新型人工转捩技术及风洞试验验证  

An innovative artificial transition technique and its validation through wind tunnel tests

作　　者：赵子杰[1] 高超[1] 张正科[1] 

机构地区：[1]西北工业大学航空学院,西安710072

出　　处：《航空学报》2015年第6期1830-1838,共9页Acta Aeronautica et Astronautica Sinica

基　　金：西北工业大学基础研究基金(JC-201103);航空科学基金(2013ZD53057)~~

摘　　要：给出了一种新型分布型人工转捩粗糙元设计技术,该技术解决了传统人工转捩方法在跨声速风洞试验中存在的效率低、可靠性和重复性差等问题。通过理论研究确定了该转捩技术的形式,包括粗糙元形状、高度和排列方式等技术参数以及针对不同模型的设计方案;同时对翼型模型(NACA0012)和全机模型(GBM-01或AGARD-B标模)在不同马赫数和迎角下分别进行了测压和测力风洞试验,借助升华法,对人工转捩技术的边界层转捩效果进行了验证研究。结果表明:在不同模型上使用不同的设计方案,该转捩技术可以得到可靠的固定转捩效果,并获得具有大气飞行中高雷诺数特点的气动力结果。An innovative artificial transition technique of distributed roughness elements is designed aimed at solving the problems encountered in fixed artificial transition tests with traditional methods in transonic wind tunnel. The shape, height and arrangement of the roughness elements and the design schemes for different configurations of models are determined by theoretical analysis. Meanwhile, the pressure coefficient on an airfoil surface （NACA0012） and the aerodynamic coefficients on an airplane model （GMB-01, or AGARD-B calibration model） are measured in the tests of artificial fixed transition. Subli- mation flow visualization technique is used to judge or identify transition. The differences between natural free transition and artificial fixed transition are analyzed. The effectiveness of the innovative artificial transition technique is observed and analyzed, The results show that this kind of innovative artificial transition technique can trigger boundary layer transition from laminar to turbulent and is able to obtain aerodynamic results comparable to those at the high Reynolds number atmospheric flight conditions.

关 键 词：跨声速空气动力学 跨声速风洞 人工转捩 粗糙元 升华法 边界层 

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]