請用此 Handle URI 來引用此文件：
http://tdr.lib.ntu.edu.tw/jspui/handle/123456789/68268完整後設資料紀錄
| DC 欄位 | 值 | 語言 |
|---|---|---|
| dc.contributor.advisor | 朱錦洲 | |
| dc.contributor.author | Po-Lun Lo | en |
| dc.contributor.author | 羅博倫 | zh_TW |
| dc.date.accessioned | 2021-06-17T02:16:12Z | - |
| dc.date.available | 2021-01-04 | |
| dc.date.copyright | 2018-01-04 | |
| dc.date.issued | 2017 | |
| dc.date.submitted | 2017-10-11 | |
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| dc.identifier.uri | http://tdr.lib.ntu.edu.tw/jspui/handle/123456789/68268 | - |
| dc.description.abstract | 實際上，飛行器在著陸的過程中，其與地面之距離將不斷的變化。因此，在降落過程應將受到為動態地面效應(Dynamic Ground Effect)的影響。本研究將利用循環式水洞搭配輸送帶系統，來針對的定翼型微型飛行器進行近地效應分析。本論文，首先對於不同攻角、雷諾數與展弦比之結果做分析，再探討靜態(Static Effect)分析與動態分析結果之差異，最後由數值計算之結果與張建成教授所提出的力元理論做比對與驗證。本實驗將針對NACA4412的翼型做探討，其規格為弦長5cm而展弦比為2、3與4的模型翼。文中將探討6~25之攻角以及雷諾數5000、6000、7500、9000與10000等條件下進行近地效應之模擬。由結果分析可知，不論動態或靜態分析，其近地效應約從1.00c處開始影響，而在0.5c以下影響更劇烈。在相同雷諾數的環境下，靜態分析存在臨界攻角而動態則無明顯的臨界攻角(以下)，此差異來自於靜態與動態在高攻角條件下兩者在翼面分離渦旋的情況不同。在適當的攻角條件下，升力大小隨雷諾數提升而增加，而高攻角條件下則無此趨勢。在不同展弦比的結果中顯示，展弦比長的力的能夠在低雷諾數下得到更多升力來源。在較低攻角的條件下，可由靜態分析結果來分析真實情況；而在高攻角的條件下，應由動態分析來探討，否則將存在30%~40%之間的誤差。 | zh_TW |
| dc.description.abstract | This study is aimed to investigate the influence of ground effect during the landing process of the airfoil NACA 4412 under static and dynamic experimental force measurements in a water tunnel that has moving ground simulation with numerical validations. Airfoils of 5‑cm chord length (C) and 3° pitch angle (θ) at various aspect ratios (AR=2, 3, & 4) are vertically immersed in the water with a narrowed‑neck support linked between the load cell above water surface and the airfoil beside the conveyor belt. The conveyor belt is designed to synchronize with the inflow velocity (U) in order to remove the boundary effects generated by the velocity difference at the side wall, and is capable of matching Reynolds numbers (Re) from 5,000 to 10,000 as utilize in the present study. The forces exerted on the airfoil are measured by a 2‑D load cell under the two prescribed situations, namely static ground effect (SGE) and dynamics ground effect (DGE).In SGE, the forces exerted on the airfoil are measured statically at various clearance and angle of attacks α=θ+γ, where γ is chosen to match with those in the DGE. As in DGE, the forces are measured at a continuous descending motion of normalized constant velocity vf=vf*∕U=tan(γ) towards the ground (moving conveyor), so‑called dynamic. It is emphasized that γ is the inflow angle relative to the descending airfoil determined by vf, and α in DGE is varied from 6° to 25° (with θ=3°).The results show that the ground effect in either SGE or DGE is essential to the airfoil only when the clearance decreases below a unit chord length (C), and the influence becomes rather tremendous as the clearance deceases below 0.5C. Next, it is found that the lift coefficient CL increases with increasing α in SEG and DGE cases under the same Re. However, the increment of CL ceases when a critical α is achieved in SGE. When α is low‑to‑moderate, CL is shown to increase with increasing Re in both SGE and DGE cases. In addition, the lift curve with respect to the clearance in SGE and DGE are almost the same when α is low‑to‑moderate, and thus the results in SGE can be reasonably applied to that in DGE. However, when dealing with α beyond a certain angle, the analysis of DGE must be taken into account in order to prevent an error that could reach about 30 to 40%. | en |
| dc.description.provenance | Made available in DSpace on 2021-06-17T02:16:12Z (GMT). No. of bitstreams: 1 ntu-106-R04543075-1.pdf: 145360615 bytes, checksum: 463e9c9dad280d3c648d648dee878819 (MD5) Previous issue date: 2017 | en |
| dc.description.tableofcontents | 口試委員會審定書. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . i
誌謝. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ii 中文摘要. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . iii Abstract . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . iv 目錄. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . vi 圖目錄. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ix 表目錄. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . xiii 第一章緒論. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 1.1 前言. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 1.2 微型飛行器之簡介. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 1.3 研究動機與目的. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 1.4 微型飛行器之文獻. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 1.5 不同翼型之文獻. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 1.6 失速攻角之文獻. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 1.7 近地效應之文獻. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8 1.7.1 近地效應前言. . . . . . . . . . . . . . . . . . . . . . . . . . . 8 1.7.2 早期的近地效應分析. . . . . . . . . . . . . . . . . . . . . . . 9 1.7.3 靜態近地效應(Static Ground Effect) . . . . . . . . . . . . . . . 9 1.7.4 動態近地效應(Dynamic Ground Effect) . . . . . . . . . . . . . 13 1.7.5 近地效應結語. . . . . . . . . . . . . . . . . . . . . . . . . . . 15 1.8 低展弦比之文獻. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 1.9 流場分析文獻. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 1.10 總結. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 第二章基礎理論. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 2.1 簡介. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 2.2 參數介紹. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 2.2.1 因次參數與無因次參數介紹. . . . . . . . . . . . . . . . . . . 19 2.2.2 無因次參數. . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 2.3 NACA 系列翼型介紹. . . . . . . . . . . . . . . . . . . . . . . . . . . 24 2.4 低雷諾數流. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 第三章數值方法. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 3.1 簡介. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 3.2 網格產生. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 3.2.1 網格類型. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 3.2.2 網格設定. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 3.3 控制方程式介紹. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 3.3.1 連續方程式. . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 3.3.2 動量守恆方程式. . . . . . . . . . . . . . . . . . . . . . . . . . 28 3.4 數值方法. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 3.4.1 分離求解器. . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 3.4.2 空間離散. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 3.4.3 時間離散. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36 3.4.4 壓力-速度耦合關係的處理. . . . . . . . . . . . . . . . . . . . 38 第四章實驗介紹. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43 4.1 簡介. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43 4.2 實驗設備. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43 4.2.1 循環式水洞水槽(Water Tunnel) . . . . . . . . . . . . . . . . . 43 4.2.2 模型機翼NACA4412 . . . . . . . . . . . . . . . . . . . . . . . 44 4.2.3 雙軸荷重元（Load Cell） . . . . . . . . . . . . . . . . . . . . . 45 4.2.4 IAI 機械手臂與控制器. . . . . . . . . . . . . . . . . . . . . . 46 4.2.5 輸送帶設備. . . . . . . . . . . . . . . . . . . . . . . . . . . . 47 4.2.6 雷射系統. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 48 4.2.7 CCD 攝像機. . . . . . . . . . . . . . . . . . . . . . . . . . . . 48 4.3 實驗架設與流程. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49 4.3.1 測試段之整體架設. . . . . . . . . . . . . . . . . . . . . . . . 49 4.3.2 線性手臂流程. . . . . . . . . . . . . . . . . . . . . . . . . . . 50 4.3.3 荷重元流程. . . . . . . . . . . . . . . . . . . . . . . . . . . . 50 4.3.4 雷射流程. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 51 4.3.5 實驗整體流程. . . . . . . . . . . . . . . . . . . . . . . . . . . 51 第五章結果與討論. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52 5.1 簡介. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52 5.2 定雷諾數分析. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 54 5.2.1 靜態分析. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 54 5.2.2 動態分析. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 58 5.3 定攻角分析. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 64 5.3.1 靜態分析. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 64 5.3.2 動態分析. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 68 5.4 動態與靜態近地效應之比對. . . . . . . . . . . . . . . . . . . . . . . 72 5.5 不同展弦比分析. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 75 5.6 顯影比較. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 77 5.7 實驗與模擬比對. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 84 5.8 壓力分佈討論. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 86 5.8.1 機翼表面壓力分佈. . . . . . . . . . . . . . . . . . . . . . . . 86 第六章結論與未來展望. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 92 6.1 結論. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 92 6.2 未來展望. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 93 參考文獻. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 94 附錄. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 101 | |
| dc.language.iso | zh-TW | |
| dc.subject | NACA4412 | zh_TW |
| dc.subject | 數值計算 | zh_TW |
| dc.subject | 近地效應 | zh_TW |
| dc.subject | 實驗量測 | zh_TW |
| dc.subject | 有限翼 | zh_TW |
| dc.subject | 低雷諾數 | zh_TW |
| dc.subject | 低展弦比 | zh_TW |
| dc.subject | Numerical calculations | en |
| dc.subject | Finite wing | en |
| dc.subject | low Reynolds numbers | en |
| dc.subject | Low aspect ratio | en |
| dc.subject | Ground effect | en |
| dc.subject | Experimental measurement | en |
| dc.title | 低雷諾數下有限翼近地效應之實驗與數值模擬分析 | zh_TW |
| dc.title | Experimental and Numerical Analysis of Finite Wing in
Ground Effect at Low Reynolds Numbers | en |
| dc.type | Thesis | |
| dc.date.schoolyear | 106-1 | |
| dc.description.degree | 碩士 | |
| dc.contributor.coadvisor | 張建成 | |
| dc.contributor.oralexamcommittee | 陳建甫,蘇正瑜,宮春斐 | |
| dc.subject.keyword | 近地效應,NACA4412,低展弦比,低雷諾數,有限翼,實驗量測,數值計算, | zh_TW |
| dc.subject.keyword | Ground effect, Low aspect ratio,low Reynolds numbers,Finite wing,Experimental measurement,Numerical calculations, | en |
| dc.relation.page | 106 | |
| dc.identifier.doi | 10.6342/NTU201704259 | |
| dc.rights.note | 有償授權 | |
| dc.date.accepted | 2017-10-11 | |
| dc.contributor.author-college | 工學院 | zh_TW |
| dc.contributor.author-dept | 應用力學研究所 | zh_TW |
| 顯示於系所單位： | 應用力學研究所 | |
文件中的檔案：
| 檔案 | 大小 | 格式 | |
|---|---|---|---|
| ntu-106-1.pdf 未授權公開取用 | 141.95 MB | Adobe PDF |
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