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在亚跨超计算流体力学(CFD)软件平台(TRIP)上开发了基于RANS/LES混合思路的IDDES流动模拟技术,并通过NACA0021翼型60°大迎角分离流动与串列圆柱绕流模拟对RANS/LES混合方法的精确度进行了验证,针对某战斗机外形的垂尾脉动压力开展了数值模拟研究。战斗机来流马赫数为0.1,基于全机长度的雷诺数为2×106,模型迎角为20°、30°和40°。分别通过脉动压力系数、脉动压力功率谱密度、空间流动结构以及侧向力响应曲线等对战斗机的垂尾脉动压力进行了分析。脉动压力模拟结果表明:当垂尾完全沉浸在边条翼脱体涡破碎后的宽频湍流脉动气流中时,垂尾翼梢位置的脉动压力会发生明显的增大。
IDDES flow simulation technology based on RANS / LES mixed-signal was developed on the Sub-Trans-Computational Fluid Dynamics (CFD) software platform (TRIP), and the flow around the NACA0021 airfoil RANS / LES hybrid method to verify the accuracy of a fighter shape vertical tail pulsation pressure carried out numerical simulation study. Fighter jet Mach number 0.1, based on the length of the machine Reynolds number 2 × 106, the model angle of attack of 20 °, 30 ° and 40 °. The vertical tail pressure fluctuation of fighter aircraft was analyzed respectively by the pulsating pressure coefficient, the pulsating pressure power spectral density, the spatial flow structure and the lateral force response curve. The simulation results of pulsating pressure show that when the vertical tail is completely immersed in the wide-band turbulent pulsating airflow after the wing flapping off-body vortex is broken, the pulsating pressure at the tail of the tail will be obviously increased.