高亚声速翼型柔壁自适应壁风洞实验技术  

High Subsonic Airfoil Test Technique on Flexible Adaptive Wind Tunnel

作　　者：代捷[1] 徐敏[1] 贺家驹[1] 左培初[1] 

机构地区：[1]西北工业大学

出　　处：《空气动力学学报》1995年第3期283-290,共8页Acta Aerodynamica Sinica

摘　　要：本文通过解跨声速小扰动方程求解假想外场，给出进行自适应壁风洞实验的迭代方案。用此方案，在堵塞比ε＝８％，实验段高弦比Ｈ／Ｃ＝１．５的情况下，对ＮＡＣＡ００１２翼型进行了高亚声速、迎角６°以下的验征性实验，实验结果与国外大风洞无干扰数据符合较好。同时，本文还给出了另一种自适应壁风洞实验方案：一步法，并将用此方法算出的壁面形状与迭代法的收敛壁面形状作了比较。结果表明：二者具有较好的一致性。本文研究表明：两种方案均有很好的应用前景。In this paper,a new iterative testing strategy is described for two dimensional model testing in transonic flexible adaptive wall wind tunnel by using the transonic small perturbation equation to com- pute the exterior flow fields.According to this strategy,experiments had been done in Northwestern Polytechnic University high speed flexible adaptive wall test section with a NACA0012 airfoil with 8%of block- age. The experimental results agree well with the interference-free data by large wind tunnel abr oad.Another strategy is also described in this paper,that is one-step method. The streamlined wall shapes computed by the two strategies are compared and found that they agree well,with each other.The study in this paper displays good prospects that the two strategies could apply to future transonic airfoil test.

关 键 词：柔壁风洞 自适应壁风洞 迭代法 洞壁干扰 

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]