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A literal study on the Gu-Chang (구창의 문헌연구)

  • Jung Han Sol;Park Jong Hoon;Ryuk Sang Won;Lee Kwang Gyu
    • Journal of Physiology & Pathology in Korean Medicine
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    • v.16 no.1
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    • pp.32-44
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    • 2002
  • Gu-Chang is a disorder characterized by recurring ulcers confined to the oral mucosa. Despite much clinical and research attention, the causes remain poorly understood. In this paper, we will compare Gu-Chang with Recurrent Aphthous Stomatitis(RAS) in order to know what is the similiarity between Gu-Chang and RAS. So we will arrange various oriental and western medical literatures which are important. As a result of arrangement of the causes, symptoms and therapys of Gu-Chang, we can conclude through the studies as follows. 1. The etiologies of Gu-chang are following. In the Sthenia syndrome, there are evil heat of external factor, heat of heart and spleen, insomnia, heat of upper warmer, stress and diet, heat of lung and heart, excessive heat of upper warmer, inappropriate food intake, heat conveyance of organ, heat of stomach merdian, moistured heat of spleen and stomach and stasis of liver energy. In the Asthenia syndrome, there are deficiency of stomach energy, deficiency of upper warmer leading to heat, deficiency of middle warmer leading to cold, deficiency of lower warmer leading to heat, deficiency of middle energy, deficiency of blood, decreased fire and deficiency of soil, yin fire of lower warmer, deficiency of heart yin, deficiency of spleen yin and deficiency of qi and blood. 2. In western medicine the causes of RAS is presumed as local, microbial, systemic, nutritional, genetic, immunologic factors. 3. Once Gu-chang is compared with RAS, in the deficiency of yin leading to hyperactivity of fire, deficiency of yin leading to floating of fire and stasis of liver energy, recurring of Gu-chang is similar to RAS. Although recurring of Gu-chang due to tripple warmer of excessive fire has no recurrance, since there are the degree of Pain, site of lesion, dysphagia etc, it is similar to major RAS. It is may be believed that Sthenia Gu-chang is similar to major RAS, shape of recurring, site of lesion, degrree of Pain and white color of Asthenia Gu-chang are similar to minor RAS, but there is no similarity concerning herpes RAS in the literatures that describe the symptoms. 4. Generally, the treatment of Gu-chang is divided into Asthenia and Sthenia Syndrome. The method of cure to Sthenia syndrome is heat cleaning and purge fire, Asthenia syndrome is nourish yin to lower and adverse rising energy and strength the middle warmer and benefit vital energy. 5. Following is the medication for Sthenia syndrome. Heat of heart and spleen is Do Jok San, Yang Gyek San, Juk Yup Suk Go Tang, evil heat of external factor is Yang Gyek San Ga Gam, Stasis of liver energy is Chong Wi Fae Dok Yum, moistured heat of spleen and stomach is Chong Gi Sam Syep Tang. The medication for Asthenia Syndrome is following. Deficiency of upper warmer leading to heat is Bo Jung Ik Gi Tang, deficiency of middle warmer leading to cold is Bu Ja Lee Jung Tang, deficiency of lower warmer leading to heat is Yuk Mi Ji Hwang Tang, deficiency of yin leading to hyperactivity of fire is Ji Baek Ji Hwang Hwan, deficiency of yin leading to floating of fire is Lee Jung Tang Ga Bu Ja Medicine for external use were Yang Suk San, Boo Wyen San, Rok Po San, Yoo Hwa San ate. 6. In western medicine, there is no specific treatment for RAS, and management strategies depend on dinical presentation and symptoms and includes antibiotics, oral rinses, glucocorticoids, immunomodulatory drugs, vitamines, analgesics, laser and antiviral agents.

The Vortical Flow Field of Delta Wing with Leading Edge Extension

  • Lee, Ki-Young;Sohn, Myong-Hwan
    • Journal of Mechanical Science and Technology
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    • v.17 no.6
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    • pp.914-924
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    • 2003
  • The interaction and breakdown of vortices over the Leading Edge Extension (LEX) - Delta wing configuration has been investigated through wing-surface pressure measurements, the off-surface flow visualization, and 5-hole probe measurements of the wing wake section. The description focused on analyzing the interaction and the breakdown of vortices depending on the angle of attack and the sideslip angle. The Effect of angle of attack and sideslip angle on the aerodynamic load characteristics of the model is also presented. The sideslip angle was found to be a very influential parameter of the vortex flow over the LEX-delta wing configuration. The introduction of LEX vortex stabilized the vortex flow, and delayed the vortex breakdown up to a higher angle of attack. The vortex interaction and breakdown was promoted on the windward side, whereas it was suppressed on the leeward side.

Study on the Turbulent Edge Propagation Speed of a Lifted Diffusion Flame in Turbulent Mixing Layer (난류 혼합층 확산화염에서 부상선단의 난류전파속도에 대한 연구)

  • Kim, Jun-Hong;Chung, S.H.;Ahn, K.Y.;Kim, J.S.
    • 한국연소학회:학술대회논문집
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    • 2004.11a
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    • pp.55-61
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    • 2004
  • Leading front of a lifted diffusion flame in turbulent mixing layer was investigated in order to find a appropriate definition of the turbulent edge propagation speed. The turbulent lifted diffusion flame was simulated by employing the flame hole dynamics combined with level-set method which yields a temporally evolving turbulent extinction process. By tracing the leading front locations of the temporal flame edges, temporal variations of the liftoff height, local flow velocity, and edge propagation speed at the leading front were investigated and they demonstrated the flame-stabilization condition of the turbulent lifted flame. Finally, a turbulent edge propagation speed was defined and its temporal variation from the simulation was discussed.

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An Interal Flow Analysis of Turbo Pump Inducer (터보펌프 인듀서의 내부 유동 해석)

  • Shim, Chang-Yeul;Kang, Shin-Hyoung
    • Proceedings of the KSME Conference
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    • 2001.06e
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    • pp.631-636
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    • 2001
  • The internal flow in the rocket pump inducer of LE-7 engine for H-II rocket was predicted at design and off-design flow rates using CFD code, CFX- Tascflow. In this numerical study, the performance curve of inducer coressponding to flow rates variation and the internal flow in the front of blade leading edge show good agreement between the calculations and the measurements. Backflow is appeared at suction side of leadinge edge tip, and this region is extended to upstream as flowrate decrease. Because of backflow, pressure loss coressponding to meridinal coordinate occupy 50% from inlet domain to leading edge. By this phenomena, pressure loss in front of blade leading edge take a great effect to inducer performance.

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FLAP DEELECTION OPTIMZATION FOR TRANSONIC CRUISE PERFORMANCE IMPROVEMENT OF SUPERSONIC TRANSPORT WING

  • Kim Hyoung-Jin;Obayashi Shigeru;Nakahashi Kazuhiro
    • 한국전산유체공학회:학술대회논문집
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    • 2000.10a
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    • pp.32-38
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    • 2000
  • Wing flap deflection angles of a supersonic transport are optimized to improve transonic cruise performance. For this end, a numerical optimization method is adopted using a three-dimensional unstructured Euler code and a discrete adjoint code. Deflection angles of ten flaps; five for leading edge and five fur railing edge, are employed as design variables. The elliptic equation method is adopted for the interior grid modification during the design process. Interior grid sensitivities are neglected for efficiency. Also tested is the validity of the approximate gradient evaluation method for the present design problem and found that it is applicable for loading edge flap design in cases of no shock waves on the wing surface. The BFGS method is used to minimize the drag with constraints on the lift and upper surface Mach numbers. Two design examples are conducted; one is leading edge flap design, and the other is simultaneous design of leading edge and trailing edge flaps. The latter gave a smaller drag than the former by about two counts.

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Influence of the Leading Edge Shape of a 2-Dimensional hydrofoil on Cavitation Characteristics (2차원 날개단면의 앞날 형상 변화에 따른 캐비테이션 특성 연구)

  • I.H. Song;J.W. Ahn;I.S. Moon;K.S. Kim
    • Journal of the Society of Naval Architects of Korea
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    • v.37 no.1
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    • pp.60-66
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    • 2000
  • In order to improve cavitation characteristics for a high-speed propeller, leading edge shape of a 2-D hydrofoil is investigated numerically and experimentally. For flowfield analysis around the leading edge, the incompressible Reynolds Averaged Navier-Stokes(RANS) equation is solved using the standard $k-\varepsilon$ turbulence model and a finite volume method(FVM). The cavitation thickness, which is occurred on hydrofoil surface, is predicted using the panel code. It is shown that the calculation codes predict the experimental trend fairly well. From these results, new hydrofoils are designed

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Tool Path Generation of Multi-Patch Sculptured Surface with Reparameterization (여러 개의 패치로 이루어진 곡면에서 재매개변수화를 통한 공구경로 생성)

  • 이성근
    • Journal of the Korean Society of Manufacturing Technology Engineers
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    • v.9 no.5
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    • pp.119-126
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    • 2000
  • Recently, according to the various taste of consumers, the design of a product is changed variously and complicatedly. The complicated product is not usually constructed with one path but multi-path. By the way, in machining, higher precision and the reduction of leading and machining time is required. But, for the multi-patch sculptured surface, the amount of machining data becomes large. This means the increase of leading and machining time. In this study, the tool path generation method with reparameterization is proposed for multi-patch sculptured surface and variable step size using NURBS is used to satisfy the precision and to reduce leading and machining time.

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Positional Stability Analysis of Trailing Aircraft in Formation Flight (편대비행에서 후방 항공기의 위치 안전성 분석)

  • Cho, Hwan Kee
    • Journal of the Korean Society for Aviation and Aeronautics
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    • v.24 no.2
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    • pp.19-24
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    • 2016
  • Positional stability analysis based on aerodynamic forces and induced moments of formation flight using two small aircraft models is presented. The aerodynamic force and moments of the trailing aircraft are analyzed in the aspect of flight stability. The induced moments with the change of local flow direction by wing-tip vortex from the leading aircraft can affect the flight positional stability of aircraft in closed formation flight. Aerodynamic forces and moments of trailing aircraft model are measured by 6-component internal balance at the 49 locations with vertical and lateral space between two aircraft models. Results are shown that the positional stability of trailing aircraft in formation flight can be analyzed by positional stability derivatives with vertical and lateral space. It is concluded that flying positions can be important factors for aircraft position stability due to induced aerodynamic force and moments with vertical and lateral spacing by the variation of flow pattern from the leading aircraft in formation flight.

A Study on the Development Strategy for ODM Exporting Company of OEM Exporting Company - Based on the Case Studies - (우리나라 중소 OEM 수출기업의 ODM 수출기업으로의 발전전략에 관한 연구 - 사례분석을 중심으로 -)

  • Kim, Gwi-Ok;Bae, Jung-Han
    • THE INTERNATIONAL COMMERCE & LAW REVIEW
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    • v.33
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    • pp.311-343
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    • 2007
  • At present, more than 80% export made by Korean small-medium sized companies is OEM(Original Equipment Manufacturing). But OEM export of made-in korea products has been facing limitations from 1990s. Some leading companies among those small-medium sized companies which have been fulfilling OEM export are transferring their exporting strategies to Own Brand or ODM(Original Development/Design Manufacturing) and some of their strategies successful. However, most of small-medium sized OEM exporting companies are still groping for some ways to upgrading to Own Brand or ODM exporting strategies. Therefore, this article deals with how the leading ODM exporting companies have been transferred from OEM to ODM exporting strategies. It also discusses the primary factors of success and barrier and how to develop the ODM exporting strategies based on investigating literature and interviews with the leading ODM exporting companies.

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On the Evolution of Leading Waves Generated by a Wavemaker (조파기에 의하여 발생된 선단파의 전개)

  • 박인규;최항순
    • Journal of Korean Society of Coastal and Ocean Engineers
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    • v.4 no.3
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    • pp.156-160
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    • 1992
  • The evolution of leading waves generated by a wavemaker in a two-dimensional tank has been studied. The front of wave trains can be described in general by the Schrodinger equation. In particular, when the slope of the carrier waves is steep, and hence nonlinearity becomes important, the cubic Schrodinger equation is proved to be an appropriate mathematical model. Computations are made by using the Crank-Nicolson algorithm and compared with experimental data. It is found that the numerical result predicts the evolution of leading waves fairly well and the evolution is significantly affected by nonlinearity for steep waves when kh>1.36.

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