无尾飞机的高性能翼型设计研究  

Study of Airfoil Design for Tailless Aircraft

作　　者：常志英[1] 张彬乾[1] 

机构地区：[1]西北工业大学航空学院,陕西西安710072

出　　处：《航空计算技术》2009年第2期33-36,共4页Aeronautical Computing Technique

摘　　要：针对无尾布局飞机高升阻比与小低头力矩的翼型设计要求,在研究前加载与后卸载对翼型气动力影响的基础上,基于前加载与后卸载设计思想,采用调整翼型的厚度与弯度及其分布的翼型设计方法,很好地解决了无尾布局小低头力矩翼型设计问题,实现了具有高升阻比、小低头力矩的翼型设计目标。结果表明,该方法简单、易行,结果可靠,具有较好的工程实用性和操作性。Based on the airfoil design requirement of high lift- to- drag ratio and small pitch- down moment for tailless aircraft,the effec.ts of forward- loading and aftunloading on airfoil aerodynamic characteristics was investigated by CFD. Applying the idea of forward- loading and aftunloading,the distribution of thickness and camber of airfoil were optimized,and the airfoil design with higher lift- to- drag ratio and small pitch- down moment has been successfully performed. Results indicated that this airfoil design method is efficacious and convenient in engineering.

关 键 词：无尾飞机 翼型设计 气动性能 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]