Abstract
A comprehensive research program was conducted for the specific purpose of acquiring benchmark test data suitable for evaluations of three-dimensional transonic codes. High-quality data were obtained for three advanced technology wings by using a unique test apparatus and by devoting careful attention to details of the experiment. The test apparatus included provisions for removal of the wind tunnel boundary layer and measurements of far-field pressures. The test data were used in preliminary evaluations of three selected transonic computational methods. For these limited evaluations, nonconservative formulations more closely predicted measured pressures than conservative formulations. In addition, full potential solutions were found to be uniformly in better agreement with experiment than small disturbance results.
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