Bulletin of the American Physical Society
69th Annual Meeting of the APS Division of Fluid Dynamics
Volume 61, Number 20
Sunday–Tuesday, November 20–22, 2016; Portland, Oregon
Session R31: Experimental Techniques - Scalar Measurements |
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Chair: Hirotaka Sakaue, University of Notre Dame Room: F152 |
Tuesday, November 22, 2016 1:30PM - 1:43PM |
R31.00001: Temperature Distribution Measurement of The Wing Surface under Icing Conditions Hiroshi Isokawa, Takeshi Miyazaki, Shigeo Kimura, Hirotaka Sakaue, Katsuaki Morita De- or anti-icing system of an aircraft is necessary for a safe flight operation. Icing is a phenomenon which is caused by a collision of supercooled water frozen to an object. For the in-flight icing, it may cause a change in the wing cross section that causes stall, and in the worst case, the aircraft would fall. Therefore it is important to know the surface temperature of the wing for de- or anti-icing system. In aerospace field, temperature-sensitive paint (TSP) has been widely used for obtaining the surface temperature distribution on a testing article. The luminescent image from the TSP can be related to the temperature distribution. (TSP measurement system) In icing wind tunnel, we measured the surface temperature distribution of the wing model using the TSP measurement system. The effect of icing conditions on the TSP measurement system is discussed. [Preview Abstract] |
Tuesday, November 22, 2016 1:43PM - 1:56PM |
R31.00002: High Speed Pressure Sensitive Paint for Dynamic Testing Carolina Pena, Kyle Chism, Paul Hubner Pressure sensitive paint (PSP) allows engineers to obtain accurate, high-spatial-resolution measurements of pressure fields over a structure. The pressure is directly related to the luminescence emitted by the paint due to oxygen quenching. Fast PSP has a higher surface area due to its porosity compared to conventional PSP, which enables faster diffusion and measurements to be acquired three orders of magnitude faster than with conventional PSP. A fast time response is needed when testing vibrating structures due to fluid-structure interaction. The goal of this summer project was to set-up, test and analyze the pressure field of an impinging air jet on a vibrating cantilever beam using Fast PSP. Software routines were developed for the processing of the emission images, videos of a static beam coated with Fast PSP were acquired with the air jet on and off, and the intensities of these two cases were ratioed and calibrated to pressure. Going forward, unsteady pressures on a vibrating beam will be measured and presented. Eventually, the long-term goal is to integrate luminescent pressure and strain measurement techniques, simultaneously using Fast PSP and a luminescent photoelastic coating on vibrating structures. [Preview Abstract] |
Tuesday, November 22, 2016 1:56PM - 2:09PM |
R31.00003: Simultaneous measurement of temperature and velocity of air flow over 1000°C using two color phosphor thermometry Masatoshi Fukuta, Satoshi Someya, Tetsuo Munakata Thermal barrier coatings were applied to the gas turbines and the internal combustion engines for the high thermal efficiency. The evaluation and the improvement of coatings require to measure transient gaseous flow near the wall with coatings. An aim of this study is to combine a two color phosphor thermometry with the PIV to measure simultaneously temperature and velocity of the gas over 1000°C. The temperature and velocity distribution of an impinging jet of high temperature air was simultaneously visualized in experiments. The temperature was estimated from an intensity ratio of luminescent in different ranges of wavelength, 500 \textasciitilde 600 nm and 400 \textasciitilde 480 nm. Uncertainty of measured temperature was less than 10°C. Temperatures measured by the developed method and by thermocouples were agreed well. The measured velocity by the PIV with phosphor particles were also agreed well with the velocity measured by a Laser Doppler Velocimeter. [Preview Abstract] |
Tuesday, November 22, 2016 2:09PM - 2:22PM |
R31.00004: Development of molecular based optical techniques for thermometry and velocimetry for fluorocarbon media Shahram Pouya, Gary Blanchard, Manoochehr Koochesfahani Fluorocarbon solvents are very stable inert fluids with unique physical properties that make them attractive compounds as refrigerant and several medical applications such as contrast enhanced ultrasound imaging. Since they do not mix with typical organic solvents or water, most luminescent (fluorescent or phosphorescent) probes cannot be used as tracers for optical diagnostic techniques. Perfluoropentane, a compound from this family, is used as a simulant fluid by NASA for two-phase heat transfer/mixing experiments under micro-gravity condition due to its low boiling temperature. Here we study the feasibility of employing non-intrusive optical methods for measurements of temperature and/or velocity within Perfluoropentane as the working fluid. Preliminary results of temperature and velocity measurement using Laser Induced Fluorescence and Molecular Tagging Velocimetry are presented. [Preview Abstract] |
Tuesday, November 22, 2016 2:22PM - 2:35PM |
R31.00005: ABSTRACT WITHDRAWN |
Tuesday, November 22, 2016 2:35PM - 2:48PM |
R31.00006: Experimental Testing of the T-NSTAP in Supersonic Flow Katherine Kokmanian, Marcus Hultmark A fast response nanoscale temperature sensor (T-NSTAP) was developed at Princeton University. This novel sensor has been shown to increase both the spatial and the temporal resolutions compared to conventional cold-wire probes, due to its large aspect ratio yet small overall size (100 nm x 2 $\mu$m x 200 $\mu$m). The T-NSTAP has been tested in various subsonic facilities, however it has not yet been tested under supersonic conditions. Here we will present the first measurements from supersonic flows using the T-NSTAP in Princeton's Low Turbulence Variable Geometry Facility at Mach 3 and later in Princeton's Hypersonic Boundary Layer Facility (HBLF) at Mach 8 in order to enable unfiltered data of the temperature field in high speed flows. Since the HBLF can generate more challenging conditions than these probes have previously been tested in, our attention will be focused on ensuring that the T-NSTAP can withstand these conditions. Assuming that a shock will form at the front edge of the sensor, the total force on the T-NSTAP was calculated to be on the order of $\mu$N, which is less than when it was tested in subsonic pressurized conditions. Investigations will be undertaken to ensure that the structural and electrical properties of the sensors are maintained during the tests. [Preview Abstract] |
Tuesday, November 22, 2016 2:48PM - 3:01PM |
R31.00007: Dual Luminescence Imaging for Two Phase Flow Hirotaka Sakaue, Katsuaki Morita Dual luminescence imaging gives time-resolved information of fluid dynamic phenomena. It uses two luminescent probes; one is sensitive to the detecting medium and the other as a reference. It is a non-intrusive technique, and both luminescent outputs are captured by a high-speed color camera as color-filtered images. By taking a ratio of the two images at the same time frame, this imaging technique can give time-resolved information. It is suitable for a moving and free surface objects. It is also suitable for a measurement where a target is small to mount a conventional thermocouple and pressure probes. Some of the applications of this imaging are described in the presentation, such as icing and boiling phenomena. [Preview Abstract] |
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