本論文研究一縮減翼盒在進行快速加油時的燃油流動情形，給定速度進口條件與壓力出口條件，比較三種面積相同之孔洞幾何設計（圓、半圓、三角）對於翼盒結構所造成的壓力。本文先利用與燃油流動類似的水壩崩塌與水柱撞擊案例進行驗證，以確定使用模型與網格設置之正確性。接著利用翼盒進行網格獨立測試、時間步獨立測試與收斂殘值（Residual）測試，以確保上述三項CFD參數並不會對模擬結果造成太大的影響。
暫態模擬結果顯示半圓孔對於機翼油箱所造成的壓力最大，也需要最大的加油壓力才能給予相同的進口質量流率；我們也發現，進口壓力會直接受到傳輸通道的質量流率影響，同時有起伏現象。

This paper investigates the internal flow pattern of a reduced wing fuel tank during refueling process. Under the boundary conditions of constant inlet velocity and outlet pressure, the wall pressures of the wing fuel tank simulated using three different types of orifice (semicircle, circle, and triangle shapes) but with same opening area are compared are calculated. The built two-phase physical model is respectively run with a dam-break problem and a water jet impingement problem collected from the literature to validate the model applicability and the mesh layout established. The grid independent test, the time-step independent test, and the convergence criteria test are next conducted to determine the appropriate mesh configuration, the time-step size and the converging residual to be employed in the calculations. It is found that the wing fuel tank associated with semicircle-shaped pathway requires the highest input pumping power since it induces the highest pressure on the wall. It is also shown that the variation of pumping pressure versus time is synchronized with that of the pathway mass flow rate versus time, both showing oscillating behaviors.

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