Abstract
Conclusions The harmonic gradient and the source distribution methods for computing supersonic aerodynamics are compared using the F-18 as a test case. For rigid-body modes, good agreement in pressure distributions is observed except for high reduced frequencies and near the wing tip. For oscillating flaps and control surfaces, the SPIP program requires a large number of source points to give the proper pressure jump across the hinge line, while the ZONA51C code handles the sharp pressure change quite satisfactorily without requiring additional elements to be placed near the hinge line. Flutter results for the F-18 wing agree very well between these two aerodynamic methods.
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