摘要
研究了涡扇动力翼吊布局飞机考虑动力效应时的流场数值模拟和气动干扰的若干问题。在数值模拟方法方面,介绍了便于实际工程应用的发动机进排气边界状态参数设定算法;通过设定无总温总压增量的喷口边界模拟发动机的无动力状态,避免了研究喷流效应时由通气短舱和喷气构型之间的几何外形差异带来的网格差异对计算结果的影响,提高了复杂构型流场数值模拟结果的可信度。通过数值模拟发现,发动机喷流的引射虽然可使气流加速从而降低翼面压力,但发动机做功导致的翼面压力抬升亦不可忽视。发动机喷流可能引发强烈的挂架气动干扰,其原因是由机身、发动机、机翼和挂架构成的收缩-扩张流道引起的气流加速。通过适当延长和增厚挂架可以削弱这种干扰。
Numerical simulation method and aerodynamic interference effects of wing-mounted nacelle aircraft were studied.In aspect of numerical simulation,a practical engineering compatible algorithm for the determination of engine intake and exhaust boundary parameters directly from free stream and engine work-ing conditions was developed.Mesh difference arises from geometry inconsistency between powered and un-powered nacelle,which is a confounding factor when estimating power effect,is eliminated via set up a zero-energy-increase exhaust boundary condition.Then,the credibility of numerical simulation result of complex configuration in aircraft design was improved.The numerical simulation results shown that the engine power has two opposite aspects of effects on wing surface pressure,one is that engine ejection speed the flow up and bring the pressure down,the other is that the engine increasesd the pressure near the nuzzle.The numerical simulation result also revealed that engine jet stream can induce severe flow interferences on surface of pylon, duel to the flow acceleration through the convergent-divergent duct that composed of fuselage,wing,nacelle and pylon surface.Extending and thickening the pylon appropriately,a better flow channel and pylon surface curvature distribution could achieved,and then the interference of the jet flow and pylon surface is relieved, the shock in the inner side of the pylon is eliminated.
出处
《空气动力学学报》
CSCD
北大核心
2014年第4期433-438,共6页
Acta Aerodynamica Sinica
关键词
气动干扰
动力发动机
边界条件
数值模拟
aerodynamic interference
powered nacelle
boundary condition
numerical simulation
