摘要
文中以绕DLR-F6翼身、翼/身/架/舱组合体流场为算例,研究了多区域网格尾迹积分技术在复杂构型气动力计算中的应用。采用"对角线判断"方法提高了尾迹面插值搜索区的搜索效率。同时,引入了较高精度尾迹插值方法,为气动力的精确计算提供了平台。研究结果表明:采用文中的尾迹积分技术计算复杂构型的气动力有较高的计算效率和精度。
In this paper,taking transonic flow of DLR-F6 wing-body,wing-body-pylon-nacelle configurations as typical computational examples,the application of multi-block wake integration technique to complex configuration was studied.＂Diagonal estimation＂ method was proposed to improve search efficiency of wake interpolation area and a wake interpolation method with high precision was introduced to provide an accurate aerodynamic computing platform.The numerical simulation results show that multi-block wake integration technique adopted in this paper can be used to compute aerodynamics for complex configurations with high efficiency and precision.
出处
《弹箭与制导学报》
CSCD
北大核心
2011年第5期135-137,140,共4页
Journal of Projectiles,Rockets,Missiles and Guidance
基金
中国民航飞行学院青年科学基金(Q2008-06)资助
