摘要
高超声速风洞中,针对动态稳定性参数的特种试验通常采用模型尾支撑强迫振动的方式。采用三维非定常N-S方程开展动导数特种风洞试验尾支撑干扰数值模拟研究。空间方向的离散采用二阶精度的Roe格式,非定常流动求解采用“双时间步”方法的隐式LU-SGS格式。基于Etkin非定常气动力模型,采用小振幅强迫简谐分析法给出动态阻尼导数的数值计算方法。针对7?钝锥标模开展了三种不同支撑的数值模拟与试验对比研究。在标模验证的基础上,对比类X-51A动导数试验模型与真实飞行条件下的动态特性,开展尾支撑干扰对动导数的影响研究,获得尾支撑干扰带来的动导数变化量。
In hypersonic wind tunnel,sting support is usually used for the special test of dynamic stability parameters.A Computational Fluid Dynamics analysis of the dynamics of airbreathing hypersonic airframe/propulsion integrative vehicle at supersonic flight conditions is performed using 3D un-steady Navier Stokes equations.The 2-order Roe scheme and the dual-time-step method based on LU-SGS are respectively applied to discrete of the spatial and time derivative of the unsteady flow.Based on the unsteady Etkin pneumatics model,this analysis uses dynamic force-harmonic simu-lations to develop direct-dynamic stability derivatives,as well as cross and cross-coupling deriva-tives.Numerical simulation of 7?blunt cone model was carried out by three different sting supports.On the basis of standard model verification,the influence of sting interference on dynamic derivatives was analyzed,so as to get the dynamic derivative variations brought by the sting in-terference.
出处
《流体动力学》
2019年第1期38-46,共9页
International Journal of Fluid Dynamics
