A numerical method for predicting steady and unsteady aerodynamic flows about aircraft wing configurations is presented. The numerical procedure solves the three-dimensional full-potential equation by a strongly implicit approximate factorization algorithm. Steady-flow analyses are obtained by relaxation, while unsteady analyses are calculated by time-accurate marching. In the present work, calculated steady, quasisteady, and unsteady wing surface pressures are presented for an F-5 fighter configuration and compared to experimental data for subsonic and transonic flight conditions.
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Malone et al. (1986) studied this question.
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