Design and Numerical Study on Aerodynamics Performance for F16 Leading Edge Extension

碩士 === 國立成功大學 === 航空太空工程學系 === 106 === In this research, we use commercial software, ANSYS CFX, to carry out the simulations of the F16 aerodynamics flow fields. The flight with a modified Leading Edge Extension (LEX) is proposed to increase the lift/drag ratio. The Shear Stress Transport k-ω turbul...

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Bibliographic Details
Main Authors:	Hsien-HaoTeng, 鄧先浩
Other Authors:	San-Yih Lin
Format:	Others
Language:	zh-TW
Published:	2018
Online Access:	http://ndltd.ncl.edu.tw/handle/r53785

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spelling	ndltd-TW-106NCKU52950182019-05-16T01:07:58Z http://ndltd.ncl.edu.tw/handle/r53785 Design and Numerical Study on Aerodynamics Performance for F16 Leading Edge Extension F16翼前緣延伸設計空氣動力學特性之數值研究 Hsien-HaoTeng 鄧先浩碩士國立成功大學航空太空工程學系 106 In this research, we use commercial software, ANSYS CFX, to carry out the simulations of the F16 aerodynamics flow fields. The flight with a modified Leading Edge Extension (LEX) is proposed to increase the lift/drag ratio. The Shear Stress Transport k-ω turbulent model is used. The unstructured grid system is generated by the ICEM CFD. The prism grid system around the wall surface is generated to simulate boundary layer viscosity flow field and Tetrahedron Mesh is used for the other computation domain. The lift, drag, and pitch moment are computed. The strong vortex structures upper the wing and vortex bursts under different sweep angle of LEX are investigated. San-Yih Lin 林三益 2018 學位論文 ; thesis 110 zh-TW
collection	NDLTD
language	zh-TW
format	Others
sources	NDLTD
description	碩士 === 國立成功大學 === 航空太空工程學系 === 106 === In this research, we use commercial software, ANSYS CFX, to carry out the simulations of the F16 aerodynamics flow fields. The flight with a modified Leading Edge Extension (LEX) is proposed to increase the lift/drag ratio. The Shear Stress Transport k-ω turbulent model is used. The unstructured grid system is generated by the ICEM CFD. The prism grid system around the wall surface is generated to simulate boundary layer viscosity flow field and Tetrahedron Mesh is used for the other computation domain. The lift, drag, and pitch moment are computed. The strong vortex structures upper the wing and vortex bursts under different sweep angle of LEX are investigated.
author2	San-Yih Lin
author_facet	San-Yih Lin Hsien-HaoTeng 鄧先浩
author	Hsien-HaoTeng 鄧先浩
spellingShingle	Hsien-HaoTeng 鄧先浩 Design and Numerical Study on Aerodynamics Performance for F16 Leading Edge Extension
author_sort	Hsien-HaoTeng
title	Design and Numerical Study on Aerodynamics Performance for F16 Leading Edge Extension
title_short	Design and Numerical Study on Aerodynamics Performance for F16 Leading Edge Extension
title_full	Design and Numerical Study on Aerodynamics Performance for F16 Leading Edge Extension
title_fullStr	Design and Numerical Study on Aerodynamics Performance for F16 Leading Edge Extension
title_full_unstemmed	Design and Numerical Study on Aerodynamics Performance for F16 Leading Edge Extension
title_sort	design and numerical study on aerodynamics performance for f16 leading edge extension
publishDate	2018
url	http://ndltd.ncl.edu.tw/handle/r53785
work_keys_str_mv	AT hsienhaoteng designandnumericalstudyonaerodynamicsperformanceforf16leadingedgeextension AT dèngxiānhào designandnumericalstudyonaerodynamicsperformanceforf16leadingedgeextension AT hsienhaoteng f16yìqiányuányánshēnshèjìkōngqìdònglìxuétèxìngzhīshùzhíyánjiū AT dèngxiānhào f16yìqiányuányánshēnshèjìkōngqìdònglìxuétèxìngzhīshùzhíyánjiū
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Design and Numerical Study on Aerodynamics Performance for F16 Leading Edge Extension

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