变弯度柔性机翼与多段翼型气动特性对比研究  

Comparative Study on Aerodynamic Characteristics of Variable-Blend Flexible Wing and Muti-Element Wing

作　　者：李嘉仪 黄再兴 张宪政 童明波[1] 陈吉昌 Li Jiayi;Huang Zaixing;Zhang Xianzheng;Tong Mingbo;Chen Jichang(Ministerial Key Discipline Laboratory of Advanced Design Technology of Aircraft,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;AVIC Jiangxi Hongdu Aviation Industry Group Company Ltd.,Nanchang 330096,China)

机构地区：[1]南京航空航天大学飞行器先进设计技术国防重点学科实验室,江苏南京210016 [2]江西洪都航空工业集团有限责任公司,江西南昌330096

出　　处：《航空科学技术》2022年第12期54-61,共8页Aeronautical Science & Technology

基　　金：航空科学基金(20182352015)。

摘　　要：随着民机飞行性能要求的不断提高,机翼变体技术逐渐成为研究热点,在柔性变形翼设计与传统后缘襟翼优化方面研究成果逐渐增多,而对于两种机翼构型在不同飞行工况下的气动性能对比则研究较少。本文以标准NACA4418翼型为基础,分别建立柔性变后缘弯度机翼及二段翼二维模型,通过求解定常不可压Navier-Stokes方程,研究了在飞行参数及后缘偏转角相同的情况下两种翼型的升阻力特性,并分别讨论不同迎角、不同后缘弯度对两种翼型气动性能的影响。本文结果对民机变弯度机翼构型设计具有一定的工程参考意义。With the continuous improvement of civil aircraft flight requirements,wing variant technology has gradually become a research hotspot.Research achievements in there is lessvariable-bend flexible wings design and traditional trailing edge flap optimization have gradually increased,while research on performance comparison between two wing configurations under different flight conditions.In this paper,based on the standard NACA4418 airfoil,two dimensional models of variable-bend flexible wings and two-stage wing are established respectively.By solving the steady incompressible Navier Stokes equations,the lift drag characteristics of the two airfoils are studied under the same flight parameters and trailing edge deflection angle,and the effects of different angles of attack and different trailing edge cambers on the aerodynamic performance of the two airfoils are discussed respectively.The results of this paper have engineering reference significance for the configuration design of civil aircraft wing with variable curvature.

关 键 词：变弯度机翼 柔性翼 后缘襟翼 CFD仿真 

分 类 号：V224.5[航空宇航科学与技术—飞行器设计]