Analysis for alleviation of flow separation on the symmetrical plane of thick airfoil with vortex generators at subsonic speed = Vortex generators 를 이용한 두꺼운 익형 대칭면에서의 아음속 박리 완화에 대한 연구

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The flow over the thick airfoil is characterized by the rapid velocity decrease toward the trailing edge, thus flow separates inevitably from the rear surface of the wing. To prevent or reduce the extent of flow separation, vortex generators are attached on the pressure recovery region of the airfoil. The main function of the vortex generators is the production of vortices trailing downstream, enhancing mixing between external flow and boundary layer. As a consequence the separation point of flow is shifted downstream delaying or preventing flow separation depending upon the vortex strength. In this thesis an analysis of flow behavior involving flow separation is carried out using a computer. It is shown qualitatively that flow separation on a thick airfoil under angle of attack can be delayed or prevented by installing the vortex generators.
Advisors
Chang, Paul K.장극
Description
한국과학기술원 : 항공공학과,
Publisher
한국과학기술원
Issue Date
1986
Identifier
64997/325007 / 000841237
Language
eng
Description

학위논문(석사) - 한국과학기술원 : 항공공학과, 1986.2, [ [iv], 59 p. ]

URI
http://hdl.handle.net/10203/26617
Link
http://library.kaist.ac.kr/search/detail/view.do?bibCtrlNo=64997&flag=dissertation
Appears in Collection
AE-Theses_Master(석사논문)
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