低速风洞和桨叶气流的理论计算和实验研究  

A Testing Study and Theoretical Cornputation of the Air Flow Concerning Low-speed Wind Tunnel and Wing Sections

作　　者：郭金基[1] 张应元[1] 谢耀康 

机构地区：[1]中山大学应用力学与工程系

出　　处：《中山大学学报（自然科学版）》1995年第4期1-6,共6页Acta Scientiarum Naturalium Universitatis Sunyatseni

摘　　要：从建立低速轴流风洞气流的贝努里能量方程出发，根据轴流风机的叶栅理论和相对运动的流体方程，求出经过桨叶的气流的全压力，应用翼型特性曲线，得到气体动力学参数和通过一系列的风洞试验测定气流的阻力系数。应用上述的方程和实验数据，可以计算风洞的压力、流量和功率，理论计算与实验结果基本相符。文中还指出风洞桨叶的安装角严重地影响气体动力学参数和风机的功率。最后给出算例。This paper presents the theoretical computation of the air flow of the low-speed wind tunned and wing sections.The Bernoulli energy equation of air flow of theaxis fluid wind tunnel is estabished.Based on the Vanes pale theory of the axis windmechine and relatiuely movement air flow equation, we found the total pressure of thefluid pass through wing sections.Appling to the characteristic curve of wing model,theparameter of air kinetics of the vanes is obtained Through a series of experiments con-ducted on wind tunnel,the resistanca coefficiends of the air fluid has been found.By ap-plying above aquations and experimental data,the total pressure,flow and power effi-ciency of the wind tunnel are calculated here;and they almost coincide.The paperpoints out how the fixing angle of the wing sections can greatly influence the kineties pa-rameters and power efficiency of the wind mechine in the wind tunnel.Some examplesare presented.

关 键 词：风洞 桨叶 气体动力学 气流 轴流风洞 低速风洞 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]