Analysis of lift and pitching moment of airfoil at subsonic speed affected by flap deflection involving flow separation = 아음속 유동에서 박리를 동반한 익형의 플랩의 영향을 고려한 양력과 피칭 모멘트 해석

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For the analysis of high lift system, a numerical method is presented, which is improved from Jacob``s method. From this analysis, lift and pitching moment can be obtained for multi-component airfoil system in incompressible flow. The applicability of the presented method is restricted to the field causing trailing edge separation. The potential flow calculation is based on singularity distributions (vortices and sources) on the airfoil surface. Separated flow region is simulated by outflow region, produced by source distribution on the separated part of airfoil surface. The separation point is predicted iteratively using computed results of potential flow calculation and boundary layer calculation for attached flow part. The comparison of the results of presented analysis and experiments for the airfoils of NACA 0010, NACA 2412 and NACA 4415 shows a comparatively good agreement.
Advisors
Chang, Paul K.장극
Description
항공공학과
Publisher
한국과학기술원
Issue Date
1982
Identifier
63243/325007 / 000801281
Language
eng
Description

학위논문(석사) - 항공공학과, 1982.2, [ vii, 54, [13] p. ]

Keywords

아음속류.

URI
http://hdl.handle.net/10203/26561
Link
http://library.kaist.ac.kr/search/detail/view.do?bibCtrlNo=63243&flag=dissertation
Appears in Collection
AE-Theses_Master(석사논문)
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