Newton A. Mas
Results of wind-tunnel tests are presented for a wing with the leading edge swept back 63 degrees and of symmetrical section in combination with a body at Mach numbers from 0.5 to 0.95 and from 1.09 to 1.51. The test Reynolds numbers varied from 0.35 to 0.52 million. Measured lift, drag, and pitching-moment coefficients for the configuration are compared with corresponding calculated characteristics.
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