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针对2020年使用的N+2代民用飞机的翼身融合(BWB)布局发展需要,以减小激波阻力为目标,采用计算流体力学(CFD)方法,开展弱化激波、减小激波阻力的鼓包流动控制技术研究。提出了λ形激波结构“强干扰”和等熵压缩“弱干扰”两种鼓包激波减阻流动控制原理,给出了两种鼓包基本形状设计方法和工程应用的可行性分析,指出λ形激波结构鼓包更易于在工程上实现。系统研究了产生λ形激波结构的鼓包位置、高度和长度等参数对控制激波与减小波阻的影响规律,提出了鼓包参数选择原则。研究结果表明,以激波强度和位置为依据,通过鼓包参数优化匹配,可达到弱化激波、减小波阻的目的,减阻效果显著,对RAE2822和NACA0012翼型的最大减阻量分别可达到21%和12%。
In order to reduce the shock resistance of the N + 2 generation civil aircraft used in 2020, it is necessary to develop the BWB layout to reduce the shock resistance by adopting CFD (Computational Fluid Dynamics) method Drum Flow Control Technology. The control principle of two types of drum shock wave damping flow control with λ-shaped shock wave structure, strong interference and isentropic compression and weak interference is proposed. The feasibility of two basic design methods of drum shape and engineering application are given Analysis shows that the shock absorber with λ-shaped shock structure is easier to implement in engineering. The influence of the parameters such as the location, height and length of the shock wave on the control shock wave and the reduction of wave resistance is studied systematically. The principle of selecting the parameters of the drum puff is proposed. The results show that, based on the strength and location of shock wave, the optimization of the parameters of the blister can achieve the purpose of weakening the shock wave and reducing the wave resistance, and the drag reduction effect is remarkable. The maximum drag reduction for the RAE2822 and NACA0012 airfoils respectively Reached 21% and 12%.