摘要
1.引盲 研究细长翼及其前缘襟翼大幅度振动所引起的气动力,有助于了解非定常流的一些特点,对未来高机动飞机的设计和飞行控制也有重要意义。计算这种情况的气动力,因涉及大尺度非定常分离流问题,需要能模拟自由涡面变化的位流方法,如常值偶极子格网法〔‘、涡格法山。〕和混合涡法〔‘〕。这些方法及其应用还在发展中〔,,。〕。为拓展位流方法的应用范国,本文就涡格法对单。
The unsteady aerodynamic loads on wings with lending edge separation in inviscid incompressible flow are calculated using vortex-lattice method. The calculated results of delta and double delta wings with oscillating L.E. flaps not only show influence upon aerodynamic response as a result of different oscillatory frequencies and hinge line swept-back angles, but also reveal the phenomena of aerodynamic lag and nonlinear interaction associated with unsteady vortex flows.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1990年第9期A515-A520,共6页
Acta Aeronautica et Astronautica Sinica
基金
航空科学基金
关键词
机翼
非定常流
气动力
襟翼
incompressible flow, unsteady flow, separation flow, nu-merical calculation.
