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題名 | 具支撐桿效應之穿音速彈丸流場計算=Computation of Transonic Flow Past a Projectile with Sting Effect |
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作者姓名(中文) | 翁興中; 蘇艾; 孫忠銓; 魏建國; 楊乃中; 熊日瀾; | 書刊名 | 力學 |
卷期 | 16:1 2000.06[民89.06] |
頁次 | 頁33-41 |
分類號 | 440.137 |
關鍵詞 | 支撐桿效應; 穿音速紊流流場; 彈底流場; Sting effect; Transonic turbulent flow; Base flow; |
語文 | 中文(Chinese) |
中文摘要 | 本研究以「薄層Navier-Stokes 迫近法」來模擬馬赫數為0.96、4°及10°攻角、 包括支撐桿 (Sting) 效應之 SOCBT (Secant-Ogive-Cylinder-Boattail) 彈丸的穿音速紊 流流場 (Turbulent Flow)。 計算結果與量測之實驗值比較後可以發現:(1) 計算所得之彈 體表面壓力及彈底 (Base) 之環向壓力值,均相當接近實驗值。(2) 支撐桿本身之幾何外形 ,對彈底流場結構及彈丸之船尾 (Boattail) 部會產生顯著的影響;對有支撐桿之彈丸計算 所得之背風側 (Leeward Side) 之表面壓力值,較無支撐桿效應之計算更接近實驗值。因此 在計算流場中將支撐桿效應納入,的確已經明顯地改進了實驗和實際飛行性能數據間的差異 。 |
英文摘要 | The thin-layer Navier-Stokes approximation is employed to simulate a M��=0.96 transonic turbulent flow past a SOCBT projectile with sting at 4°and 10° angles of attack. The present results show that (1)the computed longitudinal surface pressure and circumferential pressures of the base with sting are compared very well with experimental those. (2)the geometry of the sting has contributed a significant effect to the flow structure of the base and the boattail of a projectile. based on this effect, the computed surface pressures on the leeward side of the projectile with sting, are much closer to the experimental pressures than those without sting. Thus, it can be concluded that the sting effect included in the computed flow has contributed a significant improvement for the difference between experimental and real flight performance data. |
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