Abstract
Wave drag coefficients for several aircraft configurations have been computed using a full-potential method and have been compared with the results of parallel far-field (area rule) analyses and experimental zero-lift drag data. The aircraft analyzed included a supersonic cruise configuration, an advanced fighter concept, and the F-16 aircraft. The results of these studies indicate that the full-potential method generally gives wave drag levels that agree more closely with test data than do the far-field values. The full-potential method does not encounter problems when components such as wing or tail leading edges or canopy forward faces are at sonic conditions, as does the far-field technique. The full-potential code does, however, encounter problems in generating computational grids in deeply recessed areas such as diverters.
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