文中通过数值计算和风洞试验相结合的方法研究卷弧翼不同安装方式滚转力矩特性的差异,为转速设计提供依据。通过研究得到以下结论:数值计算和风洞试验得出的滚转特性规律一致,验证了计算分析结论的可靠性;两种方法均再现了卷弧翼的自身诱导滚转现象,且在跨音速出现滚转换向。文中提出的两种对装形式均能消除卷弧翼自身诱导的滚转效应,利于导弹转速设计。

In this research, the numerical method and the wind tunnel test were adopted to investigate the characteristics of the rolling moments of the missile with curved wing. According to different arrangement of the wing which provides the basis information for rotating speed design, the rolling characteristics obtained by using both methods have the same trend, which validates the reliability of the numerical method. Two kinds of wing arrangement are promoted based on the obtained characteristics and can avoid rolling effect induced by the wings themselves, which is propitious to rotating speed design.