翼身融合布局与传统布局飞机结冰特性对比分析

Comparative Analysis of Icing Characteristics Between Blended-wing-body Aircraft and Traditional Layout Aircraft

翼身融合(BWB)布局是提升未来民机综合性能的重要布局方式,其结冰飞行安全问题逐渐受到人们重视。针对翼身融合布局飞机与常规布局飞机的结冰问题,本文通过数值模拟的方法来开展结冰特性研究。本文提出基于Navier-Stokes方程对空气流场进行求解,并应用欧拉法计算水滴撞击特性,之后采用Shallow-Water结冰热力学模型的结冰计算方法。首先,通过将翼身融合布局飞机和传统布局飞机的计算结果与风洞试验数据进行对比,验证空气流场计算的正确性,并将两者进行对比分析;其次,数值预测飞机表面冰形的特征,将两种布局飞机结冰特性进行对比,结果表明,结冰对两种布局飞机气动外形的破坏程度从后掠翼翼根至翼尖逐渐变大,但传统布局飞机结冰只发生在机翼前缘和机头处,而翼身融合布局飞机前部几乎都发生了结冰,可为相关的结冰特性研究及防除冰设计提供技术参考。

The Blended-Wing-Body(BWB)layout is an important layout to improve the comprehensive performance of civil aircraft,and its icing flight safety issue is gaining attention.The icing characteristics of BWB and conventional layout aircraft are studied by numerical simulation.In this paper,the air flow field is solved based on the Navier-Stokes equation,and the Euler method is used to calculate the water droplet impact characteristics.Then the icing calculation method of the Shallow-Water icing thermodynamic model is adopted.Firstly,the correctness of the air flow field calculation is verified by comparing the calculation results of the BWB layout aircraft and the conventional layout aircraft with the wind tunnel test data,and the two are compared and analyzed to understand the differences between the two layouts.Secondly,the characteristics of aircraft surface ice formation are numerically predicted and the icing characteristics of two aircraft layouts are compared.The results show that the damage of icing on the aerodynamic shape of both layouts is gradually increasing from the root to the tip of the swept wing,but the icing of the conventional layout aircraft occurs only at the leading edge of the wing and aircraft head,while the icing of the front part of the BWB layout aircraft occurs almost everywhere,which can provide a technical reference for the related icing characteristics research and anti-icing design.It can provide technical reference for the related icing characteristics research and anti-icing design.