后掠会增加效率，但是会降低喘振裕度，而前掠有相反的趋势。
Backsweep can improve the efficiency at the expense of surge margin.
根据设计转速下的计算结果，预估了压气机设计点的喘振裕度。
The surge margin at design operating point was estimated by the numerical results.
一种新的颤振分析方法——鲁棒颤振裕度法被介绍，它利用结构奇异值理论将系统模型和试飞数据有机结合起来进行颤振边界预测。
Pass to incorporate organically the flight test data and the system model, make use of the structured singular value theories proceed the flutter boundary estimate.
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