Research on dynamic wind tunnel test technology of rotor airfoil
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摘要: 旋翼翼型的设计优化及性能确定亟须建立并发展翼型动态风洞试验技术。通过动力学仿真与结构优化设计，基于FL–11低速风洞研制出旋翼翼型两自由度动态试验装置，可实现俯仰/沉浮单自由或两自由度耦合运动，最高振荡频率达到5 Hz；基于FL–20连续式跨声速风洞研制出旋翼翼型高频高速动态试验装置，最高振荡频率达到17 Hz，试验最高雷诺数为5 × 106，模拟参数包线满足真实直升机参数要求；基于FL–14低速风洞研制出大尺度旋翼翼型动态试验装置，翼型模型弦长为800 mm，试验最高雷诺数达到4 × 106。完善了旋翼翼型动态试验精准测试相关技术，并开展了验证性试验，试验数据规律合理、量值可靠，表明试验系统及相关测试技术具有较高的可靠性，可为旋翼翼型动态气动特性试验评估提供重要的设备平台和技术支撑。Abstract: It is urgent to establish and develop the dynamic wind tunnel test technology for rotor airfoil design optimization and performance determination. Through dynamic simulation and structural optimization design, based on the FL–11 low-speed wind tunnel, a two degree of freedom dynamic test device for rotor airfoil is developed. It can not only complete the single degree of freedom dynamic motion of pitch and plunge, but also realize the coupling operation of pitch/plunge, with the highest oscillation frequency of 5 Hz. Based on the FL–20 continuous transonic wind tunnel, a set of high-frequency and high-speed oscillation test device for rotor airfoil is developed, with the maximum pitch oscillation frequency exceeding 17 Hz and the maximum test Reynolds number exceeding 5 × 106. The simulated parameter envelope meets the parameter requirements of the real helicopter. A large-scale rotor airfoil dynamic test device is developed based on the FL–14 low-speed wind tunnel, with the airfoil model chord length of 800 mm and the maximum test Reynolds number of 4 × 106. The accurate measuring and testing technique of the rotor airfoil dynamic test is developed, and the verification test is carried out. The results show that the dynamic test data of the rotor airfoil are reasonable and reliable, which indicates that the test system and related test technology have high reliability. It can provide important technical support for the research of rotor airfoil dynamic stall.
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Keywords:
- rotor /
- airfoil /
- dynamic /
- wind tunnel test /
- plunging oscillation
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图 1 低速风洞两自由度动态试验装置
Fig. 1 Dynamic test device of two degree of freedom in low speed wind tunnel
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图 3 低速风洞动态试验装置控制系统结构
Fig. 3 Control system structure of low speed wind tunnel dynamic test device
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图 4 旋翼翼型高频高速动态试验装置
Fig. 4 High frequency and high speed rotor airfoil dynamic test device
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图 5 大尺度旋翼翼型动态试验装置示意图
Fig. 5 Schematic diagram of dynamic test device for large scale airfoil model
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图 7 FL–14低速风洞旋翼翼型动态试验张线抑振
Fig. 7 Vibration suppression of rotor airfoil dynamic test in FL–14 low-speed wind tunnel
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图 10 旋翼翼型动态风洞试验传感器安装布置示意图
Fig. 10 Installation layout of sensors for dynamic wind tunnel test of rotor airfoil
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图 12 高速风洞动态天平与翼型连接方式
Fig. 12 Connection between dynamic balance and airfoil in high speed wind tunnel
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图 13 低速风洞翼型动态试验天平安装连接图
Fig. 13 Installation and connection diagram of airfoil dynamic test balance in low speed wind tunnel
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图 17 旋翼翼型动态振荡位移变形测量试验照片
Fig. 17 Test photo of oscillation displacement and deformation measurement for rotor airfoil
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图 18 耦合振荡试验频率影响结果对比
Fig. 18 Comparison of frequency influence results of coupled oscillation test
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图 19 旋翼翼型静态/动态风洞试验测力结果和测压结果对比
Fig. 19 Comparison of static and dynamic wind tunnel test results of rotor airfoil
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图 20 变振荡频率的翼型气动曲线
Fig. 20 Aerodynamic curve of airfoil with varying oscillation frequency
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图 21 不同平衡迎角下振荡翼型气动曲线
Fig. 21 Aerodynamic curves of oscillating airfoil at different balanced angles of attack
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图 22 高频高速动态试验装置运动能力考核试验结果
Fig. 22 Test results of motion ability assessment of high frequency and high speed dynamic test device
表 1 国内外主要气动研究机构动态试验模拟能力对比表
Table 1 Comparison of dynamic test simulation capabilities of major international aerodynamic research institutes
风洞名称 模型尺度（弦长）/m 来流马赫数 雷诺数/(105) 振荡幅值 振荡频率/Hz 运动自由度 美国NASA结冰风洞[37] 0.40 0.40（最大） 37 10° 5.0 俯仰 德国荷兰DNW TWG[12] 0.30 0.30～0.50 35 4°～7° 6.6 俯仰 法国ONERA F2[38] 0.50 0.16（常用） 19 10° 5.0 俯仰 俄罗斯TsAGI SVS−2[35] 0.18 0.30～0.60 25 5° 15.0 俯仰 中国南京航空航天大学
非定常风洞[33]0.30 0.10（最大） 7 10° （俯仰）
100 mm （沉浮）4.0（俯仰）
2.0（沉浮）俯仰/沉浮 中国西北工业大学 NF−3[39] 0.70 0.20（最大） 32 15° （俯仰）
100 mm （沉浮）5.0（俯仰）
3.0（沉浮）俯仰/沉浮 中国西北工业大学 NF−6[31] 0.20 0.30 14 10° 8.0 俯仰 中国气动中心 FL−11[40] 0.40 0.20～0.32 30 20° （俯仰）
150 mm （沉浮）6.0（俯仰）
5.0（沉浮）俯仰/沉浮 中国气动中心 FL−14[29] 0.80 0.25（最大） 40 30° 4.0 俯仰 中国气动中心 FL−20[41-42] 0.21 0.20～0.60 50 10° 17.0 俯仰 
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表 2 装置前五阶固有频率
Table 2 The first five order inherent frequency
阶数 固有频率/Hz 1 18.5 2 20.3 3 24.9 4 48.0 5 65.3
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表 3 旋翼翼型动态试验装置技术指标
Table 3 Technical specifications of rotor airfoil dynamic test device
风洞 测试内容 技术指标 FL−11 α −180°～180°，精度0.01°，在线连续可调 h −150～150 mm，精度0.01 mm，在线连续可调 α1 ≤30°，精度0.05°，在线连续可调 h1 ≤150 mm，精度0.05 mm，在线连续可调 fpi、fpl 俯仰0.1～6.0 Hz，沉浮0.1～5.0 Hz，
精度优于0.01 Hz，在线连续可调Rec 3 × 106 FL−20 α1 3°、5°、8°、10°，精度优于0.1° α0 −5°、0°、5°、10°，精度优于0.1° fpi 0.2～17.0 Hz，精度优于0.05 Hz Ma 0.2～0.6 Rec 5 × 106（压力2 atm） FL−14 α −180°～180°，精度0.01°，在线连续可调 α1 ≤30°，精度0.05°，在线连续可调 fpi 0.1～4.0 Hz，精度优于0.01 Hz，在线连续可调 Rec 4 × 106
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表 4 翼型模型结构优化结果
Table 4 Optimization results of airfoil model structure
优化目标 质量/kg 受载最大
等效应力/N最大位移
/mm第一阶固有
频率/Hz失效
指标初始值 12.567 252.15 7.46 56.10 0.728 优化值 8.288 227.16 5.74 63.28 0.319 变化值 4.279 25.34 1.72 7.18 0.409 变化率 34.05 9.91 23.06 12.80 56.18
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表 5 静态测量精准度结果
Table 5 Results of static measurement
俯仰角度 沉浮位移 名义值/(°) 实测值/(°) 名义值/mm 实测值/mm −5 −4.957 −30 −29.946 5 5.046 −15 −15.054 10 9.985 15 15.001 20 20.038 30 29.932
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表 6 俯仰–沉浮两自由度耦合振荡动态测量结果
Table 6 Dynamic measurement results of pitching and plunging coupled oscillation
俯仰角度 沉浮位移 名义值/(°) 实测值/(°) 名义值/mm 实测值/mm 5 4.951
（无吹风）30 30.930
（无吹风）4.964
（吹风，v=34 m/s）31.940
（吹风，v=34 m/s）4.947
（吹风，v=45 m/s）32.882
（吹风，v=45 m/s）
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