大前进比旋翼气动特性计算研究  

Computing Research on Aerodynamic Characteristics of Rotor with High Advance Ratio

作　　者：邱逢昌 樊枫[1] QIU Fengchang;FAN Feng(Scienee and Technology on Rotorcraft Aeromechanics Laboratory,China Helicopter Research and Development Institute,Jingdezhen Jiangxi 333001)

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：《中国科技纵横》2022年第1期85-88,共4页China Science & Technology Overview

摘　　要：基于CAMRADII对HART Ⅱ模型旋翼,开展了大前进比旋翼气动特性数值模拟。以HART Ⅱ模型旋翼为研究对象,建立一个大前进比旋翼计算模型,并将计算值与试验数据进行对比验证。在此基础上,针对HART Ⅱ模型旋翼在大前进比下的气动特性开展计算研究,分析了旋翼性能、旋翼功率和旋翼载荷在不同总距、不同前进比下的变化规律。计算结果表明:在相同总距下,旋翼拉力随前进比的增大而减小;在相同拉力下,旋翼升阻比随前进比的增大先增大后减小;在相同拉力下,旋翼诱导功率和型阻功率之和随前进比的增大而增大;在r/R=0.91截面处,前行侧产生负升力,随着前进比的增大负升力越大,后行侧产生的升力随着前进比的增大产生的升力越小。Based on CAMRAD II for HART II model rotor;a research on the aerodynamic characteristics of a rotor with a high advance ratio was carried out.Take the HART II model rotor as a research objection for the rotor with a high advance ratio;and compare the calculated value with the experimental data for verification.On this basis,a study was carried out on the aerodynamic characteristics of the HART II model rotor at a high advance ratio,the changes in rotor performance,rotor power and rotor load under different collective pitch and different advance ratio were analyzed.The calculation results show that:under the same collective pitch,the rotor thrust decreases with the advance ratio;under the same rotor thrust,the rotor lift-to-drag ratio first increases and then decreases with the advance ratiojunder the same rotor thrust,the calculated induced plus profile power increases with the advance ratio;at the section i/R=0.91;the advancing side produces negative lift,and the negative increase with the advance ratio;and the less lift will be produced at the retreating side as the advance ratio increase.

关 键 词：大前进比 气动特性 旋翼性能 旋翼功率 旋翼载荷 

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]