CAJ | 학술논문

机翼颤振是气动弹性的一个重要现象，并且是飞机结构破坏的一个主要原因。在跨声速阶段颤振临界速度呈现的“凹坑”现象，使得颤振最易在这一阶段发生。亚声速阶段利用偶极子网格法，超声速阶段利用ZONA51法，计算了AGARD 455．6机翼跨声速附近的颤振速度。总结其临界速度变化规律，符合跨声速阶段的“凹坑”现象。研究方法和所得结论具有普遍适用性，能够对跨声速机翼颤振速度做出较为简单方便但依旧精确的估算。
궤익전진시기동탄성적일개중요현상，병차시비궤결구파배적일개주요원인。재과성속계단전진림계속도정현적“요갱”현상，사득전진최역재저일계단발생。아성속계단이용우겁자망격법，초성속계단이용ZONA51법，계산료AGARD 455．6궤익과성속부근적전진속도。총결기림계속도변화규률，부합과성속계단적“요갱”현상。연구방법화소득결론구유보편괄용성，능구대과성속궤익전진속도주출교위간단방편단의구정학적고산。
Flutter is an important phenomenon of aeroelasticity ,also the main cause of airplane destruction . The pit that the flutter speed curve shows in transonic implies flutter is most likely to take place in tran‐sonic stage .In this paper ,double lattice method and ZONA51 method are adopted respectively in subsonic and supersonic ,which are used to compute the flutter speed in the range of transonic .The summarized flutter speed curve reveals the consistency with the phenomenon during the transonic stage . Research methods and conclusions are generally applicable ,and can be used to estimate transonic flutter speed more simply but still accurately .