本文为NACA0012翼型在NH-1风洞进行跨音速二维测压实验的研究报告。文中将本风洞的实验结果与国外大风洞的相应实验结果及国内某些理论计算结果作了比较。比较表明曲线规律一致,数据符合较好,说明按现行实验方法得到的本风洞跨音速测压数据是可靠的。本文还对参考点M数、洞壁干扰修正及激波位置等问题作了简要的分析。 This paper is the NACA0012 airfoil in the NH-1 wind tunnel transonic two-dimensional manometry test research report. In this paper, the experimental results of this wind tunnel are compared with the corresponding experimental results of wind tunnel in foreign countries and some theoretical calculation results in China. The comparison shows that the curves are consistent and the data are in good agreement, which shows that the transonic piezometric data obtained by the current experimental method is reliable. This article also made a brief analysis of the M number of reference points, the correction of the wall interference and the location of the shock wave.