{"title":"Development of a liquid oxygen density reference system","authors":"Yayu Li","doi":"10.1109/ICIASF.1997.644677","DOIUrl":"https://doi.org/10.1109/ICIASF.1997.644677","url":null,"abstract":"The development of a liquid oxygen density reference system is used in the measurement of liquid oxygen density. The system consists mainly of liquid oxygen container, special purpose thermostat, pressure control device, buoy, evacuation system, electronic balance measurement system, tracking and commanding system of chip microprocessor, and PC. The analysis of measurement uncertainty for the liquid oxygen density reference system indicates that the system error is /spl plusmn/0.02%. In the light of random error possibly resulting from measurements, the measurement uncertainty of liquid oxygen density for the system is /spl plusmn/0.05%. The measurement of liquid oxygen density will be more correct, reliable and convenient for the liquid oxygen density reference system, when compared with sensor of traditional liquid oxygen density measurement.","PeriodicalId":122871,"journal":{"name":"ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities","volume":"72 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1997-09-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116724718","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}
S. de Ponte, L. Gasparini, G. Gibertini, L. Codazzi
{"title":"New concepts about 4 hole wall stress probe","authors":"S. de Ponte, L. Gasparini, G. Gibertini, L. Codazzi","doi":"10.1109/ICIASF.1997.644684","DOIUrl":"https://doi.org/10.1109/ICIASF.1997.644684","url":null,"abstract":"For improving the wall shear stress measurement in a fluid stream, a new procedure for calibration of the \"triangular probe\" is developed. This new procedure allows to have thinner probes, completely submerged into the viscous sublayer, thus it is less intrusive and reduces the experimental perturbations. Comparisons to numerical results on an airfoil surface confirm the validity of this new procedure.","PeriodicalId":122871,"journal":{"name":"ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities","volume":"8 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1997-09-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125616964","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":"Design of a steady-state heat flux probe for measurements in an induction-heated plasma flow [wind tunnels]","authors":"J.F. Lumens, B. Bottin, M. Carbonaro","doi":"10.1109/ICIASF.1997.644760","DOIUrl":"https://doi.org/10.1109/ICIASF.1997.644760","url":null,"abstract":"The design of a steady-state heat flux probe for high-enthalpy plasma flows was performed using empirical and numerical methods. A commercial code has been used to assess the local heat transfer inside the probe, at the stagnation point. The study led to the optimization of the cooling circuit geometry and to the quantification of the convective heat transfer coefficient. A minimal mass flow rate was thus defined to avoid local boiling. Classical uncertainty theory has been used to derive the maximum mass flow rate leading to the state-of-the-art uncertainty of 10%. It is shown that with the proposed geometry it is possible to obtain an uncertainty of 5% or less in the heat flux range (350 kW/m/sup 2/, 1200 kW/m/sup 2/). A method is proposed by which the operational chart of the probe can be drawn for any change in the design parameters. The chart is given for the present design.","PeriodicalId":122871,"journal":{"name":"ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities","volume":"59 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1997-09-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124390376","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 6-component jet rig balance for studying new thrust vectoring concepts","authors":"M. Ramaswamy, F. Alvi, A. Krothapalli","doi":"10.1109/ICIASF.1997.644682","DOIUrl":"https://doi.org/10.1109/ICIASF.1997.644682","url":null,"abstract":"A new concept for efficient thrust vectoring of jet exhausts for aerospace applications, known as CounterFlow Thrust Vector (CFTVC) Control has been investigated at the Fluid Mechanics Research Laboratory (FMRL) over the past few years. Although pressure measurements and flow visualization results have proven the efficacy of this technique, it was felt that more direct measurements of the vectoring angles and thrust efficiency are needed to evaluate the CFTVC performance more rigorously. Therefore a special 6-component balance to measure the main thrust as well as the lateral thrust, (which may be in any direction) was conceived, designed and fabricated at FMRL. This paper provides complete details of the design, fabrication, assembly, calibration and data reduction procedures of this balance. Some typical results obtained using this rig are also presented which clearly demonstrate the accuracy and usefulness of this instrument.","PeriodicalId":122871,"journal":{"name":"ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities","volume":"24 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1997-09-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133916579","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}
S. Hogg, W. Carscallen, J. Gostelow, D. Buttsworth, T. V. Jones
{"title":"Wide bandwidth stagnation temperature measurements in vortical flows behind turbine vanes","authors":"S. Hogg, W. Carscallen, J. Gostelow, D. Buttsworth, T. V. Jones","doi":"10.1109/ICIASF.1997.644757","DOIUrl":"https://doi.org/10.1109/ICIASF.1997.644757","url":null,"abstract":"A new fast response measurement technique for total temperature, originally developed for testing in transient facilities, has been adapted and used to make turbine vane wake flow measurements in a continuously running linear cascade. The bandwidth of the new method approaches 100 kHz, and is a considerable improvement on previous techniques. The measurements show clear evidence of vortex shedding over a range of Mach numbers. The shedding is consistent with previous schlieren and wake pressure measurements. At sub-sonic exit Mach numbers, the total temperature data shows vortex shedding at a Strouhal number of just above 0.2. This is consistent with data from other cascades. At supersonic exit conditions, the measurements show that the vortex shedding breaks down into a number of different intermittent shedding modes. This is also consistent with earlier results. The existence of strong vortex driven energy separation in the wake through the Eckert-Weise effect, in which temperatures are suppressed in the centre and discrete 'hot spots' appear towards the edges of the wake flow, is confirmed by the total temperature measurements. The new measurements are used to explain earlier results from the cascade, which were previously thought to be anomalous.","PeriodicalId":122871,"journal":{"name":"ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities","volume":"31 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1997-09-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121897743","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":"Design and calibration of an unsteady pressure measurement system","authors":"H. Boerrigter, J. Charbonnier","doi":"10.1109/ICIASF.1997.644680","DOIUrl":"https://doi.org/10.1109/ICIASF.1997.644680","url":null,"abstract":"A calibration method for fast response pressure transducers has been developed and tested. The results prove that the setup is very effective, and have indicated resonant behaviour in existing pressure transducers due to the presence of a protective screen. In parallel, a simulation program has been developed which runs on a PC, computing the frequency behaviour of unsteady pressure measurement systems. A verification of the simulations against data obtained with the calibration method shows excellent results. The same program has been shown to correctly compute the time response of pressure measurement systems, thus providing the means to optimize response times. Finally, the program has been used for the design of a new setup, which was shown to perform differently than intended, but exactly as necessary.","PeriodicalId":122871,"journal":{"name":"ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities","volume":"46 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1997-09-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125255981","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":"Miniature rotating amplifier system for windtunnel application packs 256 pre-conditioning channels in 187 cubic inch","authors":"M.H.J.B. Versteeg, H. Slot","doi":"10.1109/ICIASF.1997.644681","DOIUrl":"https://doi.org/10.1109/ICIASF.1997.644681","url":null,"abstract":"For a NASA windtunnel model NLR developed a 256 channel pressure sensor signal conditioning and amplifier system. This system was to be mounted within the rotating part of the model in a volume of 7 inch diameter and less than 6 inch long. The development of this system, called Rotating Amplifier System (RAS), required a close cooperation between electrical and mechanical designers to meet all customer requirements. For all 256 channels the bridge supply voltage, offset and gain are separately remote controllable to allow for adjustments during a running experiment. These configuration settings are loaded into the system using a dedicated serial link. For on-line calibration an R-Cal function is available with 3 separate resistor values. The mechanical construction of the RAS unit consists of a cylindrical unit that is mounted on the propeller shaft between gearbox and sliprings. The RAS unit is of modular design and consists 16 of identical modules, each containing 16 self contained amplifier channels, sensor power supplies and associated control logic. The amplifier system was realized using specially developed hybrid modules and packs the complete functionality in 187 cubic inch.","PeriodicalId":122871,"journal":{"name":"ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities","volume":"24 3 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1997-09-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121033568","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":"Rayleigh light scattering as a pulse local probing of non-equilibrium gas flows","authors":"O. Nerushev, S. Novopashin, A. L. Perepelkin","doi":"10.1109/ICIASF.1997.644751","DOIUrl":"https://doi.org/10.1109/ICIASF.1997.644751","url":null,"abstract":"The pulse local probing technique based on Rayleigh light scattering phenomenon in gas phase is presented. The range of possibilities is demonstrated by the measurement of parameters of supersonic laminar and turbulent jets, profiles of shock waves and condensation in free jets of Ar.","PeriodicalId":122871,"journal":{"name":"ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities","volume":"130 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1997-09-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116205711","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}
K. Asai, Hiroshi Kanda, C. T. Cunningham, Richard Erausquin, J. P. Sullivan
{"title":"Surface pressure measurement in a cryogenic wind tunnel by using luminescent coating","authors":"K. Asai, Hiroshi Kanda, C. T. Cunningham, Richard Erausquin, J. P. Sullivan","doi":"10.1109/ICIASF.1997.644671","DOIUrl":"https://doi.org/10.1109/ICIASF.1997.644671","url":null,"abstract":"In recent experiments, we demonstrated the feasibility of using luminescent coatings for surface pressure measurement in a cryogenic wind tunnel. This technique is based on a new coating technology in which luminescent molecules are directly deposited onto the model surface by an electrochemical process. The resulting coating has an extremely high oxygen sensitivity for mole fractions of oxygen is less than 0.1%. This capability allows us to measure the pressure field on the model surface in a cryogenic wind tunnel. To demonstrate this technology, a 14%-thick bump model was tested in the 0.1-m Transonic Cryogenic Wind Tunnel at NAL. Mach number was changed from 0.4 to 0.84 whereas temperature was maintained at 100 K. A small amount of oxygen was injected into the tunnel and the mole fraction of oxygen in the test gas was kept constant. We acquired two intensity images, one taken at low speeds and the other taken at high Mach numbers. By taking the ratio of these images, surface pressure distributions on the model were clearly captured. The result of the in situ calibration showed that effects of temperature dependence of the coating was negligible. The paint-derived pressure distributions are in good agreement with pressure tap measurements.","PeriodicalId":122871,"journal":{"name":"ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities","volume":"32 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1997-09-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128134063","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}
P. Sagnier, J. Verant, D. Devezeaux, A. Mohamed, A. Masson
{"title":"Real gas flow characterization in the ONERA F4 high enthalpy wind tunnel","authors":"P. Sagnier, J. Verant, D. Devezeaux, A. Mohamed, A. Masson","doi":"10.1109/ICIASF.1997.644756","DOIUrl":"https://doi.org/10.1109/ICIASF.1997.644756","url":null,"abstract":"The ONERA F4 Hot Shot wind tunnel provides hypersonic air flows at high enthalpy and high pressure total conditions. In such a wind tunnel, real gas effects are large yielding experimental difficulties to assess the test section free stream characteristics. Flow contamination was a problem for total enthalpy determination when using the first arc chamber configuration, made of copper and organic materials. This point has been dramatically improved with the new arc chamber made of carbon materials. Test section free stream knowledge is achieved by direct means involving optical techniques and by indirect means, i.e. through the numerical rebuilding of experiments on nozzle and standard model flows. The free stream flow is observed to be close to equilibrium on data like pressure or translational temperature, while nitric oxide (NO) concentration measurement is rather close to a nonequilibrium situation. The possibility to model such results is discussed. Finally, example example of force measurements on a capsule model is given to compare real gas with perfect gas results.","PeriodicalId":122871,"journal":{"name":"ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities","volume":"2086 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1997-09-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132359195","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}