Pub Date : 2003-08-25DOI: 10.1109/ICIASF.2003.1274855
U. Fey, R. Engler, Y. Egami, Y. Iijima, Keisuke Asai, Ulrich. Jansen, J. Quest
The identification of laminar-turbulent boundary layer transition on wind tunnel models provides essential data for modern wing design. However, simulating true flight Reynolds numbers with scaled models requires the use of cryogenic wind tunnels. Transition detection in 'warm' wind tunnels can be realized using commercially available IR cameras. In parallel, the temperature sensitive paint (TSP) technique is well established as an additional tool. In cryogenic testing, IR imaging becomes more difficult because of the reduction in radiated energy and the shift to longer wavelengths. Therefore, the TSP technique has become a promising alternative here. However, applying temperature sensitive paint in a large-scale cryogenic wind tunnel like the European Transonic Wind tunnel (ETW) needs specific modification of existing TSP formulations. Cooperative tests in the ETW therefore were performed by DLR and NAL (Japan). In these measurements, NAL's paint and DLR's mobile PSP/TSP system for data acquisition and evaluation were used. Some efforts were made to adapt the system to specific conditions given at the ETW wind tunnel. So for the first time it was successfully realized to perform a TSP luminescent paint test at cryogenic temperatures in a commercial wind tunnel.
{"title":"Transition detection by temperature sensitive paint at cryogenic temperatures in the European Transonic Wind tunnel (ETW)","authors":"U. Fey, R. Engler, Y. Egami, Y. Iijima, Keisuke Asai, Ulrich. Jansen, J. Quest","doi":"10.1109/ICIASF.2003.1274855","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274855","url":null,"abstract":"The identification of laminar-turbulent boundary layer transition on wind tunnel models provides essential data for modern wing design. However, simulating true flight Reynolds numbers with scaled models requires the use of cryogenic wind tunnels. Transition detection in 'warm' wind tunnels can be realized using commercially available IR cameras. In parallel, the temperature sensitive paint (TSP) technique is well established as an additional tool. In cryogenic testing, IR imaging becomes more difficult because of the reduction in radiated energy and the shift to longer wavelengths. Therefore, the TSP technique has become a promising alternative here. However, applying temperature sensitive paint in a large-scale cryogenic wind tunnel like the European Transonic Wind tunnel (ETW) needs specific modification of existing TSP formulations. Cooperative tests in the ETW therefore were performed by DLR and NAL (Japan). In these measurements, NAL's paint and DLR's mobile PSP/TSP system for data acquisition and evaluation were used. Some efforts were made to adapt the system to specific conditions given at the ETW wind tunnel. So for the first time it was successfully realized to perform a TSP luminescent paint test at cryogenic temperatures in a commercial wind tunnel.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"27 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":"121964527","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.2003.1274851
A. Arnott, G. Schneider, Klaus-Peter Neitzke, J. Agocs, B. Sammler, A. Schroder, J. Kompenhans
Experiments using multi-window, particle image velocimetry (PIV) were performed in the low-speed wind tunnel of Airbus Bremen, Germany, over a two-dimensional, slat/wing/flap model in a high-lift configuration. For this, a system for acquiring PIV data from multiple cameras simultaneously was devised and installed underneath the LSWT. The PIV experiments were performed at the mid-span of the model, for incidences of 12/spl deg/, 17.5/spl deg/ & 19/spl deg/. Nearly 5000 PIV images were obtained during the tests, the images capturing the flowfields from the slat wake, slat/wing gap, flow mixing over the main wing, wing/flap-gap and wing wake. The analysis of the results reveals that such a technique is a viable and valuable tool for industrial wind tunnel tests, with high quality data showing the unsteady nature of the slat wake and slat gap flow with distance downstream and unsteady flow separation over the flap.
{"title":"Multi-window PIV for high-lift measurements","authors":"A. Arnott, G. Schneider, Klaus-Peter Neitzke, J. Agocs, B. Sammler, A. Schroder, J. Kompenhans","doi":"10.1109/ICIASF.2003.1274851","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274851","url":null,"abstract":"Experiments using multi-window, particle image velocimetry (PIV) were performed in the low-speed wind tunnel of Airbus Bremen, Germany, over a two-dimensional, slat/wing/flap model in a high-lift configuration. For this, a system for acquiring PIV data from multiple cameras simultaneously was devised and installed underneath the LSWT. The PIV experiments were performed at the mid-span of the model, for incidences of 12/spl deg/, 17.5/spl deg/ & 19/spl deg/. Nearly 5000 PIV images were obtained during the tests, the images capturing the flowfields from the slat wake, slat/wing gap, flow mixing over the main wing, wing/flap-gap and wing wake. The analysis of the results reveals that such a technique is a viable and valuable tool for industrial wind tunnel tests, with high quality data showing the unsteady nature of the slat wake and slat gap flow with distance downstream and unsteady flow separation over the flap.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"49 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":"131623474","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.2003.1274876
V. Zudov, A. Shevchenko, P. Tretyakov
Experimental investigation of a longitudinal vortex/normal shock interaction is conducted at Mach numbers of 3, 4 and 6. The fields of total pressures in the core of a longitudinal vortex and its neighbourhood are obtained. The optical visualization of flow structure in an interaction region is executed. The strongly unsteady character of interaction process is detected. The numerical modeling of the streamwise vortex interaction with the oblique and normal shock wave was solved using three-dimension unsteady Euler and Navier - Stokes equations. Results of an experimental study of the region of interaction of a plane shock wave arising in the flow around a wedge and an axisymmetric shock wave formed by counterflow injection with a jet wake formed by co-current injection of gases (H2, air, Ar). Three interaction modes are distinguished, depending on the gas-jet parameters: strong interaction with a subsonic velocity in the wake, moderate interaction with the formation of a subsonic flow region bounded by the shock wave whose shape is close to conical, and neutral interaction where the dynamic pressure in the jet is sufficient to overcome the pressure difference on the shock wave.
{"title":"The interaction of streamwise vortex with a shock wave","authors":"V. Zudov, A. Shevchenko, P. Tretyakov","doi":"10.1109/ICIASF.2003.1274876","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274876","url":null,"abstract":"Experimental investigation of a longitudinal vortex/normal shock interaction is conducted at Mach numbers of 3, 4 and 6. The fields of total pressures in the core of a longitudinal vortex and its neighbourhood are obtained. The optical visualization of flow structure in an interaction region is executed. The strongly unsteady character of interaction process is detected. The numerical modeling of the streamwise vortex interaction with the oblique and normal shock wave was solved using three-dimension unsteady Euler and Navier - Stokes equations. Results of an experimental study of the region of interaction of a plane shock wave arising in the flow around a wedge and an axisymmetric shock wave formed by counterflow injection with a jet wake formed by co-current injection of gases (H2, air, Ar). Three interaction modes are distinguished, depending on the gas-jet parameters: strong interaction with a subsonic velocity in the wake, moderate interaction with the formation of a subsonic flow region bounded by the shock wave whose shape is close to conical, and neutral interaction where the dynamic pressure in the jet is sufficient to overcome the pressure difference on the shock wave.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"34 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":"131920751","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.2003.1274890
Junnai Zhai, R. Rebstock
The design and optimization of 2D profiles play a decisive role in the enhancement of the overall performance of an aircraft. Though there are a large series of profiles available with detailed test data, for a high performance aircraft the profiles must be specially designed. Thus there is a need for the 2D profile testing in wind tunnels at high Reynolds numbers. In order to meet this need, the cryogenic wind tunnel Cologne (DNW-KKK) has developed the 2D profile measuring technique for cryogenic conditions. In the first 2D test setup the profile is only driven at one end by a servomotor. This can not prevent the profile from twisting under the thermal and aerodynamic load. The 2D support is thus modified from a one motor drive system into a synchronized two motor drive systems. Boundary layer blowing is used in DNW-KKK to control the boundary layer at the intersection areas between the profile and the tunnel walls, so that the flow around the profile is two dimensional. Besides the pressure measurement, infrared thermograph, laser velocimetry and dynamic measurement using kulite have been performed. With these techniques the requirements of 2D measurements can be met. For a better preparation of the profile tests and wall correction in our wind tunnel, we have investigated the characteristics of the profiles with numerical methods before the test. We have computed the polar under the two different far field boundary conditions: solid walls and infinite flow. The difference of these two polar is then the wind tunnel wall effect. We have compared this difference with the effect calculated by our wall correction method. The comparison shows that the wall correction method used is correct. Up to now various 2D profiles, such as laminar, high lift, high speed profiles and profiles for windmills have been tested in DNW-KKK. The repeatability of the measurements is very high.
{"title":"Advancement of 2D profile testing at high Reynolds number in the cryogenic wind tunnel Cologne","authors":"Junnai Zhai, R. Rebstock","doi":"10.1109/ICIASF.2003.1274890","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274890","url":null,"abstract":"The design and optimization of 2D profiles play a decisive role in the enhancement of the overall performance of an aircraft. Though there are a large series of profiles available with detailed test data, for a high performance aircraft the profiles must be specially designed. Thus there is a need for the 2D profile testing in wind tunnels at high Reynolds numbers. In order to meet this need, the cryogenic wind tunnel Cologne (DNW-KKK) has developed the 2D profile measuring technique for cryogenic conditions. In the first 2D test setup the profile is only driven at one end by a servomotor. This can not prevent the profile from twisting under the thermal and aerodynamic load. The 2D support is thus modified from a one motor drive system into a synchronized two motor drive systems. Boundary layer blowing is used in DNW-KKK to control the boundary layer at the intersection areas between the profile and the tunnel walls, so that the flow around the profile is two dimensional. Besides the pressure measurement, infrared thermograph, laser velocimetry and dynamic measurement using kulite have been performed. With these techniques the requirements of 2D measurements can be met. For a better preparation of the profile tests and wall correction in our wind tunnel, we have investigated the characteristics of the profiles with numerical methods before the test. We have computed the polar under the two different far field boundary conditions: solid walls and infinite flow. The difference of these two polar is then the wind tunnel wall effect. We have compared this difference with the effect calculated by our wall correction method. The comparison shows that the wall correction method used is correct. Up to now various 2D profiles, such as laminar, high lift, high speed profiles and profiles for windmills have been tested in DNW-KKK. The repeatability of the measurements is very high.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"34 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":"116528663","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.2003.1274865
E. Schulein
The utilization of image acquisition, image processing and skin friction computations has been developed to support skin friction measurements at the Ludwieg-tube facility at DLR. Verification of the oil-film-interferometry technique with analytical tests at different flows with given shear stress distributions showed its advantages and handicaps for skin friction measurements in 3D gradient flows. The abilities of the thin oil film technique with its application in a short duration wind tunnel are demonstrated on some 2D and 3D shock wave / turbulent boundary layer interaction flows.
{"title":"Optical skin friction measurements in the short-duration Ludwieg tube facility","authors":"E. Schulein","doi":"10.1109/ICIASF.2003.1274865","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274865","url":null,"abstract":"The utilization of image acquisition, image processing and skin friction computations has been developed to support skin friction measurements at the Ludwieg-tube facility at DLR. Verification of the oil-film-interferometry technique with analytical tests at different flows with given shear stress distributions showed its advantages and handicaps for skin friction measurements in 3D gradient flows. The abilities of the thin oil film technique with its application in a short duration wind tunnel are demonstrated on some 2D and 3D shock wave / turbulent boundary layer interaction flows.","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":"134447208","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.2003.1274891
H. Richard, W. Becker, S. Loose, M. Thimm, Johannes Bosbach, M. Raffel
Cryogenic investigations of the trailing vortices of large future transport aircrafts have been performed on an aircraft half-model with different wing tip devices. The model has been installed in the cryogenic wind tunnel (KKK) of the German-Dutch wind tunnels (DNW) in Cologne. During the tests, PIV flow field measurements have been performed in addition to conventional force, moment, and pressure distribution measurements. The measurements of the velocity field gave an insight into important aerodynamic effects as, for example, the dependents of vortex strength with changing angles of incidence as well as the differences in the spatial vorticity distribution in the wake. The PIV technique offers special advantages for the investigation of those wakes at very low temperatures, but also yields to special experimental difficulties, which are also described in this article.
{"title":"Application of particle image velocimetry under cryogenic conditions","authors":"H. Richard, W. Becker, S. Loose, M. Thimm, Johannes Bosbach, M. Raffel","doi":"10.1109/ICIASF.2003.1274891","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274891","url":null,"abstract":"Cryogenic investigations of the trailing vortices of large future transport aircrafts have been performed on an aircraft half-model with different wing tip devices. The model has been installed in the cryogenic wind tunnel (KKK) of the German-Dutch wind tunnels (DNW) in Cologne. During the tests, PIV flow field measurements have been performed in addition to conventional force, moment, and pressure distribution measurements. The measurements of the velocity field gave an insight into important aerodynamic effects as, for example, the dependents of vortex strength with changing angles of incidence as well as the differences in the spatial vorticity distribution in the wake. The PIV technique offers special advantages for the investigation of those wakes at very low temperatures, but also yields to special experimental difficulties, which are also described in this article.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"73 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":"128580824","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.2003.1274850
F. Albano, F. De Gregorio, A. Ragni
This paper summarises the activities performed in order to investigate the formation, motion and persistence of trailing vortices released by large commercial aircraft. Two different experimental test campaigns were carried out in two different large towing tank facilities performing PIV measurements. The lesson learned by the first investigation and by the experience of the scientific community, the solution adopted in order to characterise the wake vortex by the initial formation phase down to wake collapsing in the far-wake region are illustrated. Together with the adopted technical solution, with the selected experimental facility and with the improved measurement system, a particular care is taken: on the data analysis description, on the importance of advanced PIV algorithms and on the selected postprocessing methods for evaluating the main magnitudes characterising the vortex structures.
{"title":"Trailing vortex detection and quantitative evaluation of vortex characteristics by PIV technique","authors":"F. Albano, F. De Gregorio, A. Ragni","doi":"10.1109/ICIASF.2003.1274850","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274850","url":null,"abstract":"This paper summarises the activities performed in order to investigate the formation, motion and persistence of trailing vortices released by large commercial aircraft. Two different experimental test campaigns were carried out in two different large towing tank facilities performing PIV measurements. The lesson learned by the first investigation and by the experience of the scientific community, the solution adopted in order to characterise the wake vortex by the initial formation phase down to wake collapsing in the far-wake region are illustrated. Together with the adopted technical solution, with the selected experimental facility and with the improved measurement system, a particular care is taken: on the data analysis description, on the importance of advanced PIV algorithms and on the selected postprocessing methods for evaluating the main magnitudes characterising the vortex structures.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"37 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":"132452809","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.2003.1274882
B. Thurow, N. Jiang, M. Samimy, W. Lempert, G. Switzer, L. Goss
Recent progress in the development of MHz frame flow diagnostics are presented, based on enhancements to a "burst" mode Nd:YAG laser. In particular, a PDV system that can measure velocity over a plane at rates up to 1 MHz is demonstrated, as well initial results from a custom-built Optical Parametric Oscillator, designed specifically for use with the burst mode pump. Production of broadly wavelength tunable pulse trains, with order mJ individual pulse energy and order 1 cm/sup -1/ spectral linewidth is described.
{"title":"Recent enhancements to the OSU burst mode laser and MHz rate imaging systems","authors":"B. Thurow, N. Jiang, M. Samimy, W. Lempert, G. Switzer, L. Goss","doi":"10.1109/ICIASF.2003.1274882","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274882","url":null,"abstract":"Recent progress in the development of MHz frame flow diagnostics are presented, based on enhancements to a \"burst\" mode Nd:YAG laser. In particular, a PDV system that can measure velocity over a plane at rates up to 1 MHz is demonstrated, as well initial results from a custom-built Optical Parametric Oscillator, designed specifically for use with the burst mode pump. Production of broadly wavelength tunable pulse trains, with order mJ individual pulse energy and order 1 cm/sup -1/ spectral linewidth is described.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"26 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":"122881246","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.2003.1274866
J. Naughton, J. Robinson, V. Durgesh
The measurement of wall shear stress is increasingly recognized as a critical element of aerodynamic testing. Wall shear stress is necessary to characterize fully a wall-bounded flow, to provide critical information necessary for computational simulations, and to serve as a sensitive quantity for use in flow-control applications. Oil-film interferometry is a method that can be used to measure wall shear stress quickly and accurately, but the analysis of the interferograms is complex and has limited the methods use. OILFILMTOOL is a Matlab program that has been developed to simplify the analysis process. The analysis steps required to determine wall shear stress from an interferogram obtained using oil-film interferometry are discussed, and those methods currently implemented in OILFILMTOOL are highlighted. The application of OILFILMTOOL to interferograms acquired on the surface of a wedge body is discussed. It is hoped that, by implementing the complex analysis process in a simple-to-use program, the use of oil-film interferometry in aerodynamic test facilities will become more widespread.
{"title":"Oil-Film interferometry measurement of skin friction - analysis summary and description of Matlab program","authors":"J. Naughton, J. Robinson, V. Durgesh","doi":"10.1109/ICIASF.2003.1274866","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274866","url":null,"abstract":"The measurement of wall shear stress is increasingly recognized as a critical element of aerodynamic testing. Wall shear stress is necessary to characterize fully a wall-bounded flow, to provide critical information necessary for computational simulations, and to serve as a sensitive quantity for use in flow-control applications. Oil-film interferometry is a method that can be used to measure wall shear stress quickly and accurately, but the analysis of the interferograms is complex and has limited the methods use. OILFILMTOOL is a Matlab program that has been developed to simplify the analysis process. The analysis steps required to determine wall shear stress from an interferogram obtained using oil-film interferometry are discussed, and those methods currently implemented in OILFILMTOOL are highlighted. The application of OILFILMTOOL to interferograms acquired on the surface of a wedge body is discussed. It is hoped that, by implementing the complex analysis process in a simple-to-use program, the use of oil-film interferometry in aerodynamic test facilities will become more widespread.","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":"115422296","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.2003.1274859
D. Pallek, K. Butefisch, J. Quest, W. Strudthoff
A non-intrusive Moire Interferometry system has been designed and installed to determine the instantaneous deformation of aircraft models during testing in the European Transonic Windtunnel. The present paper describes the principles of the Moire technique and the experimental set-up of the system. As high accuracy for the measurement of wing twist (<0.1/spl deg/) and wing bending (<0.05 mm) is required, hardware and evaluation software have to be carefully designed. The influence of disturbing effects is discussed in detail, also the solutions to overcome these problems. Measurements of the wing twist of an A 380 type aircraft within the European HiReTT project are described, and results of selected test cases are presented and compared to other experimental and numerical methods.
{"title":"Model deformation measurement in ETW using the Moire technique","authors":"D. Pallek, K. Butefisch, J. Quest, W. Strudthoff","doi":"10.1109/ICIASF.2003.1274859","DOIUrl":"https://doi.org/10.1109/ICIASF.2003.1274859","url":null,"abstract":"A non-intrusive Moire Interferometry system has been designed and installed to determine the instantaneous deformation of aircraft models during testing in the European Transonic Windtunnel. The present paper describes the principles of the Moire technique and the experimental set-up of the system. As high accuracy for the measurement of wing twist (<0.1/spl deg/) and wing bending (<0.05 mm) is required, hardware and evaluation software have to be carefully designed. The influence of disturbing effects is discussed in detail, also the solutions to overcome these problems. Measurements of the wing twist of an A 380 type aircraft within the European HiReTT project are described, and results of selected test cases are presented and compared to other experimental and numerical methods.","PeriodicalId":166420,"journal":{"name":"20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.","volume":"10 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":"131219824","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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