分布式推进翼身融合飞行器气动特性研究

Aerodynamic characteristics research of a distributed propulsion blended-wing-body aircraft

基于下一代民用客机发展研究背景,针对某特种布局分布式推进翼身融合飞行器,采用数值仿真与风洞试验相结合的方法对其纵向气动特性及失速机理进行分析研究。介绍了该分布式推进翼身融合飞行器的气动构型及数值模型方法,针对当前翼身融合飞行器有无分布式动力影响下的纵向气动特性进行了对比分析,基于当前翼身融合飞行器无动力缩比模型风洞试验,在对数值模型方法进行校验的同时,结合流场显示结果对其大迎角失速发展过程中的流动机理进行分析研究。结果表明:当前分布式推进翼身融合体的分布式动力匣平台区域前缘展向流动是诱导失速发生的主要因素,但中部机身在大迎角下仍能够提供足够大的升力维持飞行,而分布式动力抽吸对于翼上流动具有较为明显的梳理作用,可以用于控制和改善翼身融合飞行器大迎角失速特性。

According to the development and research background of the next generation civil aircraft,the aerodynamic characteristics and stall mechanism of a specified distributed propulsion(DP)blended-wing-body(BWB)aircraft are analyzed and studied by combining the numerical simulation and the wind tunnel tests.Firstly,the DP BWB configuration and the numerical simulation methods are introduced.Secondly,the aerodynamic performance of the DP BWB aircraft between with and without the DP induced effects into consideration are compared and analyzed by using the numerical simulation.Finally,the stall mechanism is sorted out based on the wind tunnel flow-field visualization,and at the same time,the numerical simulation method is also validated.The results show that the span-wise flow along the leading edge(LE)of the plane platform for DP installation is the main factor to induce stall at high angle of attack(AOA),while the middle fuselage can still provide enough lift to maintain flight at high angle of attack,and the DP system has an obvious combination effect on the flow on the wing,which maybe is an effective way to control and improve the BWB stall characteristics at high AOA.