一种新的变前掠翼无人机气动布局

研究了一种新的变前掠翼无人机气动布局概念，在低、亚、跨和超声速状态下可通过改变机翼的前掠角来获取最佳的气动性能。根据设计指标和翼身融合技术初步设计了其几何外形，并采用三维Navier-Stokes方程数值模拟和对比分析了5种不同任务构型的气动特性。结果表明：①在Ma=0.6巡航时，平直翼加挂副油箱构型最大升阻比为14.55，而三角翼构型仅为8.29；②在Ma=0.4机动时，45°前掠翼构型失速迎角达到38°且具有最大的升力系数2.455，较平直翼构型提高了4.9%；③在Ma=1.5高速突防时，三角翼零升阻力系数最小，比平直翼加挂副油箱构型减小了14.4%，最大升阻比提高了34.6%；④所有计算状态下俯仰力矩特性均良好。研究结果验证了变前掠翼无人机气动布局新概念的合理性和先进性，可为高性能无人机的设计提供参考。

A New Aerodynamic Configuration of UAV with Variable Forward-swept Wing

A new aerodynamic configuration of unmanned aerial vehicle (UAV) with variable forward-swept wing was investigated, under which the forward-swept angle can be varied to obtain optimal aerodynamic characteristics during low, subsonic, tansonic and supersonic speeds. The basic figuration was designed according to the guidelines and blended wing-body technique, and aerodynamic characteristics of five different configurations were investigated by numerical method based on 3D Navier-Stokes equations. The results...