臺灣博碩士論文加值系統

　　本文以數值模擬探討菱形封閉式機翼設計角度，改變前翼後掠角、上反角與後翼前掠角、下反角與同時改變四項角度設計，分析其氣動力特性。在自由流風速12m/s的流場條件下，固定機翼側板尺寸、翼弦長以及展弦比，改變前後翼之掠角及反角，並與矩形封閉式機翼(baseline)比較。結果顯示，前翼方面，上反角增加，整體CL跟著提升，且CL都比baseline大，失速攻角有向後移動趨勢；而後掠角增加，CL提升其影響比上反角小，改變後掠角在機翼高攻角時才有明顯差異。分析後掠角與上反角組合之菱形封閉式機翼，在低後掠角時加大上反角，CL增益效果尤為顯著，但隨著上反角往上增加到更高角度時，CL上升逐漸趨緩下來，提升CL效果逐漸變小；後掠角方面達到10度CL已趨近飽和，再增加後掠角CL已無明顯差異，前翼組合結果相比baseline，CL值最大提升36%。後翼方面，下反角增加，整體CL有提升，但從所有探討參數中可發現，各個改變下反角之間CL差異不大；前掠角增加，CL跟著提升，但到了前掠角10度後，CL卻不會有提升效果。分析下反角與前掠角組合之菱形封閉式機翼，對下反角而言，增加下反角度雖然CL有增加，但增益效果相當小；而前掠角方面，增加前掠角度在低下反角度時，CL增益最為顯著，但前掠角到達10度時，往上再增加前掠角CL卻不再提升，後翼組合結果相比baseline，CL值最大提升34%。分析同時改變前後翼設計角度，從0度開始隨著四項設計角度增加，整體CL跟著提升，僅上升至設計角度為10度，如再加大角度，CL值不再提升，反而有下降的趨勢，同時改變前後翼的結果相比baseline，CL值最大提升35.5%。

　　This study aims to investigates about the numerical simulation of diamond shaped closed Wing. In this numerical simulation different types of wing design angles like sweepback with dihedral angle for forward wing and forward-sweep with anhedral angle for rear wing and Change the design of four angles and analyzed its aerodynamic characteristics. The wind-speed is kept constant at 12m/s, the wing side plate size, chord length and aspect ratio are kept constant. The aerodynamic simulation is carried out for various angles and compared with the rectangular closed wing of unchanged wing angle(baseline). The experimental results indicate that as dihedral angle increases CL increase significantly, as sweep back angle increases CL has slight increase. At high AOA there is a significant change in sweepback angle. Analysis of UAV combined with change in sweepback and dihedral angle leads to increase in CL up to 10 degree, but it has no significant change after that. For the rear wing, as anhedral angle increases then CL increases, at low forward-sweep angle the CL increase slightly. Analysis of UAV combined with anhedral and sweep forward angle leads to slight increase in CL up to 10 degree and it has no significant change after that. Analyze and comprehensively change the four design angles. Analyze and change the four design angles. from 0 degrees, as the four design angles increase, CL increases, but only rises to design angle of 10 degrees. continue increasing the angle and no more increase of the CL, and will decrease. The changes of the four design angle have a maximum CL value increase of 35.5% compared to the baseline.

摘要...i
Abstract...iii
誌謝...v
目錄...vii
表目錄...x
圖目錄...xi
符號說明...xx
第一章 緒論...1
1.1　研究動機...1
1.2　研究目的...3
1.3　文獻回顧...3
第二章 研究方法...7
2.1 物理模式...7
2.2 統御方程式...7
2.3 紊流模型...8
2.4邊界條件...10
第三章 數值方法及驗證...11
3.1 簡述...11
3.2網格系統...11
3.3程式驗證...12
第四章 數值模擬分析...13
4.1 前翼角度變化之數值分析...13
4.1.1固定後掠角變化上反角之數值分析...13
4.1.2固定上反角變化後掠角之數值分析...19
4.1.3變化前翼設計角度之CP圖分析...24
4.2 後翼角度變化之數值分析...26
4.2.1固定前掠角變化下反角之數值分析...26
4.2.2固定下反角變化前掠角之數值分析...31
4.2.3變化後翼設計角度之CP圖分析...36
4.3 前後翼角度變化之數值分析...38
第五章 結論...40
5.1 前翼角度變化...40
5.2 後翼角度變化...41
5.3 前後翼角度變化...42
參考文獻...107
Extended Abstract...110
Abstract...110
Results and Discussion...111
Forward-wing...112
Rear wing...112
Change the design of four angles...113

[1]Spyridon G. Kontogiannis, John A. Ekaterinaris, “Design, performance evaluation and optimization of a UAV” Aerospace Science and Technology 29 (2013) 339–350
[2]R. Barbosa, B. Escobar, V. M. Sanchez , J. Hernandez, R. Acosta, Y. Verde,” Sizing of a Solar/Hydrogen System for High Altitude Long Endurance Aircrafts”, International Journal of Hydrogen Energy , Vol. 39, 2014, pp.16637-16645.
[3]S. Jashnani, T.R. Nada, M. Ishfaq, A. Khamker, P. Shaholia,” Sizing And Preliminary Hardware Testing of Solar Powered UAV”, The Egyptian Journal of Remote Sensing and Space Sciences, Vol. 16, 2013, pp. 189–198.
[4]X. Zhu, Z. Guo, Z. Hou,” Solar-powered Airplanes: A Historical Perspective and Future Challenges”,Progress in Aerospace Sciences, Vol. 71, 2014, pp.36–53.
[5]Shiau, Jaw-Kuen, Ma, Der-Ming, Chiu, Chih-Wei, Shie, Jie-Ren, “ Optimal Sizing and Cruise Speed Determination for a Solar Powered Airplane”. Journal of Aircraft, Vol. 47, No. 2, 2010, pp. 622–629.
[6]Greer, D. Krake, K., and Drela, M., “Design and Predictions for a High-Altitude (Low-Reynolds Number) Aerodynamic Flight Experiment”, NASA/TM-1999-206579.
[7]Maughmer, M. D. and Somers, D. M., “Design and Experimental Results for a High-Altitude,Long-Endurance Airfoil”, Journal of Aircraft, Vol. 26, No. 2, pp.148-153, 1989.
[8].Maughmer, M. D. and Somers, D. M., “Figures of Merit for Airfoil/Aircraft Design Integration”,AIAA-88-4416, 1988.
[9]I.M. Kroo, “Non-planar wing concept for increased aircraft efficiency”, VKI Lecture, Stanford University, U.S.A., 2005.
[10]Gobpinaath M, “Design and Analysis of Non Planar Wing in
Commercial Aircraft”, International Journal of Innovations in Engineering and Technology, Volume 7 Issue 3 October 2016, pp. 472-485
[11]Paul O Jemitola, John P Fielding, “Box Wing Aircraft Conceptual Design”, Department of Aerospace Engineering, Cranfield University, 2012　
[12]J. Wolkovitch. "The joined wing - An overview", Journal of Aircraft, Vol. 23, No. 3 (1986), pp. 161-178.　
[13]Ishan Roy Salam, Cees Bil. "Preliminary Aerodynamic and Structural Design Tradeoff for a Box-Wing Airliner", 50th AIAA
[14]Soujanya Marisarla, Vijay Narayanan, Urmila Ghia, Karman Ghia,” PREDICTION OF STRUCTURAL BEHAVIOR OF JOINED-WING CONFIGURATION OF HIGH-ALTITUDE LONG-ENDURANCE (HALE) AIRCRAFT” 41st Aerospace Sciences Meeting and Exhibit 6-9 January 2003, Reno, Nevada AIAA 2003-625　　　
[15]M. F. Samuels, “Structural weight comparison of a joined wing and a conventional wing”, Journal of Aircraft, Vol. 19, 1982, pp. 485-491.
[16]Ilan Kroo and John Gallmant” Aerodynamic and Structural Studies of Joined-Wing Aircraft” Journal of Aircraft, VOL. 28, NO. 1 pp.74-81,1991
[17]Tielin Ma1, Xiangsheng Wang, “Conceptual Design of a VTOL Box-wing UAV with Rotatable Duct-fans”, 2019 by the American Institute of Aeronautics and Astronautics.
[18]Stephen A.Andrews, “Comparison of box-wing and conventional aircraft mission performance using multidisciplinary analysis and optimization”, Aerospace Science and Technology Volume 79, August 2018, Pages 336-351.
[19]K.O. Predachenko, “Possibility of Application Joined Wing Layout
for UAV”, IEEE 3rd International Conference Actual Problems of Unmanned Aerial Vehicles Developments, 2015.
[20]ANSYS, FLUENT 13.0 User’s Guide, ANSYS Inc, 2010.
[21]F. R. Menter, "Two-equation eddy-viscosity turbulence models for engineering applications", AIAA Journal, Vol. 32, pp. 1598-1605, 1994. 2-4紊流模型@@
[22]J. P. Van Doormaal and G. D. Raithby, "Enhancements of the SIMPLE method for predicting incompressible fluid flows", Numerical Heat Transfer, Vol. 7, pp. 147-163, 1984.
[23]S. V. Patankar, "Numerical Heat Transfer and Fluid Flow", McGraw-Hill, New York, 1980.
[24]J.H.Chen, S.S.Li, V.T.Nguyen, "The effect of leading-edge protuberances on the performance of small aspect ratio foils", 15th International Symposium on Flow Visualization June 25-28, 2012, Minsk, Belarus.