NACA0012翼型跨声速强迫运动非定常气动力模型  

Unsteady aerodynamic model of NACA0012 associated with forced oscillations and translations in transonic flight

作　　者：张庆 叶正寅[3] ZHANG Qing;YE Zhengyin(School of Aircraft, Xi′an Aeronautical University, Xi′an 710077, China;School of Mechanical & Aerospace Engineering, Nanyang Technological University, Singapore 639798, Republic of Singapore;School of Aeronautics, Northwestern Polytechnical University, Xi′an 710072, China)

机构地区：[1]西安航空学院飞行器学院,陕西西安710077 [2]南洋理工大学机械与航空工程学院,新加坡639798 [3]西北工业大学航空学院,陕西西安710072

出　　处：《哈尔滨工程大学学报》2020年第11期1683-1688,共6页Journal of Harbin Engineering University

基　　金：国家自然科学基金重点项目(11732013);校级科研基金项目(2018KY1226).

摘　　要：传统的一阶线性叠加的气动力模型不再适用于现代高机动性飞行器的非定常气动力建模,为了考察更高阶的气动力模型对非定常迟滞效应模拟的适用程度,本文采用自主发展的求解器,分别计算了NACA0012翼型在跨声速来流条件下做单自由度强迫沉浮、俯仰以及沉浮/俯仰两自由度耦合运动的非定常气动力的变化规律。然后在Etkin气动力模型的基础上,探讨了不同类型的高阶的气动导数在非定常气动力建模中的作用。研究结果表明:将Etkin气动力模型中升力和俯仰力矩对迎角的导数项由一阶拓展至二阶就可以较为精确地重构出翼型在强迫运动各阶段的非定常升力和俯仰力矩。It is unsuitable to model unsteady aerodynamics for high-agility modern aircraft by the traditional first-order linear superposition theory.For this study,in order to investigate the applicability of a higher order aerodynamic model to the simulation of hysteresis effects,the unsteady time histories of aerodynamics for NACA0012 associated with single-freedom forced motions,plunging and pitching,and coupled plunging and pitching motion under transonic conditions were investigated computationally based on in-house codes.The effects of various aerodynamic derivatives on aerodynamic models are discussed based on the Etkin aerodynamic model.Final results indicated that unsteady lift and pitching moment in forced single or coupled motions could be accurately regenerated if the Etkin model is expanded to the second order derivative of the angle of attack with respect to time.

关 键 词：跨声速 气动导数 气动力建模 沉浮运动 俯仰运动 耦合运动 Etkin模型 非定常气动力 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程]