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本文所述的实验研究,是将自行研制的M-I型表面热膜用于测定NACA0012翼型上表面的转捩区的实验。当翼型迎角α改变时转捩区位置随之改变,见图3。实验证明这种技术是令人满意的。
The experimental study described in this paper is an experiment of using self-developed M-I surface hot film to determine the transition zone of the upper surface of NACA0012 airfoil. When the airfoil α is changed, the position of the transition zone changes, as shown in Figure 3. Experiments show that this technique is satisfactory.