迎角对NACA63-618型机翼力学特性影响研究  

The Influence of Angle of Attack on the Mechanical Properties of NACA63-618 Airfoil

作　　者：罗金武 郑向华[1] 滕鹏 范煦 张博扬 LUO Jinwu;ZHENG Xianghua;TENG Peng;FAN Xu;ZHANG Boyang(School of Intelligent Manufacturing,Chengdu Technological University,Chengdu 611730,China)

机构地区：[1]成都工业学院智能制造学院,成都611730

出　　处：《成都工业学院学报》2020年第4期23-29,共7页Journal of Chengdu Technological University

基　　金：成都工业学院校级科研项目(2020ZR024);成都工业学院实验室开放基金项目(2019ZH03);国家级大学生创新创业训练计划项目(S201911116024)。

摘　　要：为探究机翼迎角参数对力学特性的影响,采用流固耦合的数值模拟方法,实现对NACA63-618型等截面机翼的流场和结构的耦合模拟,并对不同设计迎角下的机翼进行力学特性影响分析。数值模拟结果表明,因翼面形状而产生的升力对机翼的变形起着主要作用,在迎角为6度的情况下,NACA63-618型机翼升阻比相对较高,且拥有合理的压力分布,利于升力的产生和高速下的稳定性飞行。In order to explore the influence of parameters of angle of attack on mechanical properties,the numerical simulation method of fluid-solid coupling was used to realize the coupling simulation of flow field and structure of NACA63-618 airfoil with constant cross section,and and the mechanical properties of airfoil under different angles of attack was analyzed.The numerical simulation results show that the lift generated by the shape of the wing surface plays a major role in the deformation of the wing..When the angle of attack is 6 degrees,the lift-drag ratio of the wing is relatively high,and has a reasonable pressure distribution,which is conducive to the generation of lift and stable flight at high speed.

关 键 词：NACA63-618翼型 等截面 迎角设计 流固耦合 数值模拟 

分 类 号：V211.412[航空宇航科学与技术—航空宇航推进理论与工程]