Measurements were made of the flow field behind a rectangular and a triangular wing of aspect ratio 2 up-to angles of attack of 30°. The wings had a 4-inch semispan and were 5 percent thick with maximum thickness at midchord. Tests were performed at a Mach number of 2.46 and a Reynolds number of 3-12 million per foot. Flow-field measurements were taken for wing angles of attack of 0°, 6°, 20°, and 30Q.nThe downwash, sidewash, Mach number, and dynamic pressure in the wakes of both wings are compared with the predictions of various theoretical methods. The results show that for angles of attack up to 20° these flow quantities can be calculated with sufficient accuracy for most engineering purposes.nThe measured downwash, dynamic pressure, and Mach number in the wake of the rectangular wing were used to estimate the effectiveness of a hypothetical tail placed at various heights above and below the chord plane of the wing. The effectiveness was also computed using shock-expansion theory to determine the required flow quantities. These two calculations of the tail effectiveness are in fair agreement.
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