近期在國際或是國內無人載具(UAV)的發展以備受重視。但是飛機整體的設計過程卻還是需要按照傳統的方式進行估算，一般均採用計算流體力學(CFD)或是採取實際的模型進行風洞實驗，但這大都耗時耗力，因此我們便需要一個更快更方便的方式來取得所需的空氣動力係數。DATCOM Method不僅滿足以上的要求更可以估算飛機或飛彈的靜態、動態穩定分析及控制特性。
但在國內尚無印證在UAV上，因此將它與UAV結合跟風洞測試驗證便是本研究主要的工作。本文成功的運用DATCOM分析出Spoonbill無人載具氣動力分析。將DATCOM Method 估算的結果與風洞實驗的結果比較，可發現在低攻角(AOA)的範圍下，DATCOM Method與風洞實驗的結果準確性是相當高的。將DATCOM Method與風洞實驗的結果藉由公式運算進行性能分析，可知DATCOM Method的計算結果均會低於風洞實驗所得的結果20% 。因此運用DATCOM Method在無人載具的設計及氣動力分析是可行的，但在高攻角的範圍則會有較明顯的誤差產生。

The development of Unmanned Aerial Vehicle (UAV) has long been an important issue around the World. However, classical method such as wind tunnel testing and computational fluid dynamics (CFD) still play an important role in the design process of the vehicles, such time consuming methods are driving forces to the use of a more convenient and faster method to obtain desired aerodynamic coefficients.
DATCOM is just the right tool to meet such requirement, not only it can estimate the desired aerodynamic coefficients for the design process, it can also estimate the static and dynamic characteristics of the vehicle. This method is yet to be applied on UAV design in local research institutes. Thus, the objective of this project was to verify its applicability by comparing the analysis result with the wind tunnel testing data.Aerodynamic analysis of the Spoonbill UAV was completed in this thesis. By comparing the results of both DATCOM method and wind tunnel testing, DATCOM prediction matches well with the wind tunnel testing results for low angle of attack (AOA). The aerodynamic coefficients obtained by DATCOM predictions and wind tunnel testing results were used for the calculation of
aircraft performance. Comparison of the calculated performances found that the performance calculated by using DATCOM predictions is 20% less than those calculated by using the wind tunnel testing results. Therefore, the applicability of DATCOM on the UAV aerodynamic analysis was proven, but the error increases as the angle of attack increases.

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