• Title, Summary, Keyword: Smoke-wire visualization

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Flow Visualization of Turbulent Flow around a Sphere (구(球) 주위 난류유동의 정량적 가시화)

  • Jang, Young-Il;Lee, Sang-Joon
    • 한국가시화정보학회:학술대회논문집
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    • pp.50-53
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    • 2005
  • The turbulent flow around a sphere was investigated in a streamwise meridian plane using two experimental techniques: smoke-wire flow visualization in wind tunnel at Re=5,300 and PIV measurements in a circulating water channel at Re=7,400. The smoke-wire visualization shows flow separation points near an azimuthal angle of $90^{\circ}$, recirculating flow, transition from laminar to turbulent shear layer, evolving vortex roll-up and fully turbulent eddies in the sphere wake. In addition, the mean flow pattern extracted by particle tracing method in water tunnel at Re= 14,500 reveals two distinct comparable toroidal(not closed) vortices in the recirculation region. The mean velocity field measured using a PIV technique demonstrates the detailed wake configuration of close symmetric recirculation and near-wake configuration with two toroidal vortices, reversed velocity zone and vorticity contours.

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Two Visualization Techniques Using Smoke-wire and Micro Water-droplets and Their Applications to Vortex Flows (연기선과 미세 수적을 이용한 두 가지 가시화 기법과 와류에의 적용)

  • Sohn, Myong Hwan
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.44 no.12
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    • pp.1017-1026
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    • 2016
  • The present paper describes the two off-surface visualization techniques and their application examples to vortex flows. One of the two visualization techniques is the classical smoke-wire technique, and the other is the visualization technique using the micro water-droplets generated by the home-style ultrasonic humidifier. The smoke-wire technique has the limit of air flow speed (about 5 m/sec for 0.07 mm-diameter wire) and the pollution problem, but it produces very fine and clear streak line sheet. It is applied to visualize the wing-tip vortices of a 3-dimensional wing. The micro water-droplet technique has the larger limit of air flow speed (above 10 m/sec) and is free from pollution and toxic problems compared to the smoke-wire technique. It is successfully applied to visualize the complex vortex system of a double-delta wing with an apex strake.

Visualization of Turbulent Flow around a Sphere (구 주위 난류유동에 관한 가시화 연구)

  • Jang, Young-Il;Lee, Sang-Joon
    • 유체기계공업학회:학술대회논문집
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    • pp.401-402
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    • 2006
  • The turbulent flow around a sphere was investigated using two experimental techniques: smoke-wire flow visualization in wind tunnel at Re=5300, 11000 and PIV measurements in a circulating water channel. The smoke-wire visualization shows flow separation points near an azimuthal angle of $90^{\circ}$, recirculating flow, transition from laminar to turbulent shear layer, evolving vortex roll-up and fully turbulent eddies in the sphere wake. The mean velocity field measured using a PIV technique in x-y center plane demonstrates the detailed near-wake structure such as nearly symmetric recirculation region, two toroidal vortices, laminar separation, transition and turbulent eddies. The PIV measurements of turbulent wake in y-z planes show that a recirculating vortex pair dominates the near-wake region.

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Flow Visualization of an Unsteady Airfoil at Low Reynolds Numbers (저 레이놀즈수에서 비정상 에어포일의 흐름 가시화)

  • Kim, Dong-Ha;Chang, Jo-Won
    • Journal of the Korean Society of Visualization
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    • v.4 no.2
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    • pp.51-58
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    • 2006
  • A boundary layer visualization was carried out in order to investigate the influence of Reynolds number on an oscillating airfoil. An NACA 0012 airfoil is sinusoidally pitched at the quarter chord point with oscillation amplitude of ${\pm}6^{\circ}$. A smoke-wire technique was employed to visualize the boundary layer and the near-wake. The freestream velocities are 1.98, 2.83 and 4.03m/s and corresponding chord Reynolds numbers are $2.3{\times}10^4,\;3.3{\times}10^4$, and $4.8{\times}10^4$, respectively. As the reduced frequency of K=0.1 is fixed, the corresponding frequency of an airfoil was adjusted in each case. The results reveal that the point at which the shear stress in an unsteady boundary layer separation disappears does not correspond with the position of the breakdown of the boundary layer, and that the breakdown of the boundary layer occurs further downstream.

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A Review on Swirling Flow by Using Flow Visualization Techniques in the Circular Tubes (원형관 내에서 유동가시화 기법을 이용한 선회유동에 관한 연구고찰)

  • Chang, Tae-Hyun;Doh, Deog-Hee;Lee, Kwoon-Soo
    • Journal of the Korean Society of Visualization
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    • v.8 no.3
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    • pp.12-21
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    • 2010
  • Swirling flows are found in very wide range of applications, for examples, cyclone separators, spraying machines, heat exchangers and jet pumps, ect. Relatively, little work has been done on the swirl flow using flow visualization techniques. This study deals with many visualization techniques to study on swirling flow. These techniques are related to oil films methods, smoke, dye liquids, liquid crystal, stroboscope light, smoke wire, white light, naphthalene sublimation, LDV(lase doppler Velocimetry) and PIV(particle image velocimetry). The present work has handled single, annular, carved tube, swirl expansion and swirl wake using several visualization methods in the vertical and horizontal circular tube.

Experimental and Computational Investigation of Aerodynamic Characteristics of Hovering Coleoptera

  • Saputra, Saputra;Byun, Do-Young;Yoo, Yong-Hoon;Park, Hoon-Choel;Byun, Yong-Hwan
    • Proceedings of the KSME Conference
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    • pp.384-388
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    • 2007
  • Aerodynamic characteristics of Coleoptera species of Epilachna quadricollis and Allomyrina dichotoma are experimentally and numerically investigated. Using digital high speed camera and smoke wire technique, we visualized the continuous wing kinematics and the flight motion of free-flying coleoptera. The experimental visualization shows that the elytra flapped concurrently with the main wing both in the downstroke and upstroke motions. The wing motion of Epilachna quadricollis was captured and analyzed frame by frame to identify the kinematics of the wings and to implement it in the movement of a model wing (thin plate) in the simulation. The two-dimensional simulation of Epilachna quadricollis hovering flight was performed by assuming the wing cross section shape as a thin plate, even though most of insect's wings are made of curved corrugated membrane. The effect of Reynolds number are investigated by the simulation. Meanwhile, in order to investigate the role and effect of elytra, the flow visualization of Allomyrina dichotoma was carried on using smoke wire visualization technique. Here, we confirmed that the vortex generated by elytra due to its movement is strongly influence the vortex dynamic generated by hind wings.

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An Experimental Investigation of Swirl Angle in a Horizontal Round Tube by Flow Visualization Method

  • Tae-Hyun Chang
    • Journal of Advanced Marine Engineering and Technology
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    • v.27 no.7
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    • pp.879-888
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    • 2003
  • Swirling air flow in a horizontal round tube was experimentally studied for its visualization. The present investigation deals with swirl angle, flow visualization studies and accompanying vortex core behavior by using oil smoke and a hot wire anemometer for Re = 40,000 and 50000 at X/D = 41, 59 and 71. In the swirl air flow, a vortex core was formed at high swirl intensity along the test tube. The swirl angle and the vortex core depended on the swirl intensity along the test tube. The results of swirl angles measured by flow visualization and hot wire reasonably agree with those of previous studies.

An Experimental Study on Flow Angle with Swirl in a Horizontal Circular Tube (수평 원통 관에서 선회를 동반한 유동각에 대한 실험적 연구)

  • Chang, Tae-Hyun
    • Journal of the Korean Society of Manufacturing Process Engineers
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    • v.2 no.4
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    • pp.82-87
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    • 2003
  • Flow angle with Swirl in a horizontal circular tube and a cylindrical annuli were experimentally studied for its visualization. This present investigation deals with flow angle, flow visualization studies and vortex core by using oil smoke and a hot wire anemometer for Re = 40,000 and 50000 at X/D = 41, 59 and 71 in a horizontal circular tube. In the swirl air flow, a vortex core was formed at high swirl intensity along the test tube. The flow angle and the vortex core depended on the swirl intensity along the test tube. The results of flow angles with swirl measured by flow visualization and hot wire reasonably agree with those of Sparrow One of the primary objectives of this research was to measure the flow angle with swirl in a cylindrical annuli along the test tube for different Reynolds numbers. The Reynolds number for these measurements ranged from 60,000 to 100,000 with L/D = a to 4.

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Flow Visualization on the Bio-Mimic Model of Dragonfly (잠자리 모사 모형 주변의 유동가시화 실험)

  • Yun, Jun-Yong;Uhm, Sang-Jin;Ji, Young-Moo;Park, Jun-Sang
    • Journal of the Korean Society of Visualization
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    • v.8 no.2
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    • pp.16-22
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    • 2010
  • A flow visualization has been conducted to investigate unsteady flight characteristics of a model of dragonfly. The mechanism of lift generation by flapping wings is analyzed using smoke-wire and high speed camera. The experimental results of flow visualization show a discernible sequential dynamics that three mechanisms and high incidence angle of the wings are responsible for the lift generation. The leading edge vortex by the rapid acceleration of leading edge of the wing during initial stage of stroke causes a strong lift enhancement. Delayed stall during the stroke, fast supination and pronation of the wing near the end of each stroke are also responsible for the lift generation.

Visualization Study on a Reduced Frequency of a Dragonfly type wing (잠자리 유헝 날개의 무차원 진동수에 따른 가시화 연구)

  • Kim Song Hak;Chang Jo Won
    • Journal of the Korean Society of Visualization
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    • v.2 no.2
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    • pp.58-65
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    • 2004
  • The purpose of this visualization study is to investigate the effect of reduced frequency qualitatively by examining wake patterns for dragonfly flight motion. Dragonflies have two pairs of wing (a forewing and hindwing) and flight is achieved by a pitching and plunging, so it makes a separation over the wings. The separation affects the wake pattern and changed wake pattern has an influence on lift, drag, and propulsion. This experiment was conducted by using a smoke wire technique and a camera fixed above the test section used to take a photograph of the wake. An electronic device is mounted below the test section to find the exact mean positional angle of the wing. The reduced frequency in the experiment is 0.15, 0.3 and 0.45. Results show that reduced frequency is closely related to the wake pattern that determines flight efficiency.

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