直升机机身、平尾、垂尾的气动干扰

运用面元法模拟直升机机身流场,计算前飞状态的ROBIN(rotor body interaction)模型孤立机身顶部中线的压力系数分布,并与参考数据、CFD计算结果对比,验证了本方法的准确性.采用离散涡系模拟平尾、垂尾和短翼等升力面,以带短翼的UH-60直升机为例,研究了升力面参数变化对机身、平尾、垂尾气动干扰的影响.结果表明:改变升力面的安装角显著改变了气流对其周围的绕流情况,在参数中影响最大;平尾参数尤其是安装角会对垂尾和短翼的压力系数产生较大影响;减小垂尾展长和增大短翼安装角会提升各自的压力系数.

Aerodynamic interaction of fuselage,horizontal stabilator and vertical stabilator of helicopter

The panel method was used to simulate the helicopter fuselage flowfield.For the isolated fuselage of rotor body interaction (ROBIN) model,the pressure coefficient distribution along the top centerline was calculated in forward flight.The computational results were compared with the referenced data and computational fluid dynamics(CFD) results,validating accuracy of the methodology.Discrete vortices system was used to simulate the lifting surfaces,including horizontal stabilator,vertical stabilator and short wing.Aerodynamic interaction of fuselage,horizontal stabilator and vertical stabilator of UH-60 helicopter with short wing was computed and analyzed when the lifting surface parameters were adjusted.The results indicate that,change of the installation angle will have significant influence on the airflow around the lifting surface as the greatest influential parameter.Horizontal stabilator parameters,in particular the installation angle,can yield evident impact on the pressure coefficient of vertical stabilator and short wing,while decrease of the vertical stabilator span and increase of short wing installation angle can respectively increase their own pressure coefficient.