摘 要：
这是我4年来航空方面研究的第三个课题阶段，研究了一种简易的、封闭式的、吸气使用风洞，用于后续的航空研究。在这个研究中，我的对照组使用的是航空气动仿真软件PROFILI中的数据，在对10个翼型进行仿真后，选出了NACA2412、NACA2415、NACA1412三种翼型，将这三种翼型的升阻比数作为对照组。然后通过风洞的实际测试与仿真数据进行对比。研究结果显示，实际测试结果与仿真结果有一定的差异，但在最大升阻比的排序、对应迎角的先后排序等方面有一定的相似性。达到了本次研究的基础目的，但结果并不好，所以由此确定了下一阶段的目标。
关键词：简易；风洞；HX711；升阻比
Abstract:
This work constitutes the third phase of my four-year research in the aerospace field, where a simple, closed-type, suction-based wind tunnel was developed for subsequent aerospace research. In this study, data from the aerospace aerodynamic simulation software PROFILI were used as the control group. After simulating 10 airfoils, three types—NACA2412, NACA2415 and NACA1412—were selected, and their lift-drag ratios were taken as the control data. Actual tests were then conducted using the self-developed wind tunnel, with the results compared against the simulation data. The findings indicate that there are certain discrepancies between the actual test results and the simulation data, yet similarities exist in aspects such as the ranking of maximum lift-drag ratios and the sequence of corresponding angles of attack. While the basic objectives of this research phase were achieved, the overall results were unsatisfactory, thus defining the research goals for the next phase.
Keywords: Simple wind tunnel; HX711; Lift-drag ratio
