Pub Date : 1993-09-20DOI: 10.1109/ICIASF.1993.687693
R. Engler
After the first demonstration tests performed together with the developers of the OPMS system in January 1991 and after the presentation of these results at the 14th ICIASF Congress in RockviIle, USA [l], the DLR started additional tests on her own. The first step was to optimize the video camera and illumination system for measurements on model surfaces with curved and rounded parts, the next step was to change the spraying technique of the pressure-sensitive paint. DLR has accompanied all these investigations by simultaneous measurements using the conventional pressure technique for a common and comparative evaluation. Furthermore first tests for unsteady pressure measurements were made.
{"title":"Additional Developments of the Optical Pressure Measurement System (OPMS) for Non-flat Models and Unsteady Flow Conditions","authors":"R. Engler","doi":"10.1109/ICIASF.1993.687693","DOIUrl":"https://doi.org/10.1109/ICIASF.1993.687693","url":null,"abstract":"After the first demonstration tests performed together with the developers of the OPMS system in January 1991 and after the presentation of these results at the 14th ICIASF Congress in RockviIle, USA [l], the DLR started additional tests on her own. The first step was to optimize the video camera and illumination system for measurements on model surfaces with curved and rounded parts, the next step was to change the spraying technique of the pressure-sensitive paint. DLR has accompanied all these investigations by simultaneous measurements using the conventional pressure technique for a common and comparative evaluation. Furthermore first tests for unsteady pressure measurements were made.","PeriodicalId":398832,"journal":{"name":"International Congress on Instrumentation in Aerospace Simulation Facilities,","volume":"5 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-09-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131518424","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 : 1993-09-20DOI: 10.1109/ICIASF.1993.687653
G. Gundlach, E. Hirai
{"title":"Rotational Temperatures of NO and O/sub 2/ in Hypersonic Free Jet Flows Near a Hot Model Surface Measured by LIF","authors":"G. Gundlach, E. Hirai","doi":"10.1109/ICIASF.1993.687653","DOIUrl":"https://doi.org/10.1109/ICIASF.1993.687653","url":null,"abstract":"","PeriodicalId":398832,"journal":{"name":"International Congress on Instrumentation in Aerospace Simulation Facilities,","volume":"4 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-09-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115429919","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 : 1993-09-20DOI: 10.1109/ICIASF.1993.687650
L.G.M. Custers, A.H.W. Hoeijmakers, A. Harris
At NLR a six-component rotating shafl balance has been developed. The rotating shaft balance (RSB) is intended for use during propeller forces measurements, both installed and isolated testing. By using an RSB it is possible to determine the propeller wing interference effects on the propeller as well as on the wing. The development work included the design of the RSB, the creation of a suitable dynamic data acquisition system and a series of proving trials. An Fast Fourier Transform (FFT) system has been used to support the determination of the off-axis components of the forces and moments. During these trials the RSB was calibrated statically on all components and dynamically on thrust and torque. In addition propeller performance measurements have been wormed to acquire operational experience and to determine the influence of oblique inflow into the propeller plane. Both the proving trials and the performance measurements have been performed in the NLR closed circuit Low Speed wind Tunnel (UT). The RSB was mounted on an isolated propeller rig which has been used in previous wind tunnel tests. An extensively tested one fifth scale Fokker 50 model propeller has been used, thus a subslantid performance database and experience of the rig was already available. Trials showed that an accuracy of 0.2 96 on torque and 0.3 % full scale on thrust was rea l id . Results of the propeller performance test indicated an accuracy for the off-axis components of 1.5 % and 1.8 % for ESP. the off-axis moment and force. The tria Is and isolated propeller tests have given confidence in the RSB design, manufacturing and testing capabilities and a design and production approach is now defined. It is planned to use the existing RSB in conjunction with an extemal six-component balance in an installed propeller half model test. With the availability of the RSB it is now possible to close the accounting scheme in determination of propellerlwing interaction forces and moments . ' J =
{"title":"Rotating shaft balance for measurement of total propeller force and moment","authors":"L.G.M. Custers, A.H.W. Hoeijmakers, A. Harris","doi":"10.1109/ICIASF.1993.687650","DOIUrl":"https://doi.org/10.1109/ICIASF.1993.687650","url":null,"abstract":"At NLR a six-component rotating shafl balance has been developed. The rotating shaft balance (RSB) is intended for use during propeller forces measurements, both installed and isolated testing. By using an RSB it is possible to determine the propeller wing interference effects on the propeller as well as on the wing. The development work included the design of the RSB, the creation of a suitable dynamic data acquisition system and a series of proving trials. An Fast Fourier Transform (FFT) system has been used to support the determination of the off-axis components of the forces and moments. During these trials the RSB was calibrated statically on all components and dynamically on thrust and torque. In addition propeller performance measurements have been wormed to acquire operational experience and to determine the influence of oblique inflow into the propeller plane. Both the proving trials and the performance measurements have been performed in the NLR closed circuit Low Speed wind Tunnel (UT). The RSB was mounted on an isolated propeller rig which has been used in previous wind tunnel tests. An extensively tested one fifth scale Fokker 50 model propeller has been used, thus a subslantid performance database and experience of the rig was already available. Trials showed that an accuracy of 0.2 96 on torque and 0.3 % full scale on thrust was rea l id . Results of the propeller performance test indicated an accuracy for the off-axis components of 1.5 % and 1.8 % for ESP. the off-axis moment and force. The tria Is and isolated propeller tests have given confidence in the RSB design, manufacturing and testing capabilities and a design and production approach is now defined. It is planned to use the existing RSB in conjunction with an extemal six-component balance in an installed propeller half model test. With the availability of the RSB it is now possible to close the accounting scheme in determination of propellerlwing interaction forces and moments . ' J =","PeriodicalId":398832,"journal":{"name":"International Congress on Instrumentation in Aerospace Simulation Facilities,","volume":"39 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-09-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114926848","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 : 1993-09-20DOI: 10.1109/ICIASF.1993.687665
A. Baring, B. Lawton
Computer optical tomography has been used as a diagnostic technique in the study of a premixed methane-air diffusion turbulent flame of equivalence aidfuel ratio of 0.5. Visible light from a tungsten filament lamp at a wavelength of 0.65pm was used. The test plane, of 12 mm diameter, was scanned using eleven equi-spaced parallel optical paths which were rotated through 180 deg and a complete set of readings were taken at 30 cleg intervals. The optical thickness and emission ratio wen: measured along each path and at each 30 deg interval. A computer program based on the convolution method combined with the Shepp-Logan filter [ 11, was used to reconstruct a two-dimensional image of the absorption coefficient, emission function, temperature distribution and soot concentration at a chosen instant.
{"title":"Application of Computer Optical Tomography to the Study of Methane-Air Turbulent Flame","authors":"A. Baring, B. Lawton","doi":"10.1109/ICIASF.1993.687665","DOIUrl":"https://doi.org/10.1109/ICIASF.1993.687665","url":null,"abstract":"Computer optical tomography has been used as a diagnostic technique in the study of a premixed methane-air diffusion turbulent flame of equivalence aidfuel ratio of 0.5. Visible light from a tungsten filament lamp at a wavelength of 0.65pm was used. The test plane, of 12 mm diameter, was scanned using eleven equi-spaced parallel optical paths which were rotated through 180 deg and a complete set of readings were taken at 30 cleg intervals. The optical thickness and emission ratio wen: measured along each path and at each 30 deg interval. A computer program based on the convolution method combined with the Shepp-Logan filter [ 11, was used to reconstruct a two-dimensional image of the absorption coefficient, emission function, temperature distribution and soot concentration at a chosen instant.","PeriodicalId":398832,"journal":{"name":"International Congress on Instrumentation in Aerospace Simulation Facilities,","volume":"97 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-09-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134545872","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 : 1993-09-20DOI: 10.1109/ICIASF.1993.687659
A. Quast
With the usually existing temperature differenccs hctwccii thc modcl and the wind tunnel air, a temperature differcncc builds up between the laminar and the turbulent part of the model surface. As heat transfer in laminar flow is low, the laminar part keeps the model tcmpcrature. On the other hand in turbulent Ilow the hcat translcr IS high and therefore the model adopts nearly the i c q x " u r c of thc air.
由于模型和风洞空气之间通常存在温差，因此在模型表面的层流部分和湍流部分之间形成了温差。由于层流中的换热较低，层流部分保持模型温度。另一方面，在紊流状态下，hcat转换率很高，因此该模型几乎采用了空气的i / q / u / c。
{"title":"New Experiences on Transition Detection by Infrared Images","authors":"A. Quast","doi":"10.1109/ICIASF.1993.687659","DOIUrl":"https://doi.org/10.1109/ICIASF.1993.687659","url":null,"abstract":"With the usually existing temperature differenccs hctwccii thc modcl and the wind tunnel air, a temperature differcncc builds up between the laminar and the turbulent part of the model surface. As heat transfer in laminar flow is low, the laminar part keeps the model tcmpcrature. On the other hand in turbulent Ilow the hcat translcr IS high and therefore the model adopts nearly the i c q x \" u r c of thc air.","PeriodicalId":398832,"journal":{"name":"International Congress on Instrumentation in Aerospace Simulation Facilities,","volume":"1074 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-09-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116020784","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 : 1993-09-20DOI: 10.1109/ICIASF.1993.687654
Y. Chao, M.J. Lee, M. Jeng
haracteristics of flame stabilization. one another under many circumemixed” type lifted diffusion flame orne et al. and Eickhoff et al., and the influence to flame behaviors by the turbulent structures within the flow field postulated by Byggstoyl et al. and Broadwell et al. were recognized by Pitts, and he further combined them to explain the flame liftoff and blowout behaviors. Pitts [SI attempted to determind the stability behavior of turbulent jet diffusion flame by measuring the unignited cold flow characteristics such as concentration distribution and velocity profile. According to his prediction results, some accurate correlations of experimental data for liftoff heights and blowout velocities were determined. Recently, Chao and Jeng [7,8,9] investigated the stabilization of a jet diffusion flame from liffoff to blowout based on the traditional turbulent flame speed concept. And a new model of flame stabilization mechanism was derived baaed on theoretical considerations of turbulent heat transport and effect of turbulent intermittency. Moreover, Richard and Pitts 1101 measured the radial profile of the probability density function of the flammable premixture of an isothermal fuel jet at the flame base, and he recongnized , on an instantaneous basis that the mixture is seldom stoichiometric a t the flame base. However, the detailed discussion about the local turbulent mixing using the Pdf analysis has been still unaccomplished. Besides, advanced laser optical diagnostics offer important advantages in that they are non-intrusive and can prevent unacceptable perturbations to the system under study. Also, they can be used in the measurement in inaccessible environments [11]. Rayleigh scattering has been demostrated to be a powerful diagnostic tool for the measurement of local gas temperature 112,131 and concentration I14,15,10] in combustion studies. The objective of the present study is to develop the molecular Rayleigh scattering technique to investigate the probability distribution function ( pdf ) of concentration and the flame liftoff behavior. The measured pdf information together with other measurement data [Q] are applied to the newly derived lifted flame stabilization (81 to predict the flame location and flame zone structure. In addition, the dependence of the stabilization of lifted diffusion flame on the local mixing process and turbulent structures within flow field are also carefully delineated.
{"title":"An Experimental Study of the Stabilization of the Lifted Jet Diffusion Flame Using Molecular Rayleigh Scattering Technique","authors":"Y. Chao, M.J. Lee, M. Jeng","doi":"10.1109/ICIASF.1993.687654","DOIUrl":"https://doi.org/10.1109/ICIASF.1993.687654","url":null,"abstract":"haracteristics of flame stabilization. one another under many circumemixed” type lifted diffusion flame orne et al. and Eickhoff et al., and the influence to flame behaviors by the turbulent structures within the flow field postulated by Byggstoyl et al. and Broadwell et al. were recognized by Pitts, and he further combined them to explain the flame liftoff and blowout behaviors. Pitts [SI attempted to determind the stability behavior of turbulent jet diffusion flame by measuring the unignited cold flow characteristics such as concentration distribution and velocity profile. According to his prediction results, some accurate correlations of experimental data for liftoff heights and blowout velocities were determined. Recently, Chao and Jeng [7,8,9] investigated the stabilization of a jet diffusion flame from liffoff to blowout based on the traditional turbulent flame speed concept. And a new model of flame stabilization mechanism was derived baaed on theoretical considerations of turbulent heat transport and effect of turbulent intermittency. Moreover, Richard and Pitts 1101 measured the radial profile of the probability density function of the flammable premixture of an isothermal fuel jet at the flame base, and he recongnized , on an instantaneous basis that the mixture is seldom stoichiometric a t the flame base. However, the detailed discussion about the local turbulent mixing using the Pdf analysis has been still unaccomplished. Besides, advanced laser optical diagnostics offer important advantages in that they are non-intrusive and can prevent unacceptable perturbations to the system under study. Also, they can be used in the measurement in inaccessible environments [11]. Rayleigh scattering has been demostrated to be a powerful diagnostic tool for the measurement of local gas temperature 112,131 and concentration I14,15,10] in combustion studies. The objective of the present study is to develop the molecular Rayleigh scattering technique to investigate the probability distribution function ( pdf ) of concentration and the flame liftoff behavior. The measured pdf information together with other measurement data [Q] are applied to the newly derived lifted flame stabilization (81 to predict the flame location and flame zone structure. In addition, the dependence of the stabilization of lifted diffusion flame on the local mixing process and turbulent structures within flow field are also carefully delineated.","PeriodicalId":398832,"journal":{"name":"International Congress on Instrumentation in Aerospace Simulation Facilities,","volume":"69 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-09-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114693128","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 : 1993-09-20DOI: 10.1109/ICIASF.1993.687652
W. Beck, M. Muller, M. Wollenhaupt
gas flow at the species level must be iz. bulk properties are no longer these facilities to characterise the gas 0 in some cases, time resolved measurements need to be carried out so that kinetic processes such as nozzle starting and model flow development processes can be examined; 0 most important, the methods must be non-intrusive and in no way affect or influence the gas which is to be examined for this reason, many classical methods involving use of probes in the flow are not suitable. A review of nonintrusive diagnostic techniques applied to hypersonic flows has been given by Exton [I]. HEG is a free piston driven shock tunnel [2] at the DLR in Gbttingen at present undergoing commissioning tests prior to its intended use for studies on the influence of real gas effects on atmospheric reentry phenomena. Calculations of the conditions in the free stream gas flow [3] indicate that there is still a high residual kinetic and (perhaps) Boltzmann population temperature, and that the species concentrations do not mirror this temperature it is known that chemical reaction freezes quite early in the n o d e expansion. The following table gives calculated free stream conditions for a run at about 20 MJ kg-1, with diaphragm burst pressure about 50 MPa, and with air as test gas [4]:-
{"title":"Application of Spectroscopic Diagnostic Techniques to Studies on HEG: Preparatory LIF Work and Emission Spectroscopy Results","authors":"W. Beck, M. Muller, M. Wollenhaupt","doi":"10.1109/ICIASF.1993.687652","DOIUrl":"https://doi.org/10.1109/ICIASF.1993.687652","url":null,"abstract":"gas flow at the species level must be iz. bulk properties are no longer these facilities to characterise the gas 0 in some cases, time resolved measurements need to be carried out so that kinetic processes such as nozzle starting and model flow development processes can be examined; 0 most important, the methods must be non-intrusive and in no way affect or influence the gas which is to be examined for this reason, many classical methods involving use of probes in the flow are not suitable. A review of nonintrusive diagnostic techniques applied to hypersonic flows has been given by Exton [I]. HEG is a free piston driven shock tunnel [2] at the DLR in Gbttingen at present undergoing commissioning tests prior to its intended use for studies on the influence of real gas effects on atmospheric reentry phenomena. Calculations of the conditions in the free stream gas flow [3] indicate that there is still a high residual kinetic and (perhaps) Boltzmann population temperature, and that the species concentrations do not mirror this temperature it is known that chemical reaction freezes quite early in the n o d e expansion. The following table gives calculated free stream conditions for a run at about 20 MJ kg-1, with diaphragm burst pressure about 50 MPa, and with air as test gas [4]:-","PeriodicalId":398832,"journal":{"name":"International Congress on Instrumentation in Aerospace Simulation Facilities,","volume":"113 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-09-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132039272","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 : 1993-09-20DOI: 10.1109/ICIASF.1993.687674
S. Damp, E. Sommer
Ahsfrucr A concepi: for an integrable miniature signal processing unit for laser Doppler signals is presented. Its aim is to complete the existing miniature laser Doppler anemometer (as sensor head) to an LDA sensor. The colncept works in a totally new manner by using the cross-correlation for signal detection and validation. The resulting real-time histogram allows new statements about the measured process. Therefore, the concept is very suitable for universal sensor applications and gives the basis for an autonomous function. In an ASIC design signals up to 100 MHz with a time resolution of' 0.25 ns are processed in real time. The whole processing unit could be placed in a housing with 5 cm edge length and would have a power consumption of about 5 W.
{"title":"A further step to the LDA-Sensor: Concept for the Miniature Signal Processing Unit","authors":"S. Damp, E. Sommer","doi":"10.1109/ICIASF.1993.687674","DOIUrl":"https://doi.org/10.1109/ICIASF.1993.687674","url":null,"abstract":"Ahsfrucr A concepi: for an integrable miniature signal processing unit for laser Doppler signals is presented. Its aim is to complete the existing miniature laser Doppler anemometer (as sensor head) to an LDA sensor. The colncept works in a totally new manner by using the cross-correlation for signal detection and validation. The resulting real-time histogram allows new statements about the measured process. Therefore, the concept is very suitable for universal sensor applications and gives the basis for an autonomous function. In an ASIC design signals up to 100 MHz with a time resolution of' 0.25 ns are processed in real time. The whole processing unit could be placed in a housing with 5 cm edge length and would have a power consumption of about 5 W.","PeriodicalId":398832,"journal":{"name":"International Congress on Instrumentation in Aerospace Simulation Facilities,","volume":"167 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-09-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127919594","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 : 1993-09-20DOI: 10.1109/ICIASF.1993.687677
R. Barrett, J. Rickards, C. Swales, C. J. Brake
{"title":"Enhanced Performance of a Cross-Coupled 3D Laser Doppler Anemometer for Small Scale Flow Surveys Using Improved Alignment and Operational Procedures","authors":"R. Barrett, J. Rickards, C. Swales, C. J. Brake","doi":"10.1109/ICIASF.1993.687677","DOIUrl":"https://doi.org/10.1109/ICIASF.1993.687677","url":null,"abstract":"","PeriodicalId":398832,"journal":{"name":"International Congress on Instrumentation in Aerospace Simulation Facilities,","volume":"25 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-09-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124590045","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 : 1993-09-20DOI: 10.1109/ICIASF.1993.687690
P.J. Bryanslon-Cross
One objccivc of the research has bccn to image sub-micmn panicles to visualisc the instanlilncous behaviour of the flow ficld. The work has also bccn dircctcd towards lest operations which require rapid daw acquisition such as tninsicnt blow-down or facilitics with high running costs. The dcvclopincrit pcriod has also providcd an optical diagnoaic suiuble for making mcasurcmcnLs in unstcady flow regions.
{"title":"Two Application Examples of Long Range Transonic PIV (Particle Image Velocimetry) Measurements","authors":"P.J. Bryanslon-Cross","doi":"10.1109/ICIASF.1993.687690","DOIUrl":"https://doi.org/10.1109/ICIASF.1993.687690","url":null,"abstract":"One objccivc of the research has bccn to image sub-micmn panicles to visualisc the instanlilncous behaviour of the flow ficld. The work has also bccn dircctcd towards lest operations which require rapid daw acquisition such as tninsicnt blow-down or facilitics with high running costs. The dcvclopincrit pcriod has also providcd an optical diagnoaic suiuble for making mcasurcmcnLs in unstcady flow regions.","PeriodicalId":398832,"journal":{"name":"International Congress on Instrumentation in Aerospace Simulation Facilities,","volume":"15 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1993-09-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131039956","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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