直升机旋翼翼型的非定常气动特性计算方法与验证研究  

Evaluation of Airfoil Unsteady Aerodynamic Characteristics for the Helicopter Rotor

作　　者：孟微[1] 胡和平[1] 周云[1] MENG Wei HU Heping ZHOU Yun(Science and Technology on Rotorcraft Aeromechanics Laboratory, China Helicopter Research and Development Institute, Jingdezhen 333001, China)

机构地区：[1]中国直升机设计研究所,直升机旋翼动力学重点实验室,江西景德镇333001

出　　处：《航空科学技术》2017年第10期18-23,共6页Aeronautical Science & Technology

摘　　要：根据旋翼振动载荷分析需求,基于Leishman-Beddoes动态失速模型和翼型的风洞试验数据,进行翼型的非定常气动特性的建模和模型验证研究。本模型着重于非定常气动问题的物理表述,将附着流、气流分离、动态失速三个子模型进行综合,将经验系数简化为4个,其余18个参数均从翼型的静态、动态试验中获得。本模型与其他模型相比,经验系数少,物理表述清晰。与试验相关性分析表明,本模型的计算精度高、可靠性好,可用于旋翼振动载荷的计算分析。In this paper, the method of determining airloads for an airfoil undergoing unsteady aerodynamics was studied on the base of Leishman-Beddoes dynamic stall model to satisfy the requirement to pre-analysis of the rotor vibration load. The emphasis in this method was on a physical representation of the overall unsteady aerodynamic problem and it consisted of three distinct subsystems： an attached flow, a separated flow and dynamic stall model. The number of the indicial constants of the originality mode was reduced to 4, other 18 parameters can be obtained from the static and dynamic experimentation respectively. The empirical coefficients were less and the physical description was clearer than other semi-empirical models. This method is approved to be high accuracy, credibility and applicable in the rotor load pre-analysis by the correlation analysis with the results of dynamic stall test.

关 键 词：翼型气动特性 非定常 附着流 气流分离 动态失速 

分 类 号：V212.4[航空宇航科学与技术—航空宇航推进理论与工程]