Numerical Investigations On Wing-winglet Aerodynamic Performance
碩士 === 國立成功大學 === 航空太空工程學系 === 83 === A paper is proposed to investigate the aerodynamic performa- nce of transonic wings with or without using numerical methods. For the numerival methods, efforts are intended to develop and to test a finite volume metho...
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ndltd-TW-083NCKU02950132015-10-13T12:53:32Z http://ndltd.ncl.edu.tw/handle/98288339058329380304 Numerical Investigations On Wing-winglet Aerodynamic Performance 機翼與翼梢小翼空氣動力的數值探討 Bae-Yih Hwang 黃百毅 碩士 國立成功大學 航空太空工程學系 83 A paper is proposed to investigate the aerodynamic performa- nce of transonic wings with or without using numerical methods. For the numerival methods, efforts are intended to develop and to test a finite volume method for solving the solution of the three-dimensional compressible Euler equations. The finite volu- me method uses a third-order Modified Osher-Chakrovarth upwind explicit Runge-Kutta time integration with an implicit residual smoothing for time discritization. In the present study the three-dimension flows about the ON- EAR M6 wingand the NACA0012 wing are used as tests for estimati- ons. Results of the computer code developed to calculate three- dimensioncompressible flow compare well with the exprimental da- ta and the results existin codes where available. In the model study, the work emphasizes the investigations the pressure distribution of transonic wings at Mach number bet- ween 0.75 and 0.85, and the effects of the areodynamic performa- nce with the device of winglet. The main scope of the work to s- tudy the effects of using upwind extrapolations and limiter fun- tion to the numerical results, and to study the aerodynamic per- formance of the wings and the vortex flowfield downstream of the wing tip. The numerical results show that the winglet reduces t- he drag coefficients and increased th lift coefficients. The wi- ngtip pressure coeficients become more negative on the aft regi- on of the upper surface and more positime ont the lower surface because of the winglets . The tip vortex was delayed due to the winglet and reduced the strengh of tip vortex. San-Yih Lin 林三益 1995 學位論文 ; thesis 73 zh-TW |
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碩士 === 國立成功大學 === 航空太空工程學系 === 83 === A paper is proposed to investigate the aerodynamic performa-
nce of transonic wings with or without using numerical methods.
For the numerival methods, efforts are intended to develop and
to test a finite volume method for solving the solution of the
three-dimensional compressible Euler equations. The finite
volu- me method uses a third-order Modified Osher-Chakrovarth
upwind explicit Runge-Kutta time integration with an implicit
residual smoothing for time discritization. In the present
study the three-dimension flows about the ON- EAR M6 wingand
the NACA0012 wing are used as tests for estimati- ons. Results
of the computer code developed to calculate three-
dimensioncompressible flow compare well with the exprimental
da- ta and the results existin codes where available. In the
model study, the work emphasizes the investigations the
pressure distribution of transonic wings at Mach number bet-
ween 0.75 and 0.85, and the effects of the areodynamic
performa- nce with the device of winglet. The main scope of the
work to s- tudy the effects of using upwind extrapolations and
limiter fun- tion to the numerical results, and to study the
aerodynamic per- formance of the wings and the vortex flowfield
downstream of the wing tip. The numerical results show that the
winglet reduces t- he drag coefficients and increased th lift
coefficients. The wi- ngtip pressure coeficients become more
negative on the aft regi- on of the upper surface and more
positime ont the lower surface because of the winglets . The
tip vortex was delayed due to the winglet and reduced the
strengh of tip vortex.
|
author2 |
San-Yih Lin |
author_facet |
San-Yih Lin Bae-Yih Hwang 黃百毅 |
author |
Bae-Yih Hwang 黃百毅 |
spellingShingle |
Bae-Yih Hwang 黃百毅 Numerical Investigations On Wing-winglet Aerodynamic Performance |
author_sort |
Bae-Yih Hwang |
title |
Numerical Investigations On Wing-winglet Aerodynamic Performance |
title_short |
Numerical Investigations On Wing-winglet Aerodynamic Performance |
title_full |
Numerical Investigations On Wing-winglet Aerodynamic Performance |
title_fullStr |
Numerical Investigations On Wing-winglet Aerodynamic Performance |
title_full_unstemmed |
Numerical Investigations On Wing-winglet Aerodynamic Performance |
title_sort |
numerical investigations on wing-winglet aerodynamic performance |
publishDate |
1995 |
url |
http://ndltd.ncl.edu.tw/handle/98288339058329380304 |
work_keys_str_mv |
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