飞机大攻角最大侧向力和偏航力矩预测的风洞试验方法研究  

Aircraft Side-force and Yawing Moment Measurement at High Angle of Attack in the Wind Tunnel

作　　者：胡汉东[1] 杨其德[1] 祝明红[1] 邓学蓥[2] 

机构地区：[1]中国空气动力研究与发展中心,绵阳621000 [2]北京航空航天大学,北京100191

出　　处：《航空工程进展》2011年第1期19-26,共8页Advances in Aeronautical Science and Engineering

摘　　要：具有尖头细长构型的飞行器在实际大攻角飞行和风洞试验中,侧向力系数和偏航力矩系数存在非确定性,给数据分析和使用带来很大困难。为了改变这种情况,本文发展了一种附加头部微扰动的试验技术,并在YF16模型大攻角试验中开展了应用。试验中通过压力分布确定头部分离流动特征,再采用人工转捩和头部微扰动技术在大攻角风洞试验中确定侧向力和偏航力矩系数。结果表明本文发展的试验方法改善了数据的一致性,在大攻角风洞模型试验中是有效的。In the real flight and wind tunnel testing of aircraft configuration with pointed nose slender,the coefficients of side force and yawing moment which are generated by high angle of attack are inconsistency,leading to difficulty for analyzing and using.In order to remove this difficulty,an experimental technique in which a micro-perturbation is attached on nose tip of model is suggested in wind tunnel testing for measuring side force and yawing moment.Based on this technique,an experimental study was conducted on YF16 model.The pressure distribution on the nose was measured to detect flow separation characteristics.Both techniques of artificial transition and micro-perturbation were applied in wind tunnel testing for the maximum side force and moment measurement at high angle of attack.Testing results show that the new techniques are effective in the wind tunnel experiment with model at high angle of attack.

关 键 词：大攻角 分离流 转捩 风洞试验 头部扰动 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]