The objective of this research was to design a model wing using previously developed two-dimensional computation techniques for prediction of airfoil leading-edge laminar separation. The wing was designed employing various criteria with the primary objective being to maximize the wing-lift coefficient at which drag rise is caused by leading-edge separation. The model wing was fabricated for test in the McDonnell Douglas Corporation Polysonic Wind Tunnel. The test results compared well with the predicted values and demonstrated substantial improvement in leading-edge separation lift coefficient over a previously tested wing designed without benefit of the laminar separation computation technique.
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Kenneth Tatum (1981) studied this question.