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.
出处
《飞行力学》
CSCD
北大核心
2014年第3期200-204,共5页
Flight Dynamics
关键词
自然层流
高升力翼型
翼型设计
遗传算法
natural laminar flow
high-lift airtbil
airfoil design
genetic algorithm