Abstract: A numerical model and computing method are presented for calculating the apparent areas of arbitrary shaped cross section of flight vehicle, which are then used to find the non-circular factors (i.e., the ratios of local normal-force coefficient to its equivalent-circle one) and the correcting coefficients of wing-body interference factor. The comparison of the results with some analytical values indicates that the present method has high accuracy and comprehensive versatility. It is actually useful to the prediction for aerodynamic characteristics of complicated flight vehicle at high / low angles of attack.

Key words: apparent area, wing-body interference, method of finite fundamental solution