當對於具有直昇機起降需求的船艦，除了會因海上環境會影響直昇機起降時的安全性，流經此船艦在後方甲板所產生的風場如U型渦流結構等現象，也會對直昇機起降造成影響，而本研究則針對鄰近甲板的機庫構型做變化透過CFD數值模擬方法，並採用RANS中的Realizable k-ε紊流模型進行計算，量測在不同入流角下以SFS為基本構型，依現代軍艦為參考設計出Incline型、Corner型以及Chamfer型，分別量測四種機庫構型所造成的甲板流場分佈狀況、流速、渦度、紊流強度等物理特徵，並與Yang(2020)之部份實驗結果進行對照比較，該實驗透過PIV方法於迴流水槽中進行實驗，量測和本研究相同的四種機庫模型產生的流場結構等特徵，且將各種機庫在不同迎風角下對上述的量測項目進行綜合比較評估，發現當迎風角大於一臨界角度時(如本研究中的Green 30°和Green 45°兩條件)，四種機庫構型的各項物理量皆有趨於一致的現象，且四種機庫在後方甲板上形成的U型渦流結構後流場皆有往上抬升的現象，以及在後段近甲板面皆有複雜渦漩分佈，該渦漩上方皆出現較強的紊流帶，直升機於甲板起降時應避免降落在此位置。綜合所有現象之結果，其中又以Corner型機庫因其大範圍的矩型缺角設計所呈現出來的各項表現明顯亦於其他三種機庫。統整本研究結果如流場的速度大小和流向方向分佈，即可在制定風限圖所需的風向條件的部份做為初步了解後可供直升機駕駛員在遭遇相似環境條件下時可對周圍流場有一個初步應變判斷，以及船艦機庫設計上能有一個參考依據。

　　When helicopter pilots take off and land on the flight deck, the safety during the operation might be affceted by the flow field above the flight deck, such as the vortex structure cause by the wind passing through the hangar. In this research, we use the Computational Fluid Dynamics (CFD) in order to simulate the flow field above the flight on the Simple Frigate Shape (SFS) Model with different types of hangar (Base, Incline, Corner, Chamfer) under fourinflow conditions (Headwind, Green 10°, Green 30°, Green 45°). We also compare with other expermint data which use Particle Image Velocimetry (PIV) method in circulating water tank. Simulation items include flow speed, 2D, 3D streamlines, vorticity and turbulencr intensity, summarize the characteristic of flow structure, taking these conclusions as a basic knowledge which can provide such as the informations needed to establish the Ship-Helicopter Operating Limits (SHOL), give pilots a preliminary understanding of the flow field above the flight deck under different condition or even give some concept of the flight deck flow field to the designer when he allocation and design the structure of the hangar in the future.

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