摘要
在柔性条件下,采用CFD/CSD(计算流体力学/计算结构力学)松耦合静气动弹性数值计算方法,计算分析了Ma为0.2时鸭翼位置对NACA64A010翼型静气弹特性的影响,结果表明:鸭翼高度不同的模型中,具有高位鸭翼的模型气动特性较好,升力系数比具有中位鸭翼的模型高45.4%,最大升阻比比具有中位鸭翼的模型高125%,弹性变形量近似;鸭翼距离不同的模型中,具有远距鸭翼的模型气动特性较好,升力系数比具有近距鸭翼的模型增大约45.13%,在达到失速迎角后,出现了明显的升力系数平台,同时其压力分布更加合理,弹性变形特性得到改善。计算结果可为研究鸭翼对前掠翼静气弹发散特性的影响提供了参考。
Under flexible conditions, based on the CFD/CSD(Computational Fluid Dynamics/Computational Structural Dynamics) loose coupling static aeroelastic numerical calculation method, the influence of different canard positions on static aeroelastic characteristics of NACA64 A010 airfoil was calculated and analyzed whenMa Is equal to 0.2. The results show that among the models with different height of canard, the model with high canard has better aerodynamic characteristics, its lift coefficient is 45.4% higher than that of the model with middle canard, its maximum lift-drag ratio is 125% higher than that of the model with middle canard, and their elastic deformation is similar;Among the models with different canard distances, the model with far canard has better aerodynamic characteristics, and its lift coefficient increases by about 45.13% compared with the model with close canard. After reaching the stall Angle of attack, there was an obvious lift coefficient platform. In the meanwhile, the pressure distribution was more reasonable and the elastic deformation characteristics was improved. The calculation results provided a reference for studying the influence of canard on the static aeroelastic divergence characteristics of the forward-swept wing.
作者
王振
苏新兵
王宁
马斌麟
WANG Zhen;SU Xinbing;WANG Ning;MA Binlin(School of Aviation Engineering,Air Force Engineering University,Xi’an 710038,China;School of Aviation Maintenance NCO,Air Force Engineering University,Xinyang 464000,China)
出处
《兵器装备工程学报》
CAS
CSCD
北大核心
2022年第10期220-226,共7页
Journal of Ordnance Equipment Engineering
基金
陕西省自然科学基础研究计划项目(2019JM-451)。
关键词
二元机翼
静气动弹性
鸭翼位置
CFD/CSD松耦合
two-dimensional wing
flexible wing
static aeroelasticity
canard position
CFD/CSD loose coupling
