中空长航时无人机高升力层流翼型综合设计  

Integrated design of high-lift laminar airfoil for MALE UAV

作　　者：李权 曹燚 冯海勇 雷武涛 

机构地区：[1]西安飞机设计研究所总体气动设计研究所,陕西西安710089 [2]西安飞机设计研究所院长办公室,陕西西安710089

出　　处：《飞行力学》2014年第3期200-204,共5页Flight Dynamics

摘　　要：针对中空长航时无人机设计了所需的高升力、低力矩层流翼型。翼型参数化采用类函数/型函数方法;气动力求解采用XFOIL软件;寻优迭代采用基于精英策略的多目标遗传算法;并采用基于转捩模型的N-S方程对设计翼型进行了性能校核。设计结果显示,优化翼型具有明显的前加载特性,巡航升阻比高、低头力矩小,并具有不因提前转捩引发飞行安全的能力;优化翼型满足设计要求,所提方法具有良好的工程实用性。Towards the requirement of medium-altitude long-endurance （MALE） unmanned aerial vehicle （ UAV）, the required high-lift, low-torque laminar airfoil was designed. Airfoil was parameterized by the class function/shape function method, aerodynamic solution used XFOIL software, and multi-objective genetic algorithm NSGA-II was selected for optimization. The performance of designed airfoil was checked by N-S equation based on transition model. Calculation results show that optimized airfoil has obvious fore-loading characteristics, high cruising lift-to-drag ratio, small nose-down moment, and has the ability of not causing flight safety problem due to earlier transition. Optimized airfoil has well met the design requirements, and has good engineering practicability.

关 键 词：自然层流 高升力翼型 翼型设计 遗传算法 

分 类 号：V224[航空宇航科学与技术—飞行器设计] V279