(An) analysis of lift augmentation due to tangential blowing over round trailing-edge of circulation controlled airfoil = 순환 제어 날개꼴의 둥근 뒷전 위에서의 접선분출에 의한 양력 증대에 대한 해석

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The well-known vortex distribution method is applied to analyze the flow field around circulation controlled airfoil. To express the effect of lift augmentation due to tangential blowing over round trailing-edge of the airfoil, a new parameter ``circulation factor`` is introduced. Circulation factor is formulated by dimensional analysis with respect to proper parameters and experimental data. The flow field is solved by superposition of two potential flows; one due to uniform flow at angle of attack α and the other due to circulatory flow induced by tangential blowing, whose intensity is related to circulation factor and shape of airfoil. The calculated pressure distributions and lifts are in a good agreement with experimental data in a range of moderate angle of attack and blowing momentum coefficient not involving severe separation.
Advisors
Chang, Paul K.장극
Description
한국과학기술원 : 항공공학과,
Publisher
한국과학기술원
Issue Date
1983
Identifier
63618/325007 / 000811008
Language
eng
Description

학위논문(석사) - 한국과학기술원 : 항공공학과, 1983.2, [ v, 69 p. ]

URI
http://hdl.handle.net/10203/26562
Link
http://library.kaist.ac.kr/search/detail/view.do?bibCtrlNo=63618&flag=dissertation
Appears in Collection
AE-Theses_Master(석사논문)
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