具有两个测量控制面的适应壁风洞理论与实验

本文研究了具有两个测量控制面的适应壁风洞。在超临界马赫条件下,做了二维NACA-0012翼型实验。在近洞壁处的两个控制面上测取了静压。基于上述测量,叙述了在适应壁风洞中得到无干扰流场的迭代方法。给出了为外场计算这两个控制面上静压的函数关系。评述了所选取迭代方法的收敛性。得到了一步收敛公式,并且在数字模拟风洞中得到证实。结果指出,应用一步迭代公式,所选取的迭代方法可以加速使流场收敛到无界条件。

Adaptive Wall Wind Tunnel with Two Measured Interfaces -Theory and Experiment-

An adaptive wall wind tunnel with two measured interfaces has been investigated. A two-dimensional NACA 0012 airfoil model at a supercritical Mach number was tested. Static pressure measurements near tunnel walls on two interfaces were taken. Based on these measurements an iterative procedure is described to obtain interference free flow in an adaptive wall wind tunnel. The functional relationships of static pressures on two measured interfaces for the exterior region are presented. The convergence of the selected iterative procedure is described. The one-step convergence formulae are obtained and validated by the simulation of a numerical wind tunnel. The results have indicated that the selected procedure is feasible to speed up the flow convergence to the unconfined condition in applying the one-step convergence formulae.