Abstract
A general harmonic gradient method has been developed for computations of unsteady supersonic flow handling given wing-body combinations, including arbitrary external store arrangements. The harmonic gradient model is adopted so that the total panel number is least affected by the given Mach number and reduced frequencies. To assess the accuracy and effectiveness of the present method, comparison with available data is given including the National Aerospace Laboratory's measurements for underwing store and wing-with-tip missile cases. The accurate prediction and ease of application of the present method suggests that it is fully developed for supersonic aeroelastic applications to realistic aircraft configurations.
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