In order to indicate the effects of Reynolds number and other vari¬ables on the drag due to lift of delta wings for Mach numbers up to 2.0, the results of several investigations of wing-body combinations having plane delta wings with aspect ratios from 2 to 4 have been assembled for comparison and brief analysis.nThe effects of Reynolds number, leading-edge radius, and thickness ratio could generally be correlated with Reynolds number based on the leading-edge radius as a parameter. The effects of leading-edge Reynolds number on drag due to lift were large at Mach numbers less than 0.25-However, with increases in Mach number, the effects decreased and were almost negligible at a Mach number of 2.0. The effects of aspect ratio and trimming were large, as would be expected.nIt was indicated at least for subsonic and transonic speeds that improvement in the drag due to lift might be obtained from wing modifica-tions designed to inhibit flow separation.
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