环量控制翼型非定常气动力建模  

Unsteady aerodynamic modeling of circulation control airfoil

作　　者：雷玉昌 张登成[3] 张艳华[3] LEI Yuchang;ZHANG Dengcheng;ZHANG Yanhua(Graduatee School,Air Force Engineering University,Xi'an 710051,China;The No.95034th Troop of People's Liberation Army,Baise 533600,China;Aeronautics Engineering College,Air Force Engineering University,Xi'an 710038,China)

机构地区：[1]空军工程大学研究生院,西安710051 [2]中国人民解放军95034部队,百色533600 [3]空军工程大学航空工程学院,西安710038

出　　处：《北京航空航天大学学报》2021年第10期2138-2148,共11页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：针对目前环量控制技术中射流参数与迎角对翼型气动特性的影响高度耦合,对应非定常气动力模型精度较差的研究现状,基于环量控制翼型强迫俯仰振动数值模拟数据,借助Kriging模型实现环量控制翼型的定常气动力插值,借助微分方程模型完成了适用于环量控制翼型的线性微分方程建模,采用两步线性回归参数辨识方法辨识线性微分方程模型中特征时间常数等参数,对高动量系数大振幅流动状态下的非线性影响进行修正。研究结果表明:基于Kriging模型实现的环量控制翼型定常气动力插值精度较传统气动导数模型高,建立的环量控制翼型非定常气动力模型能够精确预测不同流动状态下的气动力和力矩系数变化情况。In view of the high coupling of the effects of jet parameters and angle of attack on the aerodynamic characteristics of airfoils in current circulation control technology,the accuracy of the corresponding unsteady aerodynamic models is poor.Based on the numerical simulation data of forced pitching vibration of circulation control airfoils,the steady aerodynamic interpolation of the airfoils is realized with the help of Kriging model.With the help of differential equation model,the linear differential equation modeling suitable for circulation control airfoil is completed,and the characteristic time constant and other parameters in linear differential equation models are identified by two-step linear regression parameter identification method.The nonlinear influence of high momentum coefficient and large amplitude flow is modified.The results show that the steady aerodynamic interpolation accuracy of the circulation control airfoil based on the Kriging model is higher than that of the traditional aerodynamic derivative model.The unsteady aerodynamic model can accurately predict the changes of aerodynamic force and torque coefficient under different flow conditions.

关 键 词：环量控制 非定常气动力 翼型 数值模拟 气动力模型 参数辨识 

分 类 号：V212.1[航空宇航科学与技术—航空宇航推进理论与工程] V211.3