摘要
基于势流方程,采用涡格法和三维离散涡相结合,模拟具有升力面分离涡的大攻角弹冀、弹体、尾翼组合体绕流。该方法适用于高亚音速、小攻角或大攻角有翼飞行器的压力分布、法向力和压力中心等气动特性的数值计算,并具有显示三维涡流场的能力。
Based on the potential equation, the vortex lattice and the three dimensional discrete linear vortices are successfully used to simulate the flow around the wing-body and wing-body-tail combinations with vortex separation sheded from lifting surfaces at high angles of attack. Some efficient techniques are adopted. The influence coefficients of velocity are divided into a variable part and an invariable part. For the latter, it is only computed one time. The two layer iterations are yielded in order to obtain the convergent solution more quickly. The internal layer iteration is used to control the allowable error of vortex strength, and the external layer iteration is used to control the allowable error of the vortical wakes. This method is especially suitable for calculating the pressure distribution, normal force, center of pressure and other aerodynamic characteristics exerted on the winged vehicle and the vortical strength distribution in any stations at large incidence, and posses the ability to exhibit the three dimensional vortex flow field.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1992年第2期B001-B006,共6页
Acta Aeronautica et Astronautica Sinica
关键词
机翼
机身
尾翼
组合体
Wing-body-fail combinations, Vortex flow, Numerical calculation, Subsonic flow
