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| DC 欄位 | 值 | 語言 |
|---|---|---|
| dc.contributor.advisor | 周逸儒 | zh_TW |
| dc.contributor.advisor | Yi-Ju Chou | en |
| dc.contributor.author | 邱德耀 | zh_TW |
| dc.contributor.author | Te-Yao Chiu | en |
| dc.date.accessioned | 2023-08-15T16:56:12Z | - |
| dc.date.available | 2023-11-09 | - |
| dc.date.copyright | 2023-08-15 | - |
| dc.date.issued | 2023 | - |
| dc.date.submitted | 2023-08-02 | - |
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| dc.identifier.uri | http://tdr.lib.ntu.edu.tw/jspui/handle/123456789/88583 | - |
| dc.description.abstract | 本研究探討了在攻角為7.5度和10度、雷諾數為50,000的條件下，擬序結構在NACA0012上氣動力之影響。使用譜本徵正交分解(SPOD)演算法識別擬序結構，並利用力元理論量化其對阻力和升力的影響。在7.5度攻角下，第一個SPOD模態的第零個頻率對應的流場為一遵循再附著流(reattachment flow)軌跡之近牆流動(near-wall stream)，而第一個頻率則對應於在流場重新附著的位置處所形成的逆時針渦旋對。第一個SPOD模態的第二頻率對應於在源於重新附著點(reattachment point)附近的剪切層中較小的逆時針渦旋對。在攻角為10度時，第一個SPOD模態的第零個頻率具有一個大型漩渦結構，它在翼型的上半部產生強烈的流動，對阻力和升力會產生重要影響。第一個SPOD模態的第一個頻率代表一個非對稱的渦旋對，而第二個頻率則由一系列控制前緣分離的渦旋對所組成。最後，在第二個SPOD模態的第零個頻率，翼型尾緣附近的順時針前緣分離渦旋對對阻力產生正貢獻，而逆時針前緣分離渦旋對對阻力產生負貢獻。本研究結果表明，擬序結構對於NACA0012翼型產生的氣動力力有顯著影響並且可使用SPOD演算法和力元理論有效地進行識別和量化。 | zh_TW |
| dc.description.abstract | The present study investigated the aerodynamic forces exerted by coherent structures on the NACA0012 airfoil at two different angles of attack (AoA=7.5 and AoA=10) and a chord-based Reynolds number of 50,000. The spectral proper orthogonal decomposition (SPOD) algorithm was employed to identify the coherent structures, and the force representation theory was used to quantify their impact on drag and lift forces. At an angle of attack of 7.5 degrees, the zeroth frequency of the first mode corresponded to an oscillating near-wall stream that follows the reattachment flow pattern, while the first frequency corresponded to a counter-rotating vortex pair originating where the flow reattaches. The second frequency of the first mode corresponded to smaller counter-rotating vortex pairs at the shear layer originated near the reattachment point. At an angle of attack of 10 degrees, the zeroth frequency of the first SPOD mode was found to have a large vortex structure that causes a strong flow along the suction side of the airfoil and results in a significant impact on drag and lift forces. The first frequency of the first SPOD mode represented an asymmetric vortex pair, while the second frequency of the first SPOD mode consisted of a series of vortex pairs that determine the leading-edge separation. Finally, for the zeroth frequency of the second SPOD mode, a clockwise primary LEV near the trailing edge of the airfoil provided a positive contribution to drag, while a counterclockwise LEV provided a negative contribution. The findings suggest that coherent structures have a significant impact on the aerodynamic forces exerted on airfoils and can be effectively identified and quantified using the SPOD algorithm and force element theory. | en |
| dc.description.provenance | Submitted by admin ntu (admin@lib.ntu.edu.tw) on 2023-08-15T16:56:12Z No. of bitstreams: 0 | en |
| dc.description.provenance | Made available in DSpace on 2023-08-15T16:56:12Z (GMT). No. of bitstreams: 0 | en |
| dc.description.tableofcontents | Verification Letter from the Oral Examination Committee i
Acknowledgements iii 摘要 v Abstract vii Contents ix List of Figures xv List of Tables xxvii Nomenclature xxix Chapter 1 Introduction 1 1.1 Low-Reynolds number flows pass an airfoil 1 1.2 Advancements in force representation theory 5 1.3 Techniques for extractions of coherent structures in turbulent flows 7 1.4 Dissertation overview 10 Chapter 2 Mathematical formulations 15 2.1 Governing equations of fluid motion 15 2.2 Turbulence modeling 18 2.2.1 Direct numerical simulation (DNS) 19 2.2.2 Reynolds-averaged Navier-Stokes equations (RANS) 21 2.2.3 Large-eddy simulation (LES) 25 2.3 Force representation theory 30 2.3.1 Introduction to force representation theory 30 2.3.2 Derivation of force representation theory 33 Chapter 3 Proper orthogonal decomposition (POD) 41 3.1 Overview 41 3.2 Space-only proper orthogonal decomposition 42 3.3 Spectral proper orthogonal decomposition 45 3.4 Comparison between space-only and spectral POD 48 3.5 Computing POD and SPOD from flow data 51 3.6 Data reconstruction using SPOD basis 58 3.6.1 Reconstruction in the frequency domain 59 3.6.2 Reconstruction in the time domain 61 3.7 Vorticity force decomposition using SPOD basis 63 Chapter 4 Numerical methods 69 4.1 Finite volume method (FVM) 69 4.2 Discretization of advection-diffusion equation 71 4.3 Discretization of spatial terms 73 4.3.1 Advection term 73 4.3.1.1 First-order upwind scheme 73 4.3.1.2 Second-order upwind scheme 74 4.3.1.3 Central-differencing scheme 75 4.3.1.4 QUICK scheme 75 4.3.2 Diffusion term 77 4.3.3 Source term 77 4.4 Temporal discretization 78 4.4.1 Explicit time integration 80 4.4.2 Implicit time integration 81 4.4.3 Crank-Nicholson time integration 82 4.5 Pressure-velocity coupling scheme 83 4.5.1 SIMPLE algorithm 86 4.5.2 PISO algorithm 94 4.6 Sub-grid scale (SGS) model 99 4.6.1 Smagorinsky-Lilly model 99 4.6.2 Dynamic Smagorinsky-Lilly model 100 4.6.3 WALE model 102 4.7 Boundary conditions 103 4.8 Simulation setup and validation 107 Chapter 5 Results and discussions 117 5.1 Flow fields and total vorticity forces 118 5.2 Effect of SPOD modes on aerodynamic forces 127 5.3 Vorticity forces of coherent structures in dominate modes and frequencies 134 5.3.1 AoA=7.5 134 5.3.1.1 Zeroth frequency of the first mode 134 5.3.1.2 First frequency of the first mode 137 5.3.1.3 Second frequency of the first mode 140 5.3.2 AoA=10 141 5.3.2.1 Zeroth frequency of the first mode 144 5.3.2.2 First frequency of the first mode 148 5.3.2.3 Second frequency of the first mode 150 5.3.2.4 Zeroth frequency of the second mode 153 5.3.2.5 First frequency of the second mode 153 5.3.2.6 Second frequency of the second mode 156 5.4 Quantitative comparison of SPOD modes and force contribution 158 Chapter 6 Conclusions 163 Chapter 7 Future works 167 References 169 Appendix A-MATLAB codes 187 A.1 Space-only POD 187 A.2 Spectral POD 188 A.3 Data reconstruction from SPOD modes 194 A.4 Other functions used in SPOD 196 Appendix B-Evaluation of gradients and derivatives 199 B.1 Green-Gauss cell-based scheme 199 B.2 Green-Gauss node-based scheme 200 B.3 Least square cell-based scheme 201 Appendix C-Convergence of SPOD modes 203 Appendix D-Analyzing vorticity forces of coherent structures on airfoil using space-only POD 205 D.1 Flow fields and total vorticity forces 207 D.2 Proper orthogonal decomposition 209 D.3 Turbulence and vorticity force contribution 212 D.3.1 AoA=5 212 D.3.1.1 Contribution of POD modes to aerodynamic forces 212 D.3.1.2 Coherent structures 212 D.3.1.3 Vorticity forces 214 D.3.2 AoA=10 219 D.3.2.1 Contribution of POD modes to aerodynamic forces 219 D.3.2.2 Coherent structures 220 D.3.2.3 Vorticity forces 220 D.3.3 AoA=15 224 D.3.3.1 Contribution of POD modes to aerodynamic forces 224 D.3.3.2 Coherent structures 225 D.3.3.3 Vorticity forces 226 D.3.4 Differences in drag and lift contribution 231 | - |
| dc.language.iso | en | - |
| dc.subject | 譜本徵正交分解 | zh_TW |
| dc.subject | NACA0012 翼型 | zh_TW |
| dc.subject | 大渦流模擬 | zh_TW |
| dc.subject | 力元理論 | zh_TW |
| dc.subject | SPOD | en |
| dc.subject | NACA0012 airfoil | en |
| dc.subject | Force element theory | en |
| dc.subject | LES | en |
| dc.title | 運用譜本徵正交分解分析擬序結構之渦度力對於NACA0012翼型的影響 | zh_TW |
| dc.title | Analyzing vorticity forces of coherent structures on NACA0012 airfoil using spectral proper orthogonal decomposition | en |
| dc.type | Thesis | - |
| dc.date.schoolyear | 111-2 | - |
| dc.description.degree | 博士 | - |
| dc.contributor.oralexamcommittee | 牛仰堯;曾建洲;張敬;蔡協澄 | zh_TW |
| dc.contributor.oralexamcommittee | Yang-Yao Niu ;Chien-Chou Tseng ;Ching Chang ;Hsieh-Chen Tsai | en |
| dc.subject.keyword | NACA0012 翼型,大渦流模擬,力元理論,譜本徵正交分解, | zh_TW |
| dc.subject.keyword | NACA0012 airfoil,LES,Force element theory,SPOD, | en |
| dc.relation.page | 231 | - |
| dc.identifier.doi | 10.6342/NTU202302005 | - |
| dc.rights.note | 同意授權(限校園內公開) | - |
| dc.date.accepted | 2023-08-04 | - |
| dc.contributor.author-college | 工學院 | - |
| dc.contributor.author-dept | 應用力學研究所 | - |
| dc.date.embargo-lift | 2028-07-31 | - |
| 顯示於系所單位： | 應用力學研究所 | |
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