Mixing Process in the Jet Flows of Lobed Nozzles
|
|
- Magdalene Hodge
- 6 years ago
- Views:
Transcription
1 Proceedings of VSJ-SPIE98 December 6-9,998,Yokohama, JAPA AB Mixing Process in the Jet Flows of Lobed ozzles Hu Hui, Toshio Kobayashi, Tetsuo Saga, obuyuki Taniguchi and Shigeki Segawa Institute of Industrial Science, University of Tokyo 7-- Roppongi, Tokyo 6, Japan Abstract: An experimental investigation on the mixing enhancement of the jet flow by using lobed nozzles had been conducted. The techniques of Laser Induced Fluoresce (LIF) and Particle Image Velocimetry (PIV) were used to accomplish the flow visualization, quantitative concentration measurements and velocity field measurements. The experimental results showed that, compared with a circular jet flow, lobed jet flows were found to have shorter laminar regions, smaller scale of the spanwise Kelvin-Helmholtz vortices, earlier appearance of small scale turbulent structures and thicker mixing layers in the near field of the jet flow. Bigger high-turbulent-intensity regions and faster central line velocity decay were also found in the lobed jet flows than that in a circular jet flow. All these indicted the better mixing enhancement performance of lobed nozzles over a conventional circular nozzle. Keywords: Jet Mixing Flow, Mixing Enhancement, Lobed ozzle, PIV technique and LIF technique ITRODUCTIO A lobed nozzle, which consists of a splitter plate with a convoluted trailing edge, is an extraordinary fluid mechanic device for efficient mixing of two co-flow streams with different velocity, temperature and/or spices. It has been paid great attention by many researchers in recent years and has also been widely applied to the aerospace engineering. For examples, on the commercial aero-engines, such as JT8D-7C, CFM56-5C and RB-5G/H (which are widely used in Boeing and Airbus airplanes), lobed nozzles had been used to reduce take-off jet noise and Specific Fuel Consumption (SFC) (Tillman et al., 99, Presz et al., 99, and Hu Hui et al. 996). In order to reduce the infrared radiation signals of the military aircraft to improve their survivability in the modern war, lobed nozzles had also been used to enhance the mixing process of the high temperature and high speed gas plume from air-engine with ambient cold air (Power et al., 99). Such as military helicopter "Tiger" developed by German-France, American RAH-66 "Comanche" and stealth Fighter F-7. More recently, lobed nozzles had also emerged as attractive approaches for enhancing mixing between fuel and air in combustion chambers to improve the efficiency of combustion and reduce the formation of the pollutant (Smith et al., 997). The large scale streamwise vortices generated by lobed nozzles had been suggested to be the reason for their good mixing enhancement performance by many researchers, such as Paterson, (98), Werle et al., (987), McCormick et al. (99) and Belovich et al., (997). Although these previous researches had got many important results, much work still need in order to understand the jet mixing enhancement by using lobed nozzles more clearly. In particular about the vortical and turbulent structures changes in the jet flow caused by lobed nozzles. In the meanwhile, most of these previous researches were conducted by using Pitot probe, Laser Doppler Velocimetry (LDV) or Hot film Anemeter (HFA), which are very hard to reveal the vortical and turbulent structures in jet mixing flows instantaneously and globally due to the limitation of these experimental techniques. While, in the present study, both Laser Induced Fluorescence (LIF) and Particle Image Velocimetry (PIV) technique were used to research the lobed jet mixing flows globally and instantaneously. By using the directly perceived flow visualization images and the quantity distributions of the scalar field (concentration field and field) and vector field (velocity field), the jet mixing enhancement capability of the lobed nozzles were discussed in detail. EXPERIMETAL SYSTEM AD TECHIQUES. Experimental system Figure shows the schematically experimental facility used in the present research. The tested nozzles were stalled in the middle of the water channel (55mm*55mm*6mm). Fluorescent dye (Rhodamine B) for LIF or PIV tracers (polystyrene particles of d=5um) was premixed with the water in the jet supply tank, and jet flow was supplied by a pump. The flowrate of the jet flow, which was used to calculate the representative velocity and Reynolds numbers of the jet flow, was measured by a flow meter. A honeycomb structure was installed in the entrance of the tested nozzle to insure the uniform flow entrance. A beam of argon ion laser (wavelength is nm and output power is w) passed an optical system to form a plane sheet (thickness of the laser sheet is about.5 mm). The investigated area (8mm by 8mm) was focused on a CCD camera (SOY-AVC-D7) and then, recorded by Laser Videodisc Recorder (SOY LVR-5). The shutter of the CCD camera was set at /5s, and the framing rate was frames per second. Each frame consisted of two images, which resulted in 6 recorded images per second. The images were digitized by an 8-bit gray-scale image processing system (EXUS 9) at a spatial resolution of 6 by 8 pixels (corresponded about. pixel/mm), which also can be stored to a PC (host computer) and displayed on a PC monitor. Copyright 998 by VSJ
2 water tank Laser sheet Laser beam optical system CCD camera mixing region comb structure laser flow meter tested nozzle Image process system jet supply tank pump monitor Host computer Figure. Experimental Setup Figure shows the four tested nozzles: a baseline circular nozzle A and three lobed nozzles with different lobe numbers. Lobed nozzle B has 6 lobe structures, while lobed nozzle C has lobe structures with very sharp lobe trough. The lobed nozzle D, which was the combination the lobed nozzle B and lobed nozzles C, has 9 lobe structures. All the lobed nozzles were designed to have the same lobe structure geometric parameters, i.e., the same lobe height H=5 mm, lobe width W=6 mm, inner penetration angle degree and outer penetration angle degree. The equivalent diameters of these tested nozzles at exit were the same, D=mm. During the experiment, the flow visualization and quantitative flow field measurements in two specific axial slices (passing the peak and trough of lobe, Fig. (e)) of the lobed jet flow were conducted. In the present study, the jet velocity was.m/s, and the Reynolds umber of the jet flows, based on the nozzles exit diameter, were about 6,. Z X Z Y outer penetration angle a. circular nozzle A b. lobed nozzle B lobe heigth H=5mm lobe width W= 6mm inner penetration angle c. lobed nozzle C lobe trough slice lobe peak slice d. lobed nozzle D e. two tested axial slices Figure. The tested nozzles and studied axial slices. Experimental Techniques Laser Induced Fluorescence (LIF) and Particle Image Velocimetry (PIV) techniques are both modem fluid experimental techniques. They can offer many advantages for the study the fluid mechanics over the other conventional experimental techniques. Such as: they can reveal the global structures of the flow field instantaneously and qualitatively without disturbing the flow field, which are very useful and necessary for the research of mixing layers and other complex flows. A lot of the researches on the fluid mechanics by using LIF and PIV techniques had been conducted and many promising results had been obtained in recent years (Yoda et al., 99, and Adrian, 99). In the present research, both of the LIF technique and PIV technique were used to study the mixing enhancement performance of lobed nozzles. In the present research, Rhodamine B was used as fluorescent dye. The peak of absorption spectrum of Rhodamine B occurs at 5l7.5mn, while fluorescence spectrum peak is 59nm (Fig. (a)). During the experiment, the fluorescent light was separated form the scattered light (wavelength is nm) with an optical filter. It was well known that, only the solution of the fluorescent dye with low concentration can insure the strength of fluorescent light being linear with the concentration of the fluorescent dye and the effect of laser light attenuation is negligible as the laser light sheet propagated through the flow. This also was verified by the calibration profile of the fluorescent light intensity versus the concentration of the Rhodamine B shown on Fig.(b). In the present study, the concentration of the Rhodamine B solution in the jet supply box is.mg/l. Copyright 998 by VSJ
3 .8.6 (I-Ib)/(I-Ib) Laser power=high Laser power=middle Laser power=low Theory Value.. C/C, C=.mg/l a. emission and absorption spectrum of Rhodamine B b. LIF calibration profile Figure. Spectrum of Rhodamine B and LIF calibration profiles To obtain fluid velocities by using PIV, two or more images of seeded flow fields are captured digitally at successive points in time, and comparison of these images allows the velocity fields to be constructed. In the present study, rather than tracking individual particle, the cross correlation method (Willert et al., 99) was used to obtain the average particles displacement of the ensemble of particles. In the PIV image processing, the images were divided into by 5 pixel interrogation regions. A 5 pixel in X direction (radical direction) and pixel in Y direction (jet flow direction) step size were used which resulted in 67% overlapping of the adjacent interrogation. The studied flow fields were represented by a discrete flow fields containing about velocity vectors ( by 5), The post-processing procedures which including sub-pixel interpolation (Hu Hui et al. 998) and velocity outliner deletion (Zhou et al., 996) were used to improve the accuracy of the PIV measurements. In the present study, both instantaneous flow fields and mean flow fields were used for analysis and discussion. The instantaneous flow fields were the flow field captured by CCD camera at frequency of Hz, and every instantaneous frame (two images) was used to get the instantaneous velocity fields. continue frames were used to compute the mean flow field. RESULTS AD DISCUSSIOS ). LIF results The results of visualizations and instantaneous concentration field measurements of the jet mixing flows by using LIF were shown in Fig. and Fig5. From the figures, it can be seen that: for a circular jet flow (Fig.), three different regions, which are laminar region, transition region and turbulent region, can be identified clearly in the figure, and which is similar to the results reported by Liepmann et al. (99). At the end of laminar region (=l.), spanwise Kelvin-Helmholtz vortices were found to roll up. The pairing and combining of these spanwise vortices were conducted in the transition region. In the downstream of =., the small scale mixing (low concentration region) began to occur and much small-scale turbulence and vortical structures began to appear in the flow field. Figure 5.(a) shows the results of the flow visualization and instantaneous concentration field measurement in the axial slice of the lobe trough for the lobed nozzle B. Compared with the circular jet flow (Fig. ), the jet flow of lobed nozzle B at this axial slice was found to have a shorter laminar region (=.). The scale of the spanwise Kelvin-Helmholtz vortices of the jet flow was much smaller. The transition region in which the pairing and combining process of the spanwise vortices were accomplished also became shorter. In the downstream of the location =.8, much small scale mixing and small scale turbulent structures (low concentration region) were found to appear. Figure. Instantanous concentration distribution in the circular jet flow Copyright 998 by VSJ
4 a. in the lobe trough slice b. in the lobe peak slice Figure 5. Instantanous concentration distribution in the lobed jet flow of lobed nozzle B Figure 5.(b) shows the result of the flow visualization and instantaneous concentration field measurements in the axial slice of the lobe peak for the lobed nozzle B. From the figure, it can be seen that: the laminar region was not a straight cylinder like the circular jet shown in the Fig., and looked like a expansive cut-off cone along the downstream of the lobed structure. Compared with the flow structures shown in Fig.5(a), the "clean" laminar region in the lobe peak axial slice was a bit longer (=.), but it was still shorter than that in the circular jet flow. This is caused by the different thickness of the boundary layer at the exit of the lobed nozzle (the work of the Brink et al.(99) had verified that the thickness of the boundary layer at the lobed trough is smaller than that in the lobed peak), and the thicker boundary layer at the lobe peak need a longer stream wise distance to roll-up the Kelvin-Helmholtz vortices (Hussain et al., 989). In this axial slice, it also can be seen that smallscale mixing and small-scale turbulent structure (low concentration region) were found to appear in the down stream of location =.8. The mean concentration (C i,j ) fields and the root-mean-square () value distributions of the concentration fields for the circular jet flow and the lobed jet flows were shown on Fig. 6, Fig. 7 and Fig.8. The mean concentration fields and the rootmean-square () value distributions of the concentration fields showed on these figures were got by the average of frames of the instantaneous flow fields, and they were defined as: c i, j, t Ci j =, ( ci, j, t Ci, j ) t =, r. m. si, j = t= In which c i,j,t is the instantaneous concentration of the jet flows, while the =. For the mean concentration field, it can be seen that the circular jet flow (Fig. 6 (a)) was found to have a longer and bigger high concentration region (red color region, which indicted the unmixed region) than that in the lobed jet flows (Fig.7(a), Fig.7(c), Fig.8(a) and Fig.8(c)). In the meanwhile, the thickness of the mixing layers (the yellow color region on these figures) in the circular jet flow was also found to be thinner in the near field of the jet flows. From the root-mean-square value distributions of the concentration fields for the circular jet flow and the lobed jet flows, it can also be seen that, corresponding to the unmixed high concentration region (red color region) shown on the mean concentration fields, there were lower value regions in the center of the circular jet flow and lobed jet flows. In the circular jet flow (Fig 6(b)), this lower value region was found to be bigger than that in the lobed jet flows (Fig. 7(b), Fig. 7(d), Fig. 8(b) and Fig.8(d)). In the lobed jet flows, the higher value regions (yellow color regions on the figures), which indicated the location of extensive mixing process occurring, were found to be much bigger than that in the circular jet flow. All these LIF results indicted that the lobed nozzles had much better mixing enhancement performances than the conventional circular nozzle. From the comparison of the Fig. 7 and Fig. 8, it can be suggested that, the lobed nozzle B have a better mixing performance than the lobed nozzle C. This may be explained by that, as mentioned in the above, the lobed nozzle B and lobed nozzle C were designed to have the same lobe structure geometrical parameters, and only the lobe number of them is different. The lobed nozzle C has lobe structures, which results that the lobe troughs of the lobed nozzle C was much sharper than the lobed nozzle B. The sharper lobe troughs will cause the decreasing of the effective height of the lobe structure. This will result in the scale reduction of the streamwise vortices generated by the lobe structures. (The researches of the Presz et al.(99) and Werle et al.(987) had suggested that the scale of the streamwise vortices generated by the lobe structures is equivalent to the effective height of the lobed structures). This resulted in that the mixing enhancement performance of the lobed nozzle C is not as good as the lobed nozzle B, which will also be verified, in the following PIV results. Copyright 998 by VSJ
5 concentration a. mean concentration field b. root-mean-square value distribution Figure 6. Mean concentration and root-mean-square value of the concentration field in the circular jet flow concentration a.mean concentration field (lobe peak slice) b. root-mean-square value distribution(lobe peak slice) concentration c.mean concentration field(lobe trough slice) d.root-mean-square value distribution(lobe trough slice) Figure 7. Mean concentration and value distribution of the concentration field of the lobed jet flow (lobed nozzle B) 5 Copyright 998 by VSJ
6 concentration a. mean concentration field (lobed peak slice) b. root-mean-square value distribution (lobed peak slice) concentartion c. mean concentration field (lobed trough slice) d. root-mean-square value distribution (lobed trough slice) Figure 8. Mean concentration and. value distribution of the concentration field in the lobed jet flow (lobed nozzle C) ). PIV results The PIV measurement results of the circular jet flow and lobed jet flows were showed in the Fig. 9 to Fig. which included mean velocity fields and mean fields in the circular jet flow and the axial slices of lobe peak and lobe trough of the lobed jet flows. As motioned above, the mean velocity fields and mean fields showed on these figures were got by the average of frames of the instantaneous flow fields. The mean velocity (Ui,j and Vi,j )and mean Tij shown on these figures were defined as: u i, j,t t = U i, j = Ti, j = (u ' vi, j,t t = Vi, j = i, j, t +v ' i, j,t ).5 t = = In which =, ui,j,t and vi,j,t are the instantaneous velocities in the X and Y direction, while u'i,j,t and v'i,j,t are the instantaneous turbulent velocities. (u t = i, j,t U i, j ) + (vi, j, t Vi, j ).5 - i = Figure 9. Mean velocity and distribution in the circular jet flow 6 Copyright 998 by VSJ
7 a. in the lobe trough slice b. in the lobe peak slice Figure. Mean velocity and distribution in the lobed jet flow. (lobed nozzle B) a. in the lobe trough slice b. in the lobe peak slice Figure. Mean velocity and distribution in the lobed jet flow. (lobed nozzle C) For the nature jet flow (Fig.9), between two higher region (yellow color region, which corresponding the mixing layers in the nature jet flow), a low region (blue color region, which represent the potential core region of the jet flow) was found in the center of the nature jet flow. However, in the lobed jet flows (Fig. and Fig.), the low regions (blue color region) was much smaller. In the meanwhile, most of the high regions (yellow color region) were found to concentrate in the near field of the lobed jet flows, which means the most of the mixing was completed in the near field of the lobed jet flows. While, in the circular jet flow, its high regions expend much downstream. From the comparison of the Fig. and Fig., it can be seen that, in the jet flow of lobed nozzle B (Fig.), the high region will be bigger than that in the jet flow of lobed nozzle C (Fig.). The low intensity region in the center of the jet flow was found to be smaller and shorter in the jet flow of lobed nozzle B than that in the lobed nozzle C. The conclusion of the lobed nozzle B had a better jet mixing enhancement performance than the lobed nozzle C can also be suggested from the PIV results, which verified the above LIF results circu lar n ozzle A lobed nozzle B.8 5 lobed nozzle C.8 lobed nozzle D.7 5 Y /D Figure.. The central line velocity decay of the circular jet flow and lobed jet flows 7 Copyright 998 by VSJ
8 In order to give a more quantitative comparison of the mixing enhancement performance of the lobed nozzles with the conventional circular nozzle, the central line velocity decay performance the circular jet flow and lobed jet flows were given on the Fig.. From the figure it can be seen that, the central line velocity of the circular jet flow almost keeps in constant in the measurement region (<.). While, for the lobed jet flows, the central line velocity was found to begin to decay in the downstream of =.5. This means that the length of the potential core region of the lobed jet flows is about / to / of the circular jet flow. Among the three tested lobed nozzles, the central line velocity in the jet flow of the lobed nozzle B was found to decay fastest. The lobed nozzle C, which has lobe structure and sharper lobe trough, was found to have slowest central line velocity decay, which also verified the results suggested in the above analysis. The lobed nozzle D, which was the combination of lobed nozzle B and lobed nozzle C, is in the gap between the lobed nozzle B and lobed nozzle C. SUMMURY From the above LIF and PIV results, it can be seen that, compared with a circular jet flow, lobed jet flows were found to have shorter laminar instability regions, smaller scale of the spanwise Kelvin-Helmholtz vortices, earlier appearance of the small scale turbulent structures. The thicker mixing layers and bigger high-turbulent-intensity regions were also found in the near fields of the lobed jet flows. In the meanwhile, the lobed nozzles can reduce the potential core region length of the jet flows to / ~ / of that in the circular jet flow. All these indicated the mixing enhancement performances of lobed nozzles over a circular nozzle. From the comparison results of the three tested lobed nozzles, it can also be suggested that, the lobe configuration has an important effects on the mixing efficiency of the jet flows, and it must be properly considered in the optimism design of a lobed nozzle. It should be pointed out that the present experiment research was conducted at a very low speed. Some detailed differences are expected at higher speed case. However, it can be expected that the gross mixing enhancement of a lobed nozzle over a circular nozzle would be very similar at both low and high-speed flows. ACKOWLEDGMETS The authors appreciate the helpful discussions and advisable suggestions from Prof. Wu Shousheng and Prof. Shen Gongxin of Beijing University of Aeronautics and Astronautics, P. R. China. The research fellowship provided by Japan Society for Promotion of Science (JSPS) to the first author and the supported for the Original Industrial Technology R&D Promotion Program from the ew Energy and Industrial Technology Development Organization (EDO) of Japan are also grateful acknowledged. REFERECE Adrian R. J., 99 "Particle-Imaging Techniques for Experimental Fluid Mechanics", Ann Rev. Fluid Mech. Vlo., (99), pp 6-. Belovich V. M. and Samimy M, "Mixing Process in a Coaxial Geometry with a Central Lobed Mixing ozzle" AIAA Journal, Vol.5 o.5, pp88-8l (997) Brink B.K.and Foss J.F., "Enhancement Mixing via Geometric Manipulation of a Splitter Plate" AIAA 9- (99) Hu Hui, Liu Huoxing and Wu Shousheng, "Experimental Investigation on the Aerodynamic Performance of the -D Lobed Exhaust Ejector System" ASME 96-GT- (996) Hu Hui, Saga. T., Kobayashi T., Okamoto K. and Taniguchi.," Evaluation of the Cross Correlation Method by Using PIV Standard Images", Journal of Visualization, Vol., o., pp87-9 (998). Hussain F. and Husain H.S., "Elliptic jets. Part : Characteristics of unexcited and excited jets" J.Fluid Mech. Vol.8, PP57- (989) Liepmann D. and Gharib M., "The Role of Streamwise Vorticity in the ear Field Entrainment of Round Jets", J. Fluid Mech. Vol. 5, pp6-668 (99). McCormick D. C. and Bennett J.C.Jr. "Vortical and Turbulent Structure of a Lobed Mixer Free Shear Layer" AIAA9-l9 (99). Paterson R. W., "Turbofan Forced Mixer ozzle Internal Flowfield." ASA-CR-9 (98). Power G. D., McClure M. D. and Vinh D., "Advanced IR Suppresser Design Using A Combined CFD/Test Approach", AIAA9-l5 (99). Presz W.M. Jr, Renyolds G. and McCormick D., "Thrust Augmentation Using Mixer-Ejector-Diffuser Systems"AIAA9- (99). Smith L.L, Majamak A.J., Lam I.T. Delabroy O., Karagozian A.R., Marble F.E. and Smith, O. I., "Mixing Enhancement in a Lobed Injector" Phys. Fluids, Vol.9, o., PP (997) Tillman T.G. and Presz W. M. Jr, "Thrust Characteristics of a Supersonic Mixing Ejector" AIAA9-5 (99) Werle M.J., Paterson R. W. and Presz Jr. W. M., "Flow Structure in a Periodic Axial Vortex Array" AIAA 87-6l (987). Willert C. E. and Gharib M., "Digital Particle Image Velocimetry" Experiments in Fluids, Vol.l, ppl8l-l99 (99). Yoda M., Hesselink L. and Mungal M. G., "Instantaneous Three Dimensional Concentration Measurement in the Self Similar Region of a Round High-Schmidt umber Jet", J. Fluid Mech., Vol.79, ppl-5 (99). Zhou M. and Garner. C. P., "Particle Image Velocimetry measurements of the flow field within an enclosed rotating disk-stator system and comparisons." Optical Diagnostics in Engineering, Vol. Part (996). 8 Copyright 998 by VSJ
Proceedings of 3rd International Workshop on PIV, Santa Barbara, USA, Sep.16-18, 1999 PIV and LIF Measurements on the Lobed Jet Mixing Flows
Proceedings of rd International Workshop on PIV, Santa Barbara, USA, Sep.68, 999 PIV and LIF Measurements on the Lobed Jet Mixing Flows Hui HU, Toshio KOBAASHI, Tetsuo SAGA, Shigeki SEGAWA and Nobuyuki
More informationRESEARCH ON THE MIXING ENHANCEMENT PERFORMANCE OF LOBED NOZZLES BY USING PIV AND LIF
Proceedings of FEDSM 98 1998 ASME Fluids Engineering Division Summer Meeting June 21-25,1998, Washington, DC FEDSM98-4994 RESEARCH ON THE MIXING ENHANCEMENT PERFORMANCE OF LOBED NOZZLES BY USING PIV AND
More informationMixing Process in the Jet Flow of Lobed Nozzle
Proceeding of 99 Korea-Japan Joint Seminar on Particle Image Velocimetry pp9-5 Mixing Process in the Jet Flow of Lobed Nozzle Tetsuo SAGA, Hui HU and Toshio KOBAASHI Institute of Industrial Science, University
More informationPASSIVE CONTROL ON JET MIXING FLOWS BY USING VORTEX GENERATORS
Proceedings of the Sixth Triennial International Symposium on Fluid Control, Measurement and Visualization, Sherbrooke, Canada, August -7,. PASSIVE CONTROL ON JET MIXING FLOWS BY USING VORTEX GENERATORS
More informationSIMULTANEOUS VELOCITY AND CONCENTRATION MEASUREMENTS OF A TURBULENT JET MIXING FLOW
Proceedings of International Symposium on Visualization and Image in Transport Phenomena, Turkey, -9 Oct. SIMULTANEOUS VELOCITY AND CONCENTRATION MEASUREMENTS OF A TURBULENT JET MIXING FLOW Hui HU a, Tetsuo
More informationSimultaneous Velocity and Concentration Measurements of a Turbulent Jet Mixing Flow
Simultaneous Velocity and Concentration Measurements of a Turbulent Jet Mixing Flow HUI HU, a TETSUO SAGA, b TOSHIO KOBAYASHI, b AND NOBUYUKI TANIGUCHI b a Department of Mechanical Engineering, Michigan
More informationChanges to the vortical and turbulent structure of jet flows due to mechanical tabs
321 Changes to the vortical and turbulent structure of jet flows due to mechanical tabs H Hui1*, T Kobayashi1, SWu2 and G Shen2 12nd Department, Institute of Industrial Science, University of Tokyo, Japan
More informationRESEARCH ON THE SELF-INDUCED SLOSHING PHENOMENA IN A RECTANGULAR TANK
9TH. INTERNATIONAL SYMPOSIUM ON FLOW VISUALIZATION, RESEARCH ON THE SELF-INDUCED SLOSHING PHENOMENA IN A RECTANGULAR TANK Tetsuo SAGA, Hui HU, Toshio KOBAYASHI Shigeki SEGAWA and Nobuyuki TANIGUCHI Keywords:
More informationStereoscopic PIV Measurement of a Jet Flow with Vortex Generating Tabs
The th International Symposium on Flow Visualization August -,, Kyoto, Japan F Stereoscopic PIV Measurement of a Jet Flow with Vortex Generating Tabs Hui HU* 1, Toshio KOBAASHI *, Tetsuo SAGA* and Nubuyuki
More informationVisualization of Multi-scale Turbulent Structure in Lobed Mixing Jet Using Wavelets
2001 The Visualization Society of Japan and Ohmsha, Ltd. Journal of Visualization, Vol. 4, No. 3 (2001) 231-238 Visualization of Multi-scale Turbulent Structure in Lobed Mixing Jet Using Wavelets Li, H.*
More informationA PIV Study on the Self-induced Sloshing in a Tank with Circulating Flow
Proceeding of PSFVIP-2 May 16-19, 1999, Honolulu, USA PF152 A PIV Study on the Self-induced Sloshing in a Tank with Circulating Flow Hu Hu Toshio Kobayash Tetsuo Saga, Shigeki Segawa and obuyuki Taniguchi
More informationA Comparative Study of the PIV and LDV Measurements on a Self-induced Sloshing Flow
2000 The Visualization Society of Japan and Ohmsha, Ltd. Journal of Visualization, Vol. 3, No.2 (2000) 145-156 A Comparative Study of the PIV and LDV Measurements on a Self-induced Sloshing Flow Saga,
More informationThe Effects of Scalloping Width and Position on Jet Mixing of Lobed Nozzles
doi: 10.5028/jatm.v7i4.519 The Effects of Scalloping Width and Position on Jet Mixing of Lobed Nozzles Liu Dawei 1, Huang Jun 1, Sheng Zhiqiang 1, Ji Jinzu 1 Abstract: A series of geometric models of lobed
More informationNumerical Simulation of the Vortical Structures in a Lobed Jet Mixing Flow
Numerical Simulation of the Vortical Structures in a Lobed Jet Mixing Flow Nathan J. Cooper * and Parviz Merati Department of Mechanical and Aeronautical Engineering, Western Michigan University, Kalamazoo,
More informationTHE EFFECT OF SAMPLE SIZE, TURBULENCE INTENSITY AND THE VELOCITY FIELD ON THE EXPERIMENTAL ACCURACY OF ENSEMBLE AVERAGED PIV MEASUREMENTS
4th International Symposium on Particle Image Velocimetry Göttingen, Germany, September 7-9, 00 PIV 0 Paper 096 THE EFFECT OF SAMPLE SIZE, TURBULECE ITESITY AD THE VELOCITY FIELD O THE EXPERIMETAL ACCURACY
More informationMixing Augmentation by Multiple Lobed Jets
American Journal of Fluid Dynamics 2015, 5(2): 55-64 DOI: 10.5923/j.ajfd.20150502.03 Mixing Augmentation by Multiple Lobed Jets N. K. Depuru Mohan 1,*, K. R. Prakash 2, N. R. Panchapakesan 3 1 Department
More informationFLOW-FIELD OF A 12-LOBE CONVOLUTED MIXER
24 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES FLOW-FIELD OF A 12-LOBE CONVOLUTED MIXER Leiyong Jiang, Ibrahim Yimer and W.E. Carscallen Gas Turbine Environmental Research Centre Institute for
More informationMixing Enhancement of Coaxial Jet with Arrayed Flap Actuators for Active Control of Combustion Field
Proceedings of the 2nd Symposium on Smart Control of Turbulence, Tokyo, Japan, March 4-6, 2001. Mixing Enhancement of Coaxial Jet with Arrayed Flap Actuators for Active Control of Combustion Field Naoki
More informationFLOW VISUALIZATION AND SIMULTANEOUS VELOCITY AND TEMPERATURE MEASUREMENTS IN THE WAKE OF A HEATED CYLINDER
TH INTERNATIONAL SYMPOSIUM ON FLOW VISUALIZATION August -,, University of Notre Dame, Notre Dame, Indiana, USA FLOW VISUALIZATION AND SIMULTANEOUS VELOCITY AND TEMPERATURE MEASUREMENTS IN THE WAKE OF A
More informationUnderexpanded Sonic Jets: A PIV Study
Underexpanded Sonic Jets: A PIV Study K. Bülent Yüceil Istanbul Technical University, Faculty of Aeronautics and Astronautics, 866 Maslak, Istanbul, Turkey M. Volkan Ötügen Polytechnic University, Dept.
More informationThis is the published version of a paper presented at Healthy Buildings 2017 Europe, Lublin, Poland.
http://www.diva-portal.org This is the published version of a paper presented at Healthy Buildings 2017 Europe, Lublin, Poland. Citation for the original published paper: Kabanshi, A., Sattari, A., Linden,
More informationPIV study for the analysis of planar jets in cross-flow at low Reynolds number
PIV study for the analysis of planar jets in cross-flow at low Reynolds number Vincenti I., Guj G., Camussi R., Giulietti E. University Roma TRE, Department of Ingegneria Meccanica e Industriale (DIMI),
More informationINITIAL CONDITION EFFECTS ON KELVIN-HELMHOLTZ INSTABILITIES AND DEVELOPMENT OF A ROUND JET
INITIAL CONDITION EFFECTS ON KELVIN-HELMHOLTZ INSTABILITIES AND DEVELOPMENT OF A ROUND JET Amy B. McCleney and Philippe M. Bardet The George Washington University 800 22 nd St NW, Washington, D.C. 20037
More informationActive Control of Turbulence and Fluid- Structure Interactions
Bonjour! Active Control of Turbulence and Fluid- Structure Interactions Yu Zhou Institute for Turbulence-Noise-Vibration Interaction and Control Shenzhen Graduate School, Harbin Institute of Technology
More informationExperimental investigation of flow control devices for the reduction of transonic buffeting on rocket afterbodies
Experimental investigation of flow control devices for the reduction of transonic buffeting on rocket afterbodies F.F.J. Schrijer 1, A. Sciacchitano 1, F. Scarano 1 1: Faculty of Aerospace Engineering,
More informationCHARACTERISTICS OF ELLIPTIC CO-AXIAL JETS
ELECTRIC POWER 2003 March 4-6, 2003 George R Brown Convention Center, Houston, TX EP 03 Session 07C: Fuels, Combustion and Advanced Cycles - Part II ASME - FACT Division CHARACTERISTICS OF ELLIPTIC CO-AXIAL
More informationInstrumentation. Dr. Hui Hu Dr. Rye Waldman. Department of Aerospace Engineering Iowa State University Ames, Iowa 50011, U.S.A
AerE 344 Lecture Notes Lecture # 05: elocimetry Techniques and Instrumentation Dr. Hui Hu Dr. Rye Waldman Department of Aerospace Engineering Iowa State University Ames, Iowa 500, U.S.A Sources/ Further
More informationArticle published by EDP Sciences and available at or
http://www.emath.fr/proc/vol.1/ Three-Dimensional Vorticity Dynamics in a Coowing Turbulent Jet Subjected to Axial and Azimuthal Perturbations Katherine Prestridge and Juan C. Lasheras Department of Applied
More informationExperimental Analysis on Incompressible circular and noncircular Fluid Jet through Passive Control Method
IOSR Journal of Mechanical and Civil Engineering (IOSR-JMCE) e-issn: 2278-1684, p-issn : 2320 334X PP 15-21 www.iosrjournals.org Experimental Analysis on Incompressible circular and noncircular Fluid Jet
More informationNear and far field experimental investigation on the structure of an isothermal lobed jet
Proceedings of the th WSEAS International Conference on Fluid Mechanics and Aerodynamics, Elounda, Greece, August -, (pp-) Near and far field eperimental investigation on the structure of an isothermal
More informationExperimental Study on the Non-reacting Flowfield of a Low Swirl Burner
Experimental Study on the Non-reacting Flowfield of a Low Swirl Burner Hang Yin & Ren Dai School of Energy and Powering Engineering, University of Shanghai for Science and Technology Box 25, 516# Jungong
More informationQuantum Dots (DQ) Imaging for Thermal flow studies
AerE 545 class notes #43 Quantum Dots (DQ) Imaging for Thermal flow studies Hui Hu Department of Aerospace Engineering, Iowa State University Ames, Iowa 511, U.S.A Quantum Dots Quantum dots are chemically
More informationShear instabilities in a tilting tube
Abstract Shear instabilities in a tilting tube Edmund Tedford 1, Jeff Carpenter 2 and Greg Lawrence 1 1 Department of Civil Engineering, University of British Columbia ttedford@eos.ubc.ca 2 Institute of
More informationComputational Investigations of High-Speed Dual-Stream Jets
9th AIAA/CEAS Aeroacoustics Conference and Exhibit -4 May 3, Hilton Head, South Carolina AIAA 3-33 Computational Investigations of High-Speed Dual-Stream Jets Nicholas J. Georgiadis * National Aeronautics
More informationScienceDirect. Gas flow visualization using laser-induced fluorescence
Available online at www.sciencedirect.com ScienceDirect Procedia Engineering 106 (2015 ) 92 96 Dynamics and Vibroacoustics of Machines (DVM2014) Gas flow visualization using laser-induced fluorescence
More informationEvolution of the pdf of a high Schmidt number passive scalar in a plane wake
Evolution of the pdf of a high Schmidt number passive scalar in a plane wake ABSTRACT H. Rehab, L. Djenidi and R. A. Antonia Department of Mechanical Engineering University of Newcastle, N.S.W. 2308 Australia
More informationDesign of an Acoustically Excited Jet for Laser Diagnostics Development
Design of an Acoustically Excited Jet for Laser Diagnostics Development Michael A. Willis * Auburn University, Auburn, Alabama, 36849 An acoustically excited jet facility has been designed, constructed
More informationMixing at the External Boundary of a Submerged Turbulent Jet
Mixing at the External Boundary of a Submerged Turbulent Jet A. Eidelman, T. Elperin, N. Kleeorin, I. Rogachevskii, I. Sapir-Katiraie The Ben-Gurion University of the Negev, Beer-Sheva, Israel G. Hazak
More informationAN UNSTEADY AND TIME-AVERAGED STUDY OF A GROUND VORTEX FLOW
24 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES AN UNSTEADY AND TIME-AVERAGED STUDY OF A GROUND VORTEX FLOW N J Lawson*, J M Eyles**, K Knowles** *College of Aeronautics, Cranfield University,
More informationNear Field Measurements of an Axisymmetric Turbulent Jet at Low Reynolds Numbers: A PIV and CTA Comparison
Near Field Measurements of an Axisymmetric Turbulent Jet at Low Reynolds Numbers: A PIV and CTA Comparison 1 Brian D. Landers, 2 Peter J. Disimile 1,2 Department of Aerospace Engineering, University of
More informationEXPERIMENTAL INVESTIGATION ON THE NONCIRCULAR INCOMPRESSIBLE JET CHARACTERISTICS
EXPERIMENTAL INVESTIGATION ON THE NONCIRCULAR INCOMPRESSIBLE JET CHARACTERISTICS S. Venkata Sai Sudheer 1, Chandra Sekhar K 2, Peram Laxmi Reddy 3 1,2 Assistant Professor, Mechanical Engineering, CVR College
More informationWhite Paper FINAL REPORT AN EVALUATION OF THE HYDRODYNAMICS MECHANISMS WHICH DRIVE THE PERFORMANCE OF THE WESTFALL STATIC MIXER.
White Paper FINAL REPORT AN EVALUATION OF THE HYDRODYNAMICS MECHANISMS WHICH DRIVE THE PERFORMANCE OF THE WESTFALL STATIC MIXER Prepared by: Dr. Thomas J. Gieseke NUWCDIVNPT - Code 8233 March 29, 1999
More informationLaser-Induced Iodine Fluorescence Applied to Confined Supersonic Mixing
Laser-Induced Iodine Fluorescence Applied to Confined Supersonic Mixing Marc Havermann French-German Research Institute Saint-Louis (ISL) 5, Rue du Général Cassagnou, F-68301 Saint-Louis, France ABSTRACT
More informationFigure 1. Schematic of experimental setup.
June 3 - July 3, Melbourne, Australia 9 9D- STRUCTURE OF 3D OFFSET JETS OVER A SURFACE MOUNTED SQUARE RIB Shawn P. Clark Department of Civil Engineering 7A Chancellors Circle, Winnipeg, Manitoba, R3T V,
More informationApplied Mathematics and Mechanics (English Edition) Transition control of Mach 6.5 hypersonic flat plate boundary layer
Appl. Math. Mech. -Engl. Ed., 40(2), 283 292 (2019) Applied Mathematics and Mechanics (English Edition) https://doi.org/10.1007/s10483-019-2423-8 Transition control of Mach 6.5 hypersonic flat plate boundary
More informationInhomogeneous Mixing Behavior of Recirculated Exhaust Gas in a Lean Premixed Flame
Inhomogeneous Mixing Behavior of Recirculated Exhaust Gas in a Lean Premixed Flame 2nd Japan-China Joint Seminar July 11, 2016, Gifu University, Japan Masaharu Komiyama Department of Mechanical Engineering
More informationNUMERICAL PREDICTIONS AND EXPERIMENTS ON SUPERSONIC JET MIXING FROM CASTELLATED NOZZLES
ICAS CONGRESS NUMERICAL PREDICTIONS AND EXPERIMENTS ON SUPERSONIC JET MIXING FROM CASTELLATED NOZZLES A. J. Saddington, N. J. Lawson, K. Knowles Aeromechanical Systems Group Department of Aerospace, Power
More informationTRACKING OF THERMAL STRUCTURES FROM INFRARED CAMERA BY PIV METHOD
9TH. INTERNATIONAL SYMPOSIUM ON FLOW VISUALIZATION, 2000 TRACKING OF THERMAL STRUCTURES FROM INFRARED CAMERA BY PIV METHOD T. A. Kowalewski 2, G. Hetsroni 1, B. Hu 1, A. Mosyak 1 Keywords: infrared thermography,
More informationFEDSM COMPUTATIONAL AEROACOUSTIC ANALYSIS OF OVEREXPANDED SUPERSONIC JET IMPINGEMENT ON A FLAT PLATE WITH/WITHOUT HOLE
Proceedings of FEDSM2007: 5 th Joint ASME/JSME Fluids Engineering Conference July 30-August 2, 2007, San Diego, CA, USA FEDSM2007-37563 COMPUTATIONAL AEROACOUSTIC ANALYSIS OF OVEREXPANDED SUPERSONIC JET
More informationVisualization of Xe and Sn Atoms Generated from Laser-Produced Plasma for EUV Light Source
3rd International EUVL Symposium NOVEMBER 1-4, 2004 Miyazaki, Japan Visualization of Xe and Sn Atoms Generated from Laser-Produced Plasma for EUV Light Source H. Tanaka, A. Matsumoto, K. Akinaga, A. Takahashi
More informationExperiments on the perturbation of a channel flow by a triangular ripple
Experiments on the perturbation of a channel flow by a triangular ripple F. Cúñez *, E. Franklin Faculty of Mechanical Engineering, University of Campinas, Brazil * Correspondent author: fernandodcb@fem.unicamp.br
More informationVisualization of high-speed gas jets and their airblast sprays of cross-injected liquid
Short communications Experiments in Fluids 27 (1999) 102 106 Springer-Verlag 1999 Visualization of high-speed gas jets and their airblast sprays of cross-injected liquid K. D. Kihm, T. K. Kim, S. Y. Son
More informationPlanar Laser-Induced Iodine Fluorescence Technique for Flow Visualization and Quantitative Measurements in Rarefied Flows
Planar Laser-Induced Iodine Fluorescence Technique for Flow Visualization and Quantitative Measurements in Rarefied Flows Professor James McDaniel*, Eric Cecil*, Erin Reed* and Josh Codoni* Professor Iain
More informationSUPERSONIC JET CONTROL WITH INTERNAL GROOVES
Proceedings of the International Conference on Mechanical Engineering 2005 (ICME2005) 28-30 December 2005, Dhaka, Bangladesh ICME05- SUPERSONIC JET CONTROL WITH INTERNAL GROOVES Shafiqur Rehman 1, M. Jamil
More informationJournal of Fluid Science and Technology
Bulletin of the JSME Vol.9, No.3, 24 Journal of Fluid Science and Technology Re-evaluating wake width in turbulent shear flow behind an axisymmetric cylinder by means of higher order turbulence statistics
More informationFLOW MEASUREMENT. INC 102 Fundamental of Instrumentation and Process Control 2/2560
FLOW MEASUREMENT INC 102 Fundamental of Instrumentation and Process Control 2/2560 TABLE OF CONTENTS A. INTRODUCTION B. LOCAL FLOW MEASUREMENT B.1 Particle Image Velocimetry (PIV) B.2 Laser doppler anemometry
More informationLaser Doppler Velocimetry (LDV) Part - 01
AerE 545 class notes #21 Laser Doppler Velocimetry (LDV) Part - 01 Hui Hu Department of Aerospace Engineering, Iowa State University Ames, Iowa 50011, U.S.A Techniques for Flow Velocity Measurements Intrusive
More informationA MHZ RATE IMAGING SYSTEM FOR STUDY OF TURBULENT AND TIME EVOLVING HIGH SPEED FLOWS
A MHZ RATE IMAGING SYSTEM FOR STUDY OF TURBULENT AND TIME EVOLVING HIGH SPEED FLOWS B. Thurow, J. Hileman, M. Samimy, and W. Lempert Department of Mechanical Engineering The Ohio State University Columbus,
More informationComputational Fluid Dynamics Analysis of Jets with Internal Forced Mixers
Computational Fluid Dynamics Analysis of Jets with Internal Forced Mixers L. A. Garrison A. S. Lyrintzis G. A. Blaisdell Purdue University, West Lafayette, IN, 47907, USA W. N. Dalton Rolls-Royce Corporation,
More informationEffects of Under Expansion Level on Sonic Turbulent Jets Propagation
American Journal of Fluid Dynamics 2015, 5(3A): 12-18 DOI: 10.5923/s.ajfd.201501.02 Effects of Under Expansion Level on Sonic Turbulent Jets Propagation Mrinal Kaushik 1,*, Prashanth Reddy Hanmaiahgari
More informationLaser Induced Fluorescence (LIF) Technique Part - 3
AerE 545 class notes #37 Laser Induced Fluorescence (LIF) Technique Part - 3 Hui Hu Department o Aerospace Engineering, Iowa State University Ames, Iowa 500, U.S.A Introduction Instantaneous, quantitative,
More informationINFLUENCE OF ACOUSTIC EXCITATION ON AIRFOIL PERFORMANCE AT LOW REYNOLDS NUMBERS
ICAS 2002 CONGRESS INFLUENCE OF ACOUSTIC EXCITATION ON AIRFOIL PERFORMANCE AT LOW REYNOLDS NUMBERS S. Yarusevych*, J.G. Kawall** and P. Sullivan* *Department of Mechanical and Industrial Engineering, University
More information25 years of PIV development for application in aeronautical test facilities
25 years of PIV development for application in aeronautical test facilities Jürgen Kompenhans and team Department Experimental Methods Institute of Aerodynamics and Flow Technology German Aerospace Center
More informationPIV measurements of cold flow field in a partially premixed bluff body burner M. Dutka, 1, M. Ditaranto 2, T. Løvås 1
PIV measurements of cold flow field in a partially premixed bluff body burner M. Dutka, 1, M. Ditaranto 2, T. Løvås 1 1 Department of Energy and Process Engineering, Norwegian University of Science and
More informationJournal of Fluid Science and Technology
Science and Technology LDV and PIV Measurements of the Organized Oscillations of Turbulent Flow over a Rectangular Cavity* Takayuki MORI ** and Kenji NAGANUMA ** **Naval Systems Research Center, TRDI/Ministry
More informationTURBINE BURNERS: Engine Performance Improvements; Mixing, Ignition, and Flame-Holding in High Acceleration Flows
TURBINE BURNERS: Engine Performance Improvements; Mixing, Ignition, and Flame-Holding in High Acceleration Flows Presented by William A. Sirignano Mechanical and Aerospace Engineering University of California
More informationPIV Applications to Thermal Performance of LPG
PIV Applications to Thermal Performance of LPG Cooking Burner BY USA MAKMOOL And PROF.SUMRERNG JUGJAI Assoc. PROF. SUVIT TIA 1. Rational/ Problem Statement LPG consumption of Household sector (Thailand,
More informationA Stereoscopic PIV Study of a Near-field Wingtip Vortex
48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition 4-7 January 21, Orlando, Florida AIAA 21-129 A Stereoscopic PIV Study of a Near-field Wingtip Vortex Hirofumi
More informationAEROACOUSTIC INVESTIGATION OF THE EFFECT OF A DETACHED FLAT PLATE ON THE NOISE FROM A SQUARE CYLINDER
Abstract AEROACOUSTIC INVESTIGATION OF THE EFFECT OF A DETACHED FLAT PLATE ON THE NOISE FROM A SQUARE CYLINDER Aniket D. Jagtap 1, Ric Porteous 1, Akhilesh Mimani 1 and Con Doolan 2 1 School of Mechanical
More informationFlow Control around Bluff Bodies by Attached Permeable Plates
Flow Control around Bluff Bodies by Attached Permeable Plates G. M. Ozkan, H. Akilli Abstract The aim of present study is to control the unsteady flow structure downstream of a circular cylinder by use
More informationFlow Characteristics around an Inclined Circular Cylinder with Fin
Lisbon, Portugal, 7- July, 28 Flow Characteristics around an Inclined Circular Cylinder with Fin Tsuneaki ISHIMA, Takeshi SASAKI 2, Yoshitsugu GOKAN 3 Yasushi TAKAHASHI 4, Tomio OBOKATA 5 : Department
More informationEffect of blowing rate on the film cooling coverage on a multi-holed plate: application on combustor walls
Effect of blowing rate on the film cooling coverage on a multi-holed plate: application on combustor walls P. Miron 1,2, C. Berat 1 & V. Sabelnikov 3 1 TURBOMECA-Bordes, France 2 LaTEP, Université de Pau
More informationExperimental characterization of flow field around a square prism with a small triangular prism
Journal of Mechanical Science and Technology 29 (4) (2015) 1649~1656 www.springerlink.com/content/1738-494x OI 10.1007/s12206-015-0336-2 Experimental characterization of flow field around a square prism
More information18th International Symposium on the Application of Laser and Imaging Techniques to Fluid Mechanics LISBON PORTUGAL JULY 4 7, 2016.
Multiple-eye PIV Eisaku Atsumi 1, Jun Sakakibara 2,* 1: Graduate School of Science and Technology, Meji university 2: Department of Mechanical Engineering, Meji university * Correspondent author: sakakiba@meiji.ac.jp
More informationPerformance improvement of propulsion systems by optimization of the mixing efficiency and pressure loss of forced mixers
Paper presented at the 8. European Propulsion Forum Affordability and the Environment Key Challenges for Propulsion in the 2 st Century 26.-28. March 200 in Nottingham Abstract Performance improvement
More informationComparison between Numerical and Experimental for UVP Measurement in Double Bent Pipe with Out-of-Plane Angle
Journal of Flow Control, Measurement & Visualization, 24, 2, 54-64 Published Online October 24 in SciRes. http://www.scirp.org/journal/jfcmv http://dx.doi.org/.4236/jfcmv.24.247 Comparison between Numerical
More informationPIV STUDY OF LONGITUDINAL VORTICES IN A TURBULENT BOUNDARY LAYER FLOW
ICAS CONGRESS PIV STUDY OF LONGITUDINAL VORTICES IN A TURBULENT BOUNDARY LAYER FLOW G. M. Di Cicca Department of Aerospace Engineering, Politecnico di Torino C.so Duca degli Abruzzi, 4 - I 19 Torino, ITALY
More informationLIQUID FILM THICKNESS OF OSCILLATING FLOW IN A MICRO TUBE
Proceedings of the ASME/JSME 2011 8th Thermal Engineering Joint Conference AJTEC2011 March 13-17, 2011, Honolulu, Hawaii, USA AJTEC2011-44190 LIQUID FILM THICKNESS OF OSCILLATING FLOW IN A MICRO TUBE Youngbae
More informationA. Aleksandrov, H. Bockhorn
Experimental Investigation of the impact of imposed air inlet velocity oscillations on Soot Formation and Oxidation using an advanced 2-Colour-TIRE-LII A. Aleksandrov, H. Bockhorn Engler-Bunte-Institute,
More informationEXPERIMENTS OF CLOSED-LOOP FLOW CONTROL FOR LAMINAR BOUNDARY LAYERS
Fourth International Symposium on Physics of Fluids (ISPF4) International Journal of Modern Physics: Conference Series Vol. 19 (212) 242 249 World Scientific Publishing Company DOI: 1.1142/S211945128811
More informationDynamics of Large Scale Motions in Bubble-Driven Turbulent Flow
Dynamics of Large Scale Motions in Bubble-Driven Turbulent Flow Kyung Chun Kim School of Mechanical Engineering, Pusan National University Jangjeon-dong, Geumjeong-gu, Pusan, 609-735, Korea kckim@pusan.ac.kr
More informationVisualization of Traveling Vortices in the Boundary Layer on a Rotating Disk under Orbital Motion
Open Journal of Fluid Dynamics, 2015, 5, 17-25 Published Online March 2015 in SciRes. http://www.scirp.org/journal/ojfd http://dx.doi.org/10.4236/ojfd.2015.51003 Visualization of Traveling Vortices in
More informationNew optical tools for fluid mechanics
Sddhangt, Vol. 23, Parts 5 & 6, Oct & Dec 1998, pp. 557-567. Indian Academy of Sciences New optical tools for fluid mechanics G E A MEIER DLR-Institute for Fluid Mechanics, Bunsenstrasse 10, D-37073 G6ttingen,
More informationPIV measurements and convective heat transfer of an impinging air jet
PIV measurements and convective heat transfer of an impinging air jet by T. S. O Donovan (), D. B. Murray () and A.A. Torrance (3) Department of Mechanical & Manufacturing Engineering, Trinity College
More informationVORTICITY FIELD EVOLUTION IN A FORCED WAKE. Richard K. Cohn Air Force Research Laboratory Edwards Air Force Base, CA 92524
Proceedings of the st International Symposium on Turbulence and Shear Flow Phenomena, Santa Barbara, CA, Sep. 5, 999, Eds. Banerjee, S. and Eaton, J. K., pp. 9-96. VORTICITY FIELD EVOLUTION IN A FORCED
More informationPROPERTIES OF THE FLOW AROUND TWO ROTATING CIRCULAR CYLINDERS IN SIDE-BY-SIDE ARRANGEMENT WITH DIFFERENT ROTATION TYPES
THERMAL SCIENCE, Year, Vol. 8, No. 5, pp. 87-9 87 PROPERTIES OF THE FLOW AROUND TWO ROTATING CIRCULAR CYLINDERS IN SIDE-BY-SIDE ARRANGEMENT WITH DIFFERENT ROTATION TYPES by Cheng-Xu TU, a,b Fu-Bin BAO
More informationApplied Fluid Mechanics
Applied Fluid Mechanics 1. The Nature of Fluid and the Study of Fluid Mechanics 2. Viscosity of Fluid 3. Pressure Measurement 4. Forces Due to Static Fluid 5. Buoyancy and Stability 6. Flow of Fluid and
More informationApplied Fluid Mechanics
Applied Fluid Mechanics 1. The Nature of Fluid and the Study of Fluid Mechanics 2. Viscosity of Fluid 3. Pressure Measurement 4. Forces Due to Static Fluid 5. Buoyancy and Stability 6. Flow of Fluid and
More informationThe Effect of Endplates on Rectangular Jets of Different Aspect Ratios
The Effect of Endplates on Rectangular Jets of Different Aspect Ratios M. Alnahhal *, Th. Panidis Laboratory of Applied Thermodynamics, Mechanical Engineering and Aeronautics Department, University of
More informationLARGE-SCALE COHERENT TURBULENCE STRUCTURES IN A COMPRESSIBLE MIXING LAYER FLOW
LARGE-SCALE COHERENT TURBULENCE STRUCTURES IN A COMPRESSIBLE MIXING LAYER FLOW J. Poggie Wright Laboratory, WPAFB, OH A. J. Smits Princeton University, Princeton, NJ December 22, 2009 Abstract Detailed
More informationAdvances in Fluid Mechanics and Heat & Mass Transfer
Performance Study of Nozzle Geometry on Heat Transfer Characteristics Part I: Local Heat Transfer M. Attalla Mechanical Power and Energy Department, Faculty of Engineering, South Valley University, Qena
More informationStudy of Thermal Stratification in a Natural Convection Loop by One Color Laser Induced Fluorescence
Study of Thermal Stratification in a Natural Convection Loop by One Color Laser Induced Fluorescence Chiara Spaccapaniccia 1,*, Zeinep E. Yildirim 2,Philippe Planquart 3, Jean-Marie Buchlin 4 1,3,4: Environmental
More informationACTIVE SEPARATION CONTROL ON A SLATLESS 2D HIGH-LIFT WING SECTION
26th INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES ACTIVE SEPARATION CONTROL ON A SLATLESS 2D HIGH-LIFT WING SECTION F. Haucke, I. Peltzer, W. Nitsche Chair for Aerodynamics Department of Aeronautics
More informationOn the aeroacoustic tonal noise generation mechanism of a sharp-edged. plate
On the aeroacoustic tonal noise generation mechanism of a sharp-edged plate Danielle J. Moreau, Laura A. Brooks and Con J. Doolan School of Mechanical Engineering, The University of Adelaide, South Australia,
More informationMixing in Circular and Non-circular Jets in Crossflow
Downloaded from orbit.dtu.dk on: Nov 8, 218 Mixing in Circular and Non-circular Jets in Crossflow Salewski, Mirko; Stankovic, D.; Fuchs, L. Published in: Flow, Turbulence and Combustion Link to article,
More informationAvailable online at ScienceDirect. Procedia Engineering 99 (2015 )
Available online at www.sciencedirect.com ScienceDirect Procedia Engineering 99 (5 ) 6 APISA4, 4 Asia-Pacific International Symposium on Aerospace echnology, APISA4 Effect of Combustion Heat Release on
More informationTitle mixing with a rapid chemical reacti. Citation PHYSICS OF FLUIDS (2002), 14(12): 4.
Title The effects of high-frequency ultra mixing with a rapid chemical reacti Author(s) Ito, Y; Nagata, K; Komori, S Citation PHYSICS OF FLUIDS (2002), 14(12): 4 Issue Date 2002-12 URL http://hdl.handle.net/2433/39781
More informationINFLUENCE OF MICROJET INJECTION ON SUPERSONIC JET NOISE AND FLOW FIELD
Proceedings of ASME Turbo Expo 2011 GT2011 June 6-10, 2011, Vancouver, British Columbia, Canada P GT2011-46150 INFLUENCE OF MICROJET INJECTION ON SUPERSONIC JET NOISE AND FLOW FIELD Ryuichi Okada School
More informationDetailed Outline, M E 320 Fluid Flow, Spring Semester 2015
Detailed Outline, M E 320 Fluid Flow, Spring Semester 2015 I. Introduction (Chapters 1 and 2) A. What is Fluid Mechanics? 1. What is a fluid? 2. What is mechanics? B. Classification of Fluid Flows 1. Viscous
More informationPreliminary Study of the Turbulence Structure in Supersonic Boundary Layers using DNS Data
35th AIAA Fluid Dynamics Conference, June 6 9, 2005/Toronto,Canada Preliminary Study of the Turbulence Structure in Supersonic Boundary Layers using DNS Data Ellen M. Taylor, M. Pino Martín and Alexander
More information