摘要
当前有关大攻角机翼气动力的数值方法,多数只适用于不可压情况。对于亚音速范围,只对定常情况进行过计算,至今尚未见到非定常方面的文章。为此,我们将文献[1]的方法作进一步发展,使之适合于计算大攻角非线性问题。由于亚音速非定常时间滞后以及尾涡形状不断变化,所以计算比较复杂,本文在处理过程中力求简单。
A potential difference method for computing the aerodynamic loads on wings in fully unsteady, subsonic, high angles of attack flows with leading-edge or side-edge separations is presented in this paper. For this type of nonlinear problems, the developed method can provide the time varying aerodynamic loads and the velocity fields in time domains. The numer;cal results show in good agreement with the experimental data.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1989年第1期A070-A073,共4页
Acta Aeronautica et Astronautica Sinica
关键词
机翼气动力
亚音速
大攻角
机翼
subsonic, high angle of attack, unsteady, nonlinear aerodynamic.
