翼身融合布局鼓包激波减阻技术研究  

Investigation of shock control bump for blended wing body configuration

作　　者：李沛峰 陶于金[1] 张彬乾[2] 王丹[1] Li Peifeng;Tao Yujin;Zhang Binqian;Wang Dan(365th Institute,Northwestern Polyteehnieal University,710065,Xi'an,China;College of Aeronautics,Northwestern Polytechnical University,710072,Xi'an,China)

机构地区：[1]西北工业大学第365研究所,西安710065 [2]西北工业大学航空学院,西安710072

出　　处：《应用力学学报》2018年第6期1185-1191,1413,共8页Chinese Journal of Applied Mechanics

摘　　要：为应对未来航空领域经济性和环保性要求的不断提高,本文以减小翼身融合布局(BWB)激波阻力为目标,采用计算流体力学(CFD)方法,开展了基于鼓包的弱化激波、减小激波阻力的流动控制技术研究。分析了翼身融合布局的空气动力学特点,指出了鼓包应置于相对厚度较大的中央机体和易于产生激波诱导流动分离的过渡段区域。给出了基于等熵压缩弱化激波原理的"凹-凸-凹"型非对称鼓包构造方法,设计了针对三种来流状态的三种鼓包。研究表明,三种鼓包在其设计状态下的减阻效果明显,减阻量分别为7.1counts、10.4counts和16.6counts,可消除由激波诱导的弱分离,但对强分离控制有限。非设计状态下三种鼓包均具有较好的鲁棒性,在所研究的速度范围(Ma:0.8～0.85,CL=0.286)及升力范围(CL:0.14～0.5,Ma=0.82;CL:0.12～0.5,Ma=0.83;CL:0.05～0.5,Ma=0.85)内仍可减阻。In response to the ever-increasing economic and environmental requirements of future aviation,the current research takes reducing wave drag of Blended Wing Body (BWB)configuration as the goal and uses the Computational Fluid Dynamics (CFD)method to investigate the flow control technology based on the shock control bump.Aerodynamic characteristics of the BWB are analyzed and then the bump should be arranged in the thick center-body and the blending area which is easy to generate the shock induced separation.The asymmetrical bump based on the principle of isentropic compression is used to weaken the shock waves,and the bump construction method is presented.Three asymmetrical bumps based on the three different kinds of flow states are designed.The CFD simulations show that drag reduction of the three bumps in their design points are 7.1counts, 10.4 counts and 16.6counts,respectively.The bump can eliminate weak separation induced by shock wave,but it has limitation in controlling the strong separation.The off-design behavior shows that bumps are robust in reducing drag at a certain Mach number (Ma:0.8-0.85,CL=0.286)and lift range (CL:0.14-0.5,Ma=0.82;CL:0.12-0.5, Ma=0.83;CL:0.05-0.5,Ma=0.85).

关 键 词：翼身融合布局 流动控制 鼓包 激波 计算流体力学 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程]