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題 名 | 尾部外形對彈體氣動阻力影響之數值研究 |
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作 者 | 曾培元; 許建華; | 書刊名 | 中正嶺學報 |
卷 期 | 24:1 1995.07[民84.07] |
頁 次 | 頁19-30 |
分類號 | 447.55 |
關鍵詞 | 彈尾阻力; 超音速流; 數值分析; Boattail drag; Supersonic flow; Numerical analysis; |
語 文 | 中文(Chinese) |
中文摘要 | 本文旨在利用數值方法模擬彈體流場,並探討彈體尾部形狀對氣動阻力之影響, 評估數值尋優設計的可行性與所面臨的問題。 採用基於有限體積法( Finite Volume Method )的顯式多階上風通量差分( Explicit Multi-stage, Upwind Flux-difference Splitting Scheme )為主要數值方法,求解依時性的雷諾均值 Navier-Stokes 方程組的定 常解,另選用考慮可壓性的單方程紊流模式。彈體表面壓力計算結果與實驗數據相當吻合, 而彈底部之計算結果則顯示與實驗之變化趨勢相同,另在不同速度下,針對五種船尾部形狀 進行低阻力外形尋優研究,其中以錐型船尾且船尾角約 14 度者為最佳外形。 |
英文摘要 | The purpose of this paper is to examine numerically the effect of the boattail configurations on the aerodynamic characteristics of an axisymmetric projectile at various velocities (including subsonic, transonic and supersonic speeds). The time-dependent Reynolds-averaged Navier-Stokes equations coupled with one equation turbulence model was solved by using an explicit multi-stage upwind flux-difference splitting scheme, and the numerical solution was followed in time until the steady state is reached. The comparison between calculated results and available experimental data is conducted to evaluate the effectiveness of this method. Good agreement is obtained and it is demonstrated that this numerical approach provides useful information for drag reduction in projectile design. The results of this investigation also show that the conical boattails appear to be superior to other shapes. |
本系統中英文摘要資訊取自各篇刊載內容。