弹-翼-机身组合体干扰条件下航弹的气动特性计算

本文对伍德沃德提出的面元法加以改进,以某型飞机外挂某型航弹为例,在组合体外形表面上划分大量面元,用改进后的面元法计算了在弹-翼-机身组合体干扰条件下航弹的气动力,与未受干扰条件下的计算结果和吹风数据进行了比较,并作了简要分析.计算结果表明,航弹所受的干扰主要来自机翼,随着弹体的下落和距机翼距离的增加,各气动系数很快接近无干扰时的值.

CALCULATION OF AERODYNAMIC CHARACTERISTICS WITH EXISTENCE OF THE BOMB-WING-BODY CONFIGURATION DISTURBANCE

The panel method brought forward by Woodward was improved. Taking the bomb under the wing of the plane as an example, lots of panels were plotted on the external surface of the bomb-wing-body configuration. Based on the improved panel method, aerodynamic parameters of the bomb were calculated with the existence of the bomb-wing-body configuration disturbance and compared with the experimental values and values free of disturbance. A brief analysis is executed. The result indicates that the disturbance is mainly from the wing. With the dropping of the bomb and the increase of the distance between the bomb and the wing, aerodynamic parameters swiftly approach values free of disturbance.