本研究以風洞實驗、背景紋影法與數值模擬探討馬達驅動振盪翼於穿音速流場中的非定常氣動響應。實驗模型採用 NASA SC (2)-0012 矩形翼，並透過步進馬達與曲柄搖桿機構產生週期性俯仰運動。研究中量測不同展向位置之表面壓力訊號，並使用滑移網格數值模擬分析壓力響應、震波運動與氣動力係數變化。
本研究首先評估壓力管路對量測結果的影響。結果顯示，在準穩態條件下，管路對壓力量測的影響極小；但在動態條件下，管路系統於機翼作動頻率附近會對壓力訊號造成影響。實驗與模擬所得之壓力響應具有相似的整體趨勢，但在壓力值與震波位置上仍存在差異。背景紋影與震波位置追蹤結果顯示，震波運動與機翼作動頻率具有明顯關聯。
此外，本研究將數值模擬所得之氣動力係數與 Theodorsen 理論及 add mass effect 進行比較。結果顯示，升力響應可由 add mass effect 合理預測；然而力矩響應在較高攻角下呈現較強的非線性，後續仍需進一步修正預測模型。

This study investigates the unsteady aerodynamic response of a motor-driven oscillating wing in transonic flow using wind tunnel experiments, Background-Oriented Schlieren (BOS) visualization, and numerical simulations. A NASA SC (2)-0012 rectangular wing was driven by a stepper motor and crank–rocker mechanism to generate periodic pitching motion. Surface pressure measurements were conducted at selected spanwise locations and sliding-mesh CFD simulations were performed to analyze the corresponding pressure response, shock motion, and aerodynamic coefficients.
The pressure transmission characteristics of the tube system were first examined. The tube effect was found to be negligible under quasi-steady conditions, while a noticeable influence was observed near the wing oscillation frequency under dynamic conditions. The experimental and numerical pressure responses showed similar overall trends, although differences remained in the pressure magnitude and shock location. BOS visualization and shock-position tracking confirmed that the shock motion was directly associated with the imposed pitching motion.
The numerical aerodynamic coefficients were compared with theoretical predictions based on Theodorsen theory and the add mass effect. The lift response was reasonably approximated by the add mass effect, whereas the moment response showed stronger nonlinear behavior, indicating that further model improvement is required.

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