Pub Date : 2003-08-25DOI: 10.1109/ICIASF.2003.1274864
D. Coulton, M. Lambourne
In recent years significant effort has been expended by the relevant systems and instrumentation engineers at the Aircraft Research Association to produce new and novel instrumentation/control systems in order to meet customer demands for higher productivity, reduced time-scales and increased flexibility. One such development has been the design, development and manufacture of a new generation system for the acquisition and monitoring of data from high speed pressure scanners. The paper details the reasons why the ARA decided to replace its existing commercially available data acquisition system with an alternative in-house design. The advantages that are being seen through the use of the new system are expanded on and the design philosophy explained. The design of the new data acquisition system for pressures recorded by high speed electronic scanners has achieved all its objectives and is easily reproducible at low cost. Several such systems are now in general usage in the various facilities owned by the ARA and others are planned. One major advantage of the in-house design being that future software modifications can easily be made in order to meet changing customer needs.
{"title":"A new data acquisition system for high speed pressure scanners","authors":"D. Coulton, M. Lambourne","doi":"10.1109/ICIASF.2003.1274864","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274864","url":null,"abstract":"In recent years significant effort has been expended by the relevant systems and instrumentation engineers at the Aircraft Research Association to produce new and novel instrumentation/control systems in order to meet customer demands for higher productivity, reduced time-scales and increased flexibility. One such development has been the design, development and manufacture of a new generation system for the acquisition and monitoring of data from high speed pressure scanners. The paper details the reasons why the ARA decided to replace its existing commercially available data acquisition system with an alternative in-house design. The advantages that are being seen through the use of the new system are expanded on and the design philosophy explained. The design of the new data acquisition system for pressures recorded by high speed electronic scanners has achieved all its objectives and is easily reproducible at low cost. Several such systems are now in general usage in the various facilities owned by the ARA and others are planned. One major advantage of the in-house design being that future software modifications can easily be made in order to meet changing customer needs.","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":"122633013","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.2003.1274862
M. Wernet, W. T. John, J. Bridges
Digital Particle Image Velocimetry (DPIV) has developed into a production grade research tool, which is being used at NASA GRC to improve our understanding of the decay of turbulence in jet flows - a critical element for understanding the acoustic properties of the flow. Two independent DPIV systems were installed in the GRC Small Hot Jet Acoustic Rig (SHJAR), enabling correlations in time and space. The data reported here were collected at a Mach number of 0.9 and temperature ratios of 0.86 and 2.7. The DPIV systems were mounted on independent traverse systems to facilitate image acquisition over a range of time delays and spatial separations. The collected DPIV data illustrate the differences in first order flow properties of cold and hot jets. The velocity fields from the two DPIV systems were then cross-correlated to determine the degree of correlation remaining in the flow as the downstream convection distance was increased. Increasing the physical spacing and time delays between the DPIV system acquisitions provided velocity fields containing information on the decay of turbulence in the flow. The DPIV results show that there are significant differences in the mean axial velocity component and turbulent kinetic energy for cold and hot flows at the same Mach number. The data also illustrate the decay of turbulence along the jet axis as revealed by the cross-correlations of the phase delayed and spatially separated DPIV vector maps.
{"title":"Dual PIV systems for space-time correlations in hot jets","authors":"M. Wernet, W. T. John, J. Bridges","doi":"10.1109/ICIASF.2003.1274862","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274862","url":null,"abstract":"Digital Particle Image Velocimetry (DPIV) has developed into a production grade research tool, which is being used at NASA GRC to improve our understanding of the decay of turbulence in jet flows - a critical element for understanding the acoustic properties of the flow. Two independent DPIV systems were installed in the GRC Small Hot Jet Acoustic Rig (SHJAR), enabling correlations in time and space. The data reported here were collected at a Mach number of 0.9 and temperature ratios of 0.86 and 2.7. The DPIV systems were mounted on independent traverse systems to facilitate image acquisition over a range of time delays and spatial separations. The collected DPIV data illustrate the differences in first order flow properties of cold and hot jets. The velocity fields from the two DPIV systems were then cross-correlated to determine the degree of correlation remaining in the flow as the downstream convection distance was increased. Increasing the physical spacing and time delays between the DPIV system acquisitions provided velocity fields containing information on the decay of turbulence in the flow. The DPIV results show that there are significant differences in the mean axial velocity component and turbulent kinetic energy for cold and hot flows at the same Mach number. The data also illustrate the decay of turbulence along the jet axis as revealed by the cross-correlations of the phase delayed and spatially separated DPIV vector maps.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"52 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":"133558845","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.2003.1274867
H. Kato, S. Watanabe, N. Kondo, S. Saito
Stereoscopic PIV technique was applied to the blade tip vortices of helicopter model in order to acquire the information that is needed by the understanding of the tip vortex structure during the blade-vortex interaction (BVI). The measurements have been performed in the NAL 6.5 m/spl times/5.5 m low-speed wind tunnel. The test blades have a rectangular tip and twisted NACA 0012 profile. The model was operated in the condition of maximum blade-vortex interaction (BVI) noise. The stereoscopic PIV system consisted of two CCD cameras and a double pulse Nd:YAG laser (1 J/Pulse, 532 nm). PIV image data were recorded at three positions and two azimuthal angles on the advancing side. As a result, three-component velocity fields of blade tip vortices were obtained from the PIV measurements, and location of the vortex relative to the rotor plane, the vortex core size, and the peak to peak velocity were derived. Furthermore, qualitatively valid value of turbulence intensity can be measured using by the PIV system. It was found that due to the vortex wander effects, average flowfields computed in a coordinate moving with the vortex are more accurate in terms of the derived vortex parameters than simple ensemble average flowfields.
{"title":"Application of stereoscopic PIV to helicopter rotor blade tip vortices","authors":"H. Kato, S. Watanabe, N. Kondo, S. Saito","doi":"10.1109/ICIASF.2003.1274867","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274867","url":null,"abstract":"Stereoscopic PIV technique was applied to the blade tip vortices of helicopter model in order to acquire the information that is needed by the understanding of the tip vortex structure during the blade-vortex interaction (BVI). The measurements have been performed in the NAL 6.5 m/spl times/5.5 m low-speed wind tunnel. The test blades have a rectangular tip and twisted NACA 0012 profile. The model was operated in the condition of maximum blade-vortex interaction (BVI) noise. The stereoscopic PIV system consisted of two CCD cameras and a double pulse Nd:YAG laser (1 J/Pulse, 532 nm). PIV image data were recorded at three positions and two azimuthal angles on the advancing side. As a result, three-component velocity fields of blade tip vortices were obtained from the PIV measurements, and location of the vortex relative to the rotor plane, the vortex core size, and the peak to peak velocity were derived. Furthermore, qualitatively valid value of turbulence intensity can be measured using by the PIV system. It was found that due to the vortex wander effects, average flowfields computed in a coordinate moving with the vortex are more accurate in terms of the derived vortex parameters than simple ensemble average flowfields.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"29 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":"115183426","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.2003.1274871
Chen De-rong, Liu Xiang-bin
How to get enough shock environment information with limited system capacity is a key problem in space vehicle telemetry. In this paper, an airborne shock response spectra analyzer is developed based on FPGA which can real time calculate peak response spectra on board and then sending it to the ground station instead of the signal form three-axis accelerometer during the flight test. Flight test shows the analyzer can effectively compress the shock data and get enough shock environment information with limited system capacity. Moreover, the compression ratio of shock data can be flexibly adjusted according to the telemetry system capacity and real-time requirement of measurement, and some design parameters can be changed on-line. Therefore the analyzer has good applicability.
{"title":"Airborne shock response spectra analyzer based on FPGA","authors":"Chen De-rong, Liu Xiang-bin","doi":"10.1109/ICIASF.2003.1274871","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274871","url":null,"abstract":"How to get enough shock environment information with limited system capacity is a key problem in space vehicle telemetry. In this paper, an airborne shock response spectra analyzer is developed based on FPGA which can real time calculate peak response spectra on board and then sending it to the ground station instead of the signal form three-axis accelerometer during the flight test. Flight test shows the analyzer can effectively compress the shock data and get enough shock environment information with limited system capacity. Moreover, the compression ratio of shock data can be flexibly adjusted according to the telemetry system capacity and real-time requirement of measurement, and some design parameters can be changed on-line. Therefore the analyzer has good applicability.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"1 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":"129852008","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.2003.1274892
T.J. Moller, J. Ortmanns, M. El Khalfaoui, R. Radespiel
The low speed model wind tunnel (MUB) has been transferred from the DNW-NWB to the Institute of Fluid mechanics of the TU Braunschweig (ISM). The wind tunnel is a closed return atmospheric wind tunnel with three different test sections. Two of them are closed and one is an open test section. The wind tunnel has been improved by a new closed test section with a cross section of 1.3/spl times/1.3 m. A maximum speed of 60 m/s is achieved with this test section. The second closed test section has a cross section of 0.8/spl times/0.8 m which allows velocities up to 140 m/s. Another option is an open test section with a jet that measures 1.3 m. The maximum Reynolds-Number is 7.5*10/sup 5/. The major improvement is the addition of a heat exchanger, which allows to keep the temperature of the flow constant. As a research facility the tunnel incorporates extensive flow measurement instrumentation including probe traversing and particle image velocimetry (PIV) systems. The new test section allows optimal and flexible optical access as well as the usage of conventional measurement technique.
{"title":"The new low speed wind tunnel of the TU Braunschweig","authors":"T.J. Moller, J. Ortmanns, M. El Khalfaoui, R. Radespiel","doi":"10.1109/ICIASF.2003.1274892","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274892","url":null,"abstract":"The low speed model wind tunnel (MUB) has been transferred from the DNW-NWB to the Institute of Fluid mechanics of the TU Braunschweig (ISM). The wind tunnel is a closed return atmospheric wind tunnel with three different test sections. Two of them are closed and one is an open test section. The wind tunnel has been improved by a new closed test section with a cross section of 1.3/spl times/1.3 m. A maximum speed of 60 m/s is achieved with this test section. The second closed test section has a cross section of 0.8/spl times/0.8 m which allows velocities up to 140 m/s. Another option is an open test section with a jet that measures 1.3 m. The maximum Reynolds-Number is 7.5*10/sup 5/. The major improvement is the addition of a heat exchanger, which allows to keep the temperature of the flow constant. As a research facility the tunnel incorporates extensive flow measurement instrumentation including probe traversing and particle image velocimetry (PIV) systems. The new test section allows optimal and flexible optical access as well as the usage of conventional measurement technique.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"18 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":"125662104","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.2003.1274852
W. Becker, R. Rebstock, S. Loose, H. Richard, M. Raffel
With the increasing speed of new generations of high speed trains their geometry is becoming increasingly important and the aerodynamic design has to be considered in greater detail. Particularly the train's crosswind sensitivity is a problematic in nature and has to be considered accordingly. Earlier measurements by means of particle image velocimetry (PIV) in smaller wind tunnels showed the presence of a strong vortex at the leeward side of the model. To address this issue, PIV tests and also force measurement were made on a generic high speed train model. The scaling factor of the model was 1:10. Contour and geometric ratios are nearly similar to the German ICE1 train. For the investigation of force and torque data the ICE-Model was adapted to the half model-balance of cryogenic wind tunnel Cologne (KKK). These results are presented herein. The boundary layer thickness is an essential parameter influencing the measurements. In case of semi-span model tests this problem is solved by using a peniche (standoff) between support and fuselage. The model-ground plane distance was varied in order to determine it's influence on the ICE-model measurements.
{"title":"Tests for vehicle aerodynamics in the cryogenic wind tunnel Cologne DNW-KKK","authors":"W. Becker, R. Rebstock, S. Loose, H. Richard, M. Raffel","doi":"10.1109/ICIASF.2003.1274852","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274852","url":null,"abstract":"With the increasing speed of new generations of high speed trains their geometry is becoming increasingly important and the aerodynamic design has to be considered in greater detail. Particularly the train's crosswind sensitivity is a problematic in nature and has to be considered accordingly. Earlier measurements by means of particle image velocimetry (PIV) in smaller wind tunnels showed the presence of a strong vortex at the leeward side of the model. To address this issue, PIV tests and also force measurement were made on a generic high speed train model. The scaling factor of the model was 1:10. Contour and geometric ratios are nearly similar to the German ICE1 train. For the investigation of force and torque data the ICE-Model was adapted to the half model-balance of cryogenic wind tunnel Cologne (KKK). These results are presented herein. The boundary layer thickness is an essential parameter influencing the measurements. In case of semi-span model tests this problem is solved by using a peniche (standoff) between support and fuselage. The model-ground plane distance was varied in order to determine it's influence on the ICE-model measurements.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"1 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":"129309182","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.2003.1274869
C. Tyler
The Air Force Research Laboratory Air Vehicles Directorate (AFRL/VA) initiated a joint Computational Fluid Dynamics/Experimental Fluid Dynamics (CFD/EFD) test program to investigate and analyze the flow field of a lambda wing-body aerodynamic configuration. The test program involves a multitude of cross-functional specialties, ranging from experimental testing to computational resources to state-of-the-art material manufacturing techniques. A preliminary computational grid and subsequent analysis was performed to provide estimated loads and moments necessary for proper manufacturing of a wind tunnel model. The test program used rapid prototyping manufacturing techniques to fabricate a model for ground testing; implemented innovative, non-intrusive measurement techniques in ground test; and compared CFD with experimental data acquired from ground tests. The measurement techniques employed include standard force and moment measurements as well as global optical diagnostic techniques such as intensity- and lifetime-based pressure sensitive paint, projection Moire interferometry, and Doppler global velocimetry. The results obtained from these various measurement techniques will be used for comparison with CFD results. To achieve better correlation between the wind tunnel results and the CFD results, the computational grids will include the wind tunnel structure and appropriate mounting hardware. A comparison of the results from this "virtual" wind tunnel will be made to the results from the actual wind tunnel. Computational results include a variation of multiple trailing-edge flap configurations, angles of attack, and freestream Mach number conditions achievable in the subsonic aerodynamic research laboratory. AFRL researchers acquired a better understanding of the multiple disciplines: rapid prototyping, various measurement techniques, and CFD. It can be concluded that increased communication and comparison between experimental and computational fluid diagnostics was achieved successfully. Joint CFD and EFD test programs will continue to be developed and improved.
{"title":"A joint computational fluid dynamics and experimental fluid dynamics program","authors":"C. Tyler","doi":"10.1109/ICIASF.2003.1274869","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274869","url":null,"abstract":"The Air Force Research Laboratory Air Vehicles Directorate (AFRL/VA) initiated a joint Computational Fluid Dynamics/Experimental Fluid Dynamics (CFD/EFD) test program to investigate and analyze the flow field of a lambda wing-body aerodynamic configuration. The test program involves a multitude of cross-functional specialties, ranging from experimental testing to computational resources to state-of-the-art material manufacturing techniques. A preliminary computational grid and subsequent analysis was performed to provide estimated loads and moments necessary for proper manufacturing of a wind tunnel model. The test program used rapid prototyping manufacturing techniques to fabricate a model for ground testing; implemented innovative, non-intrusive measurement techniques in ground test; and compared CFD with experimental data acquired from ground tests. The measurement techniques employed include standard force and moment measurements as well as global optical diagnostic techniques such as intensity- and lifetime-based pressure sensitive paint, projection Moire interferometry, and Doppler global velocimetry. The results obtained from these various measurement techniques will be used for comparison with CFD results. To achieve better correlation between the wind tunnel results and the CFD results, the computational grids will include the wind tunnel structure and appropriate mounting hardware. A comparison of the results from this \"virtual\" wind tunnel will be made to the results from the actual wind tunnel. Computational results include a variation of multiple trailing-edge flap configurations, angles of attack, and freestream Mach number conditions achievable in the subsonic aerodynamic research laboratory. AFRL researchers acquired a better understanding of the multiple disciplines: rapid prototyping, various measurement techniques, and CFD. It can be concluded that increased communication and comparison between experimental and computational fluid diagnostics was achieved successfully. Joint CFD and EFD test programs will continue to be developed and improved.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"86 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":"128643351","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.2003.1274884
J. Trolinger
This paper describes digital, photonic, two-dimensional, dynamic-wavefront sensing methods for flow diagnostics. A system described herein employs a 532 nm diode pumped solid state laser to produce quantitative, fully reduced phase maps at virtually real time acquisition rates to evaluate flows in wind tunnel facilities. This is done using instantaneous electronic phase shifting interferometry methods. Because measurements are instantaneous and not compared to a stored reference data point, the instrument is not vulnerable to vibrations and other environmental effects found in test facilities. A flow field can be analyzed quantitatively by measuring its effect on a traversing optical wavefront if the wavefront sensor can respond as fast as the field changes. Conversely, the effect of flow fields on optical imaging gives rise to the field of aero-optics, and the wavefront distortion and correction are of principal interest. Developments in aero-optics, electro-optics and image processing in general have led to more advanced variations and applications of interferometry improving speed, sensitivity, automation, and robustness. Video recording and new methods for performing high-speed interferometric wavefront and flow diagnostics electronically to speed up the process are described.
{"title":"High speed digital wavefront sensing for aero-optics and flow diagnostics","authors":"J. Trolinger","doi":"10.1109/ICIASF.2003.1274884","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274884","url":null,"abstract":"This paper describes digital, photonic, two-dimensional, dynamic-wavefront sensing methods for flow diagnostics. A system described herein employs a 532 nm diode pumped solid state laser to produce quantitative, fully reduced phase maps at virtually real time acquisition rates to evaluate flows in wind tunnel facilities. This is done using instantaneous electronic phase shifting interferometry methods. Because measurements are instantaneous and not compared to a stored reference data point, the instrument is not vulnerable to vibrations and other environmental effects found in test facilities. A flow field can be analyzed quantitatively by measuring its effect on a traversing optical wavefront if the wavefront sensor can respond as fast as the field changes. Conversely, the effect of flow fields on optical imaging gives rise to the field of aero-optics, and the wavefront distortion and correction are of principal interest. Developments in aero-optics, electro-optics and image processing in general have led to more advanced variations and applications of interferometry improving speed, sensitivity, automation, and robustness. Video recording and new methods for performing high-speed interferometric wavefront and flow diagnostics electronically to speed up the process are described.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"158 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":"116118207","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.2003.1274888
Y. Sakamura, T. Suzuki, M. Matsumoto
The aim of the present work is to demonstrate the feasibility of a porous pressure-sensitive paint (PSP) for time-resolved surface pressure measurements in unsteady flows. The porous PSP was composed of bathophenanthroline ruthenium(II) complex, Ru(Ph/sub 2/-phen), and a silica-gel thin-layer chromatography (TLC) aluminum plate. The dynamic response of the porous PSP was characterized by applying it to rapid pressure changes generated by a shock wave and a pulse-jet. The porous PSP was then applied to the transient starting process of flow in a two-dimensional Laval nozzle with a fast-framing complementary metal oxide semiconductor (CMOS) camera. It has been shown that the present imaging system can well capture a rapid flow evolution on the order of kilohertz such as shock wave motion in the nozzle during its starting process.
{"title":"Surface pressure distribution imaging at frame rates over 1 kHz using porous pressure-sensitive paint","authors":"Y. Sakamura, T. Suzuki, M. Matsumoto","doi":"10.1109/ICIASF.2003.1274888","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274888","url":null,"abstract":"The aim of the present work is to demonstrate the feasibility of a porous pressure-sensitive paint (PSP) for time-resolved surface pressure measurements in unsteady flows. The porous PSP was composed of bathophenanthroline ruthenium(II) complex, Ru(Ph/sub 2/-phen), and a silica-gel thin-layer chromatography (TLC) aluminum plate. The dynamic response of the porous PSP was characterized by applying it to rapid pressure changes generated by a shock wave and a pulse-jet. The porous PSP was then applied to the transient starting process of flow in a two-dimensional Laval nozzle with a fast-framing complementary metal oxide semiconductor (CMOS) camera. It has been shown that the present imaging system can well capture a rapid flow evolution on the order of kilohertz such as shock wave motion in the nozzle during its starting process.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"260 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":"114329842","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.2003.1274854
Y. Iijima, Y. Egami, A. Nishizawa, K. Asai, U. Fey, R. Engler
In this paper, a new temperature-sensitive paint (TSP) technique for boundary-layer transition detection in a production-type large cryogenic wind tunnel is present. The formulation of Ru(trpy) based TSP system has been optimized in terms of luminescence intensity and robustness. The optimum dye-binder-solvent combination has been determined through systematic sample tests. A new binder has been introduced and the resulting coating was found free from cracking at cryogenic temperatures. This is contrary to the silicone-based pervious cryogenic TSP that are subject to micro cracks at reduced temperatures. The new TSP can meet the root-mean-square roughness requirement less than 0.15 /spl mu/m. Experiments in the NAL 0.1-m transonic cryogenic wind tunnel have shown that transition occurs earlier on the unpolished surface than the polished surface, although the roughness value itself increasing by polishing. This suggests that the waviness of the coating could affect on the growth of instability in boundary layers.
{"title":"Optimization of temperature-sensitive paint formulation for large-scale cryogenic wind tunnels","authors":"Y. Iijima, Y. Egami, A. Nishizawa, K. Asai, U. Fey, R. Engler","doi":"10.1109/ICIASF.2003.1274854","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274854","url":null,"abstract":"In this paper, a new temperature-sensitive paint (TSP) technique for boundary-layer transition detection in a production-type large cryogenic wind tunnel is present. The formulation of Ru(trpy) based TSP system has been optimized in terms of luminescence intensity and robustness. The optimum dye-binder-solvent combination has been determined through systematic sample tests. A new binder has been introduced and the resulting coating was found free from cracking at cryogenic temperatures. This is contrary to the silicone-based pervious cryogenic TSP that are subject to micro cracks at reduced temperatures. The new TSP can meet the root-mean-square roughness requirement less than 0.15 /spl mu/m. Experiments in the NAL 0.1-m transonic cryogenic wind tunnel have shown that transition occurs earlier on the unpolished surface than the polished surface, although the roughness value itself increasing by polishing. This suggests that the waviness of the coating could affect on the growth of instability in boundary layers.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"292 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":"114720177","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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