空間離散算則與限制器對載具在穿音速軸向力係數計算之影響

The Influence of Spatial Schemes and Flux Limiters on Axial Force Coefficients for Vehicles in Transonic Speed

李予真(Yeu-Jen Lee) ； 林志華(Chih-Hua Lin) ； 林恆(Herng Lin)

《中國航空太空學會學刊》 37卷2期 (2005/06) Pp. 147-152

https://doi.org/10.6124/TAASRC.200506_37(2).05

摘要

本文進行吸氣式引擎載具在加力期（不通氣狀態）之軸向力係數分析，探討高次音速與穿音速飛行體之流場特性與阻力效應，並比較空間離散算則與限制器對軸向力係數之影響，以驗證數值分析的準確性。流場數值分析採用CFD-FASTRAN軟體，紊流模式選用含壁面函數的k-ε雙方程式模式。本文分析NASA Langley於1983年進行二維雙進氣道飛彈之氣動力性能試驗外形，分析三個不同的自由流馬赫數，分別爲0.60、0.80及0.95，攻角零度，以驗證零攻角軸向力係數的計算精度。另外在馬赫數0.80的算例中，增加攻角5及10度的流場分析，以進一步瞭解軸向力係數隨攻角的變化情形。

關鍵字

吸氣式引擎載具 ； 軸向力係數 ； 穿音速流 ； 紊流流場

並列摘要

To justify the simulation accuracy in axial force of an air-breathing vehicle in transonic and subsonic speed, this paper examines the three-dimensional turbulent flows around the vehicle having two rectangular side inlets ,which NASA Langley had conducted relevant wind tunnel test in 1983. Our primary concern is to clarify the zero angle drag calibration from the view of experiment and therefore appraising the evaluation of external axial force, we also address the result of axial force at zero angle of attack resulting from the choose of spatial limiter. The commercial code, CFD-FASTRAN, is used to solve the full Navier-Stokes equations with high Reynolds number k-ε turbulence model (with wall functions). Flows at zero angle of attack condition have been tested with Mach number 0.6, 0.8 and 0.95. Flow with free stream Mach number 0.8 has been simulated at different angles of attack. All cases deal with Reynolds number between 8.5~10×10^6/m.

並列關鍵字

Air-breathing vehicles ； Axial force coefficient ； Transonic flow ； Turbulent flow