2003.1274879
S. O’Byrne, P. Danehy, A. Cutler
The dual-pump coherent anti-Stokes Raman spectroscopy (CARS) method is used to measure temperature and the relative species densities of N/sub 2/, O/sub 2/ and H/sub 2/ in two experiments. Average values and root-mean-square (RMS) deviations are determined. Mean temperature measurements in a furnace containing air between 300 and 1800 K agreed with thermocouple measurements within 26 K on average, while mean mole fractions agree to within 1.6% of the expected value. The temperature measurement standard deviation averaged 64 K while the standard deviation of the species mole fractions averaged 7.8% for O/sub 2/ and 3.8% for N/sub 2/, based on 200 single-shot measurements. Measurements have been performed in a hydrogen-air flat-flame burner for fuel-lean and fuel-rich conditions. A preliminary comparison is shown between the fitted data and an adiabatic, equilibrium computation. For fuel-lean conditions, good agreement was found for temperature. Temperatures measured under fuel-rich conditions were about 50 K higher than the computation. Mole-fractions for N/sub 2/ agreed with the computation to within 3%. Measured O/sub 2/ mole fractions were systematically high while measured H/sub 2/ mole fractions were systematically low by 10-15% compared to the computation. For an equivalence ratio of 2.8, the standard deviation of 58 single-shot temperature measurements was 108 K, or 5.8%, and the standard deviations of H/sub 2/ and N/sub 2/ mole fractions were 9.8% and 3.8% of the measured values, respectively.
{"title":"N/sub 2//O/sub 2//H/sub 2/ dual-pump cars: validation experiments","authors":"S. O’Byrne, P. Danehy, A. Cutler","doi":"10.1109/ICIASF.2003.1274879","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274879","url":null,"abstract":"The dual-pump coherent anti-Stokes Raman spectroscopy (CARS) method is used to measure temperature and the relative species densities of N/sub 2/, O/sub 2/ and H/sub 2/ in two experiments. Average values and root-mean-square (RMS) deviations are determined. Mean temperature measurements in a furnace containing air between 300 and 1800 K agreed with thermocouple measurements within 26 K on average, while mean mole fractions agree to within 1.6% of the expected value. The temperature measurement standard deviation averaged 64 K while the standard deviation of the species mole fractions averaged 7.8% for O/sub 2/ and 3.8% for N/sub 2/, based on 200 single-shot measurements. Measurements have been performed in a hydrogen-air flat-flame burner for fuel-lean and fuel-rich conditions. A preliminary comparison is shown between the fitted data and an adiabatic, equilibrium computation. For fuel-lean conditions, good agreement was found for temperature. Temperatures measured under fuel-rich conditions were about 50 K higher than the computation. Mole-fractions for N/sub 2/ agreed with the computation to within 3%. Measured O/sub 2/ mole fractions were systematically high while measured H/sub 2/ mole fractions were systematically low by 10-15% compared to the computation. For an equivalence ratio of 2.8, the standard deviation of 58 single-shot temperature measurements was 108 K, or 5.8%, and the standard deviations of H/sub 2/ and N/sub 2/ mole fractions were 9.8% and 3.8% of the measured values, respectively.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"60 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":"127269093","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.2003.1274877
B. Sammler, A. Schroder, A. Arnott, D. Otter, J. Agocs, J. Kompenhans
An investigation of the vortex behaviour over a delta wing model under different angles of incidence and roll has been performed using Particle Image Velocimetry (PIV) under transonic conditions at DLR Gottingen, Germany. These tests are important for the understanding of the leading edge vortex behaviour which is responsible for enhanced lift forces and CFD validation. The investigation used a stereo PIV arrangement, with both cameras in forward-scatter mode. For high-quality stereo PIV measurements of the flow around such models under transonic conditions, many details had to be optimised, especially as the light sheets were positioned in the cross-plane to the freestream over the model. Parameters like light sheet thickness and displacement with a certain overlap had to be considered carefully. It was also necessary to observe the optical system by means of additional cameras, as the starting and stopping of the tunnel affected the light sheet. Fortunately, readjustment of its position whilst the wind tunnel was running could be done by remote control and optical tools outside the tunnel. This had to be done in connection with a special layout for the trigger sequence, as lengths of wires or optical fibres for the transmission of TTL pulses became relevant for delays in the order of microseconds. It was expected that strong centrifugal and axial accelerations would be present and tiny particles had to be used for seeding. It could be established that the vortex structure is dependent strongly on the direction of change of the roll angle. A very impressive phenomenon was the so-called busting of vortices, which was accompanied by rapidly-changing pressure distributions.
{"title":"Vortex investigation over a rolling delta wing model in transonic flow by stereo PIV measurements","authors":"B. Sammler, A. Schroder, A. Arnott, D. Otter, J. Agocs, J. Kompenhans","doi":"10.1109/ICIASF.2003.1274877","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274877","url":null,"abstract":"An investigation of the vortex behaviour over a delta wing model under different angles of incidence and roll has been performed using Particle Image Velocimetry (PIV) under transonic conditions at DLR Gottingen, Germany. These tests are important for the understanding of the leading edge vortex behaviour which is responsible for enhanced lift forces and CFD validation. The investigation used a stereo PIV arrangement, with both cameras in forward-scatter mode. For high-quality stereo PIV measurements of the flow around such models under transonic conditions, many details had to be optimised, especially as the light sheets were positioned in the cross-plane to the freestream over the model. Parameters like light sheet thickness and displacement with a certain overlap had to be considered carefully. It was also necessary to observe the optical system by means of additional cameras, as the starting and stopping of the tunnel affected the light sheet. Fortunately, readjustment of its position whilst the wind tunnel was running could be done by remote control and optical tools outside the tunnel. This had to be done in connection with a special layout for the trigger sequence, as lengths of wires or optical fibres for the transmission of TTL pulses became relevant for delays in the order of microseconds. It was expected that strong centrifugal and axial accelerations would be present and tiny particles had to be used for seeding. It could be established that the vortex structure is dependent strongly on the direction of change of the roll angle. A very impressive phenomenon was the so-called busting of vortices, which was accompanied by rapidly-changing pressure distributions.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"421 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":"126708383","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 : 2003-08-17DOI: 10.1109/ICIASF.2003.1274863
S. O’Byrne, P. Danehy, A. Houwing
Rotational temperature and velocity distributions have been measured across a hypersonic laminar flat-plate boundary layer, using planar laser-induced fluorescence. The measurements are compared to a finite-volume computation and a first-order boundary layer computation, assuming local similarity. Both computations produced similar temperature distributions and nearly identical velocity distributions. The disagreement between calculations is ascribed to the similarity solution not accounting for leading-edge displacement effects. The velocity measurements agreed to within the measurement uncertainty of 2% with both calculated distributions. The peak measured temperature was 200 K lower than the computed values. This discrepancy is tentatively ascribed to vibrational relaxation in the boundary layer.
{"title":"Plif temperature and velocity distributions in laminar hypersonic flat-plate flow","authors":"S. O’Byrne, P. Danehy, A. Houwing","doi":"10.1109/ICIASF.2003.1274863","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274863","url":null,"abstract":"Rotational temperature and velocity distributions have been measured across a hypersonic laminar flat-plate boundary layer, using planar laser-induced fluorescence. The measurements are compared to a finite-volume computation and a first-order boundary layer computation, assuming local similarity. Both computations produced similar temperature distributions and nearly identical velocity distributions. The disagreement between calculations is ascribed to the similarity solution not accounting for leading-edge displacement effects. The velocity measurements agreed to within the measurement uncertainty of 2% with both calculated distributions. The peak measured temperature was 200 K lower than the computed values. This discrepancy is tentatively ascribed to vibrational relaxation in the boundary layer.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"38 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2003-08-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122639683","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 : 2003-01-06DOI: 10.1109/ICIASF.2003.1274878
J. Grinstead, D. Driver, G. Raiche
Radial profile measurements of absolute atomic nitrogen density, temperature, and velocity using two photon laser-induced fluorescence in the NASA Ames Aerodynamic Heating Facility (AHF) are reported. Improvements in experimental technique and calibration procedure significantly reduced measurement uncertainties compared to previous efforts. The addition of a traversing system within the AHF test cabin permitted, for the first time, radial measurements of the three flow properties during a single arcjet run. Typical measurement uncertainties are 12% for absolute N density, 10-30% for temperature, and 3% for velocity. Details of the measurement technique, optical configuration, data analysis procedures, and results of two repeated demonstration runs in air/Ar flows are presented.
{"title":"Radial profiles of arcjet flow properties measured with laser-induced fluorescence of atomic nitrogen","authors":"J. Grinstead, D. Driver, G. Raiche","doi":"10.1109/ICIASF.2003.1274878","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274878","url":null,"abstract":"Radial profile measurements of absolute atomic nitrogen density, temperature, and velocity using two photon laser-induced fluorescence in the NASA Ames Aerodynamic Heating Facility (AHF) are reported. Improvements in experimental technique and calibration procedure significantly reduced measurement uncertainties compared to previous efforts. The addition of a traversing system within the AHF test cabin permitted, for the first time, radial measurements of the three flow properties during a single arcjet run. Typical measurement uncertainties are 12% for absolute N density, 10-30% for temperature, and 3% for velocity. Details of the measurement technique, optical configuration, data analysis procedures, and results of two repeated demonstration runs in air/Ar flows are presented.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"81 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2003-01-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127156639","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 : 1900-01-01DOI: 10.1109/ICIASF.2003.1274868
Jeffrey D Jordan, A. N. Watkins, Gary A Fleming, B. Leighty, Richard J Schwartz, J. L. Ingram, K. D. Grinstead, D. M. Oglesby, Charles Tyler
This paper discusses recent developments in rapid technology assessment resulting from an active collaboration between researchers at the Air Force Research Laboratory (AFRL) at Wright Patterson Air Force Base (WPAFB) and the NASA Langley Research Center (LaRC). This program targets the unified development and deployment of global measurement technologies coupled with a virtual diagnostic interface to enable the comparative evaluation of experimental and computational results. Continuing efforts focus on the development of seamless data translation methods to enable integration of data sets of disparate file format in a common platform. Results from a successful low-speed wind tunnel test at WPAFB in which global surface pressure distributions were acquired simultaneously with model deformation and geometry measurements are discussed and comparatively evaluated with numerical simulations. Intensity- and lifetime-based pressure-sensitive paint (PSP) and projection moire interferometry (PMI) results are presented within the context of rapid technology assessment to enable simulation-based R&D.
{"title":"Rapid technology assessment via unified deployment of global optical and virtual diagnostics","authors":"Jeffrey D Jordan, A. N. Watkins, Gary A Fleming, B. Leighty, Richard J Schwartz, J. L. Ingram, K. D. Grinstead, D. M. Oglesby, Charles Tyler","doi":"10.1109/ICIASF.2003.1274868","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274868","url":null,"abstract":"This paper discusses recent developments in rapid technology assessment resulting from an active collaboration between researchers at the Air Force Research Laboratory (AFRL) at Wright Patterson Air Force Base (WPAFB) and the NASA Langley Research Center (LaRC). This program targets the unified development and deployment of global measurement technologies coupled with a virtual diagnostic interface to enable the comparative evaluation of experimental and computational results. Continuing efforts focus on the development of seamless data translation methods to enable integration of data sets of disparate file format in a common platform. Results from a successful low-speed wind tunnel test at WPAFB in which global surface pressure distributions were acquired simultaneously with model deformation and geometry measurements are discussed and comparatively evaluated with numerical simulations. Intensity- and lifetime-based pressure-sensitive paint (PSP) and projection moire interferometry (PMI) results are presented within the context of rapid technology assessment to enable simulation-based R&D.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"11243 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124038655","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 : 1900-01-01DOI: 10.1109/ICIASF.2003.1274843
The following topics are dealt with: flow field diagnostic tools; PSP/TSP measurement methods; model positioning and deformation; measurement in high temperature environments; analogue and digital acquisition and analysis techniques; testing techniques and test environments; mechanical, electrical and optical measurement devices; spectroscopic methods; cryogenic wind tunnels; particle image velocimetry (PIV); measurement of vibration and deformations; skin friction measurement; vortex detection.
{"title":"20th International Congress on Instrumentation in Aerospace Simulation Facilities (IEEE Cat. No.03CH37501)","authors":"","doi":"10.1109/ICIASF.2003.1274843","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274843","url":null,"abstract":"The following topics are dealt with: flow field diagnostic tools; PSP/TSP measurement methods; model positioning and deformation; measurement in high temperature environments; analogue and digital acquisition and analysis techniques; testing techniques and test environments; mechanical, electrical and optical measurement devices; spectroscopic methods; cryogenic wind tunnels; particle image velocimetry (PIV); measurement of vibration and deformations; skin friction measurement; vortex detection.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"329 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134158977","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}
京公网安备 11010802042870号
京ICP备2023020795号-1
扫码关注我们
求助内容：
应助结果提醒方式：