ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025)最新文献

{"title":"LDA system for in-flight local velocity measurements on airplane wings","authors":"S. Becker, F. Durst, H. Lienhart","doi":"10.1109/ICIASF.1999.827165","DOIUrl":"https://doi.org/10.1109/ICIASF.1999.827165","url":null,"abstract":"The development of laminar wing technology requires wind tunnel studies with numerical flow simulations and in-flight measurements. A strategy for in-flight flow measurements is outlined. It is shown that laser Doppler anemometry (LDA) is well suited for providing the desired local velocity information, but must be specifically adapted for the various spatial, geometrical, and power constraints imposed by the test aircraft. This program yielded two optical units suitable for in-flight velocity measurements on airplane wings. Laboratory and free flight measurements studying boundary layer transition on an airplane wing downstream of an excitation source were successfully carried out and a summary of results is presented. Finally, suggestions for further advancements of LDA systems are proposed.","PeriodicalId":291132,"journal":{"name":"ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025)","volume":"73 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1999-06-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127255276","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}

{"title":"Half-model-balance for the Cologne-cryogenic-wind-tunnel development and test results","authors":"K. Hufnagel, R. Rebstock, Junnai Zhai","doi":"10.1109/ICIASF.1999.827172","DOIUrl":"https://doi.org/10.1109/ICIASF.1999.827172","url":null,"abstract":"The Cologne Cryogenic Wind Tunnel (KKK) is instrumented with internal balances. There has been high demand from the tunnel customers to make half model tests at high Reynolds numbers. The Mach number range from zero to 0.3 and the relative low costs with regard to the high Reynolds number made the KKK very attractive for half model testing. To realize this capability it was decided to develop a half-model-balance for the KKK. This was a very challenging task, because no previous attempt to solve this problem for a continuous running cryogenic wind tunnel was successful. Fortunately, the tests in the tunnel with the first balance (W519) built were very successful. During the tests a lot of experience was gained and some new problems appeared. The main problem was the unexpected large temperature gradient inside the balance, although there was a very sophisticated heating and insulating device around the balance. A finite element study was made to design a new balance in such a way that the balance is more insensitive to temperature gradients. Unfortunately the balance W519 was destroyed by an accident in the tunnel and we had to build a second one (W523) very quickly. All the things we learned had to be turned into practice very quickly without any tests in the laboratory. Finite element calculations turned out to be a very useful tool to solve this task. We used the external balance of our low speed wind tunnel as a reference balance to give us the \"true loads\". By this method no realignment of the calibration model was necessary and the calibration process could be done in three weeks. The accuracy of the new procedure, based on recalculation of the calibration loads, turned out to be better than the former one, because the accuracy of the external balance is one magnitude better than the required accuracy of the half model balance and there are no errors of misalignment. The comparison between some measurements, made with the old balance and the new one, showed a very good correspondence. The repeatability of polars with the new balance in the tunnel was about one drag and lift count.","PeriodicalId":291132,"journal":{"name":"ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025)","volume":"27 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1999-06-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132000783","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}

{"title":"Measurement technology of the impact of alumina liquid particles on a hot surface","authors":"C. Escure, M. Vardelle, A. Grimaud, P. Fauchais","doi":"10.1109/ICIASF.1999.827151","DOIUrl":"https://doi.org/10.1109/ICIASF.1999.827151","url":null,"abstract":"The aim of this study, carried out in the frame of the ASSM (Aerodynamics of Segmented Solid Motors) research program, is a better understanding of the phenomena that govern the interactions between liquid alumina particles and a hot surface or liquid alumina film. To achieve it, a complex experimental device has been designed and built. In a controlled argon atmosphere chamber are set two plasma torches and a reclining substrate. This set-up allows the use of carbon-carbon substrates. The first plasma torch produces molten alumina particles, and the second one heats the substrate up to 2300 K. An optical diagnostic characterizes the in-flight parameters of a single particle : its size and velocity by PDA (Particle Doppler Anemometry) and its temperature by two-color fast (100 ns) pyrometry. An imaging technique monitors the impact mode: splashing, deposition or rebound. For the latter the rebounding angle and velocity can be measured. A laser beam is used for visualization of trajectories in a narrow wavelength band-pass. For each droplet, its size, velocity and temperature are measured and impact is observed. The goal is to investigate how the impact mode is influenced by these parameters.","PeriodicalId":291132,"journal":{"name":"ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025)","volume":"211 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1999-06-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115645382","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}

{"title":"Non-intrusive diagnostics for the AEDC Impulse Facility: applications and results","authors":"W. Williams, M. Smith, F. Heltsley, C. Brasier, P. Sherrouse, W. Ruyten, L. Price, E. Felderman, K. M. Stephens","doi":"10.1109/ICIASF.1999.827181","DOIUrl":"https://doi.org/10.1109/ICIASF.1999.827181","url":null,"abstract":"As part of a modernization of the AEDC hypersonic test capability, a free-piston shock tunnel, known as the Impulse Facility, was constructed. Initial shakedown and calibration tests were completed in 1994. The facility remained dormant until the recent resurgence in interest in hypersonics at AEDC. A cooperative project was established between AEDC and the DLR/HEG with the objectives of accelerating and improving the development cycle for both the Impulse Facility and the HEG. An integral part of this project was an ambitious plan for the use of non-intrusive diagnostics to provide key information about the flow field. This paper is essentially a status report of the efforts to date.","PeriodicalId":291132,"journal":{"name":"ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025)","volume":"13 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1999-06-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114009875","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}

{"title":"Comparison of luminescent paints measurement systems","authors":"M. Guille, J. P. Sullivan, J. Holmes","doi":"10.1109/ICIASF.1999.827156","DOIUrl":"https://doi.org/10.1109/ICIASF.1999.827156","url":null,"abstract":"Techniques based on luminescent paints are a way to obtain the pressure and/or temperature distribution over a surface. Measurement systems associated with these techniques consist of an illumination source, a detector to measure the luminescence emitted by the paint coated on the surface and a procedure to relate luminescence to pressure or temperature, which all differ from one system to the other. Experiments are done at Purdue University using different luminescent paints measurement systems to obtain pressure and temperature distributions from a jet impinging obliquely on a flat plate. A cooperation between Purdue University and DERA makes it possible to group three systems for comparison. They include the CCD camera system and the laser scanning system developed at Purdue University, and the DERA fluorescent lifetime imaging (FLIM) system.","PeriodicalId":291132,"journal":{"name":"ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025)","volume":"96 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1999-06-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125083123","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}

{"title":"Special probes for measurements of flow parameters in a gas-turbine engine","authors":"Z.M. Romicki, S. Żurkowski","doi":"10.1109/ICIASF.1999.827144","DOIUrl":"https://doi.org/10.1109/ICIASF.1999.827144","url":null,"abstract":"Three special probes have been measurements of flow parameters, a combustion chamber of a gas turbine engine. The first arrangement has been designed for measurements of static pressure in a flow with high value of streamline curvature. The probe consists of two flat round plates (Saire plates) fixed parallel very near to each other to the stem of the probe. Pressures are measured in the centre of the inner side of each plate and averaged inside the stem. The design of the second probe (compound probe) has been governed by the purpose in doing simultaneous measurements of total pressure and total temperature, exactly at the same point of a flow. The probe is based on the direction non-sensitive Pitot probe, but with the sheathed thermocouple placed inside the pressure pipe. The same probe was used to collect samples for analysis of an exhaust gas composition. The design of the third probe has been based on the idea to measure air total pressure and static pressure in the inlet of combustion chamber vaporizer without disturbing its normal operation. The probe is based on a typical fuel injector for the annular vaporizing combustion chamber. The fuel injector has been equipped with two additional pressure pipes arranged to enable measurements of total pressure and static pressure on the outer side of the fuel outlet.","PeriodicalId":291132,"journal":{"name":"ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025)","volume":"6 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1999-06-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122515526","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}

{"title":"Determination of residual wall interferences for measurements on the TWIG model-comparison of different methods and analysis","authors":"H. Holst, J. Archambaud, A. Mignosi, M. Jacobs","doi":"10.1109/ICIASF.1999.827175","DOIUrl":"https://doi.org/10.1109/ICIASF.1999.827175","url":null,"abstract":"Measurements have been carried out in the dimensional adaptive test sections of the Transonic Windtunnel Gottingen TWG of DLR and the T2 wind tunnel of ONERA Toulouse. The TWIG model (Transonic Wall Interference Generator) was available in two different scales, so that for the test sections of different sizes, the relative model size was the same. The wall adaptation was performed using the fast Wedemeyer/Lamarche method for determining the wall shapes in both cases. As a first step, different methods for the determination of residual wall interferences have been applied to data from the adaptive test section of the University of Southampton, U.o.S. These were regarded as very reliable and accurate, and wall contour data and very dense pressure distributions were available. Residual wall interferences computed by the U.o.S., DLR, ONERA and NLR show very good agreement. The measurements on the two different TWIG models in the adaptive test sections of T2 and TWG show good agreement for the wall shapes and the measured pressure distribution. Data from TWG were taken for the determination of residual wall interferences by the different methods. The residual wall interferences do not agree so perfectly as they had with the U.o.S. Data. The reasons for this are/could possibly be: wall pressure data not so dense as before; influence of the finite length of the test section; model representation not \"good\" enough; model not centrally placed; support influences; exit section not taken into account.","PeriodicalId":291132,"journal":{"name":"ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025)","volume":"46 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1999-06-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125124256","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}

{"title":"Flow velocities visualization using Doppler picture interference velocimetry","authors":"F. Seiler, A. George, F. Leopold, J. Srulijes, G. Smeets","doi":"10.1109/ICIASF.1999.827150","DOIUrl":"https://doi.org/10.1109/ICIASF.1999.827150","url":null,"abstract":"An improved technique for visualizing a velocity field in an entire plane has been developed by taking \"Doppler Velocimetry Pictures\" using Michelson interferometry (DPV). The Doppler pictures give information about the instantaneous the local velocities of tracers passing through a light sheet. The Doppler shift of the frequency of the light scattered by tracer particles is modified by a Michelson interferometer into varying light intensities. The initial interference fringe system is transformed by flow velocities. Two different techniques for the treatment of the images are presented. The first one is based on the shift of the fringe system, the second one uses the different light intensity distribution of the fringe system. For both cases the Doppler pictures are taken by CCD cameras and the images are computer-processed for velocity presentation.","PeriodicalId":291132,"journal":{"name":"ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025)","volume":"31 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1999-06-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133873953","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}

{"title":"An integrated approach to the application of high bandwidth optical pyrometry to turbine blade surface temperature mapping","authors":"J. Douglas, C. A. Smith, S.J.R. Taylor","doi":"10.1109/ICIASF.1999.827143","DOIUrl":"https://doi.org/10.1109/ICIASF.1999.827143","url":null,"abstract":"As gas turbine manufacturers strive for improved efficiency the turbine operating temperatures increase which can only be met by improvements in blade and coating materials together with advances in cooling and coating technologies. The ultimate, and possibly the only, environment capable of testing modem blade systems is in a working engine and it is from this environment that instrumentation a range of instrumentation technologies must acquire valid blade performance data. A critical blade parameter is the surface temperature distribution and this paper reviews the various technologies currently applied to blade surface temperature distribution measurement. Optical Pyrometry is discussed in more detail and the definition of an integrated high bandwidth detection and data collection system developed. The system developed collects turbine and stores radiance measurements at the rate of 1 million per second and this paper explores the benefits that can accrue from this approach in areas such as noise reduction and blade scanning techniques. The output from such a system is a data file representing a 'thermal image' of all the blade surfaces viewed by the pyrometer. The conversion of the 'thermal image' into a temperature image is discussed and the role of complimentary measurement methods in refining the temperature image is reviewed. The integration of measurement techniques limits the ability of suppliers to deliver an 'Off-The-Shelf' measurement capability. In the light of this the limitations of the system outlined in the paper are discussed and the need for collaborative effort between the system supplier and the users technical departments emphasised.","PeriodicalId":291132,"journal":{"name":"ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025)","volume":"72 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1999-06-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124633800","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}

{"title":"Incompressible aerodynamics of a planetary entry capsule","authors":"O. Karatekin, R. Voets, J. Charbonnier, F.Y. Wang","doi":"10.1109/ICIASF.1999.827170","DOIUrl":"https://doi.org/10.1109/ICIASF.1999.827170","url":null,"abstract":"The methodology and the assorted experimental techniques utilized in the aerodynamic investigation of a planetary entry capsule at low speed are presented. The combination of novel and classical instrumentation permitted the description of topology and off surface features that are important in the study of terminal capsule aerodynamics. In addition. Suggestions on future commercial development of sensors conducive for general blunt body studies are made.","PeriodicalId":291132,"journal":{"name":"ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025)","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1999-06-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127467615","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}