X型機翼無人機（UAV）展現了獨特的氣動優勢，能透過結合升力向量傾斜與側滑誘導側向力之產生，靈活執行滾轉轉彎（BTT）與側滑轉彎（STT）機動。故，相較於傳統固定翼機型，其X型的幾何佈局賦予了優異的操縱敏捷性。本研究旨在結合USAF Digital DATCOM計算氣動力係數及六自由度（6-DOF）飛行力學模擬，深入剖析X型機翼的機動性能特徵。研究重點在於有系統地分析及獲得前翼與後方旋轉X型尾翼之「複合上／下反角」，在無風及有風環境下的綜合效益。以建立攻擊型或偵打一體型無人機，外形氣動安控的設計資料庫。
模擬結果顯示，X型機翼構型還與飛行控制強烈地耦合。較大的複合角度能顯著強化側向氣動耦合，進而增強STT的橫向控制效能，並大幅縮小轉彎半徑；然而，這種高性能也伴隨著飛行軌跡震盪之加劇，與對環境風場敏感度之增加。相較之下，BTT模式透過升力傾斜機制，在強側風擾動下，可展現較為平滑、穩定的軌跡保持能力。
此外，本研究也探討了在側風下，BTT與STT不同控制律的動態響應差異。在運用於目標截擊之模擬中，分析數據進一步顯示增加上／下反角，能提升截擊精準度。其中夾角90°之X型機翼構型，在STT模式下，表現最為優異。不僅能縮短約16%的截擊時間，更將與目標之最小脫靶量，大幅降低近94%。
本研究亦發現，副翼設計於尾翼之構型，其滾轉控制力不足。因此，提出了一項設計優化：將副翼從尾翼，移至主翼。由於主翼擁有較大的側向力臂，此修改可使滾轉控制力矩導數（C_(l_da )），約增加 1.58 倍。
總結本研究不僅從理論模擬層面，探究了主導X型機翼操縱性的「氣動—控制耦合」，更在工程實務層面，為未來開發具備高敏捷、強抗風能力之自主無人機系統，提供了極具價值的設計資料庫。包括：定量設計準則，與任務規劃參考。

X-wing unmanned aerial vehicles (UAVs) can perform both bank-to-turn (BTT) and skid-to-turn (STT) maneuvers by combining lift-vector tilting with sideslip-induced lateral forces, offering superior maneuverability over conventional fixed-wing platforms. In this study, a high-fidelity numerical investigation of X-wing maneuvering performance is conducted using a six-degree-of-freedom (6-DOF) flight-dynamics model with aerodynamic coefficients from USAF Digital DATCOM. The coupled effects of front-wing and rear X-tail anhedral–dihedral angles are systematically examined under calm and crosswind conditions. The results indicate that larger angles significantly enhance lateral control authority and reduce turning radius during STT maneuvers, though increasing trajectory oscillations and crosswind sensitivity. Conversely, BTT maneuvers exhibit smoother, more robust behavior in crosswinds. To isolate intrinsic aerodynamic characteristics from controller-induced effects, a roll- and yaw-control verification framework is developed, revealing distinct mechanisms for crosswind compensation. Furthermore, target interception simulations demonstrate that larger anhedral–dihedral angles improve performance, with the 90° configuration reducing interception time by ~16% and minimum target separation distance by ~94%. To address roll control limitations under extreme configurations, a design refinement relocating ailerons from tail surfaces to main wings is proposed, yielding an estimated 1.58-fold increase in rolling moment derivative due to the larger moment arm. Overall, this study clarifies the aerodynamic–control mechanisms governing X-wing maneuverability and provides quantitative design guidelines for high-agility, wind-resilient UAV systems.

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