关键词: 机翼-机身-尾冀组合体, 涡流, 数值计算, 亚音速流

Abstract:

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.

Key words: Wing-body-fail combinations, Vortex flow, Numerical calculation, Subsonic flow