2.4m风洞飞行器模型抖振边界试验技术研究

Buffet onset measurement technique for aircraft model in 2.4m wind tunnel

介绍了该项研究的目的、要求、研究内容、试验条件及试验方法。文中简单介绍了半模和全模两期抖振试验的主要结果,提及了研究中存在的不足和将来研究应改进或加强的工作。笔者认为:该研究的抖振、测力、测压数据,其量值可靠、规律合理,可信度高。风洞流场的品质好,抖振边界测量精度高,且有大Re数的优势,更适合飞行器的抖振特性试验和研究。

The research goals, requirements, technical contents, test conditions and techniques are presented in this paper. Test results of a half-model and a complete model, deficiency of the research, and the follow-on improvements are also introduced. The results show that, the buffet, aerodynamic and pressure data are of reliable values and confident regularity. The wind tunnel's flow field is of high quality and buffet onset measurement is precise. It follows that 2.4m wind tunnel is suitable for buffet onset measurements and research for aircraft models.