The results of an experimental investigation to determine the effects of Reynolds number on the flow characteristics over a delta wing at a Mach number of 2.4l are presented. The wing streamwise airfoil sections are based on the NACA OO-thickness series with the maximum thickness varying from 4 percent at the root section to 6.24 percent at the 90-percent spanwise station.. Force and pressure data for similar models having an aspect ratio of 1.57 were obtained over an angle-of-attacknrange at Reynolds numbers of 1.04 X 106, 3.9 X 106, 12.6 X 106,nand 18.3 X 106.nThe results showed negligible effects of a Reynolds number varia¬tion of 1.04 X 10° to 18.3 X 106 on the measured force characteristics over an angle-of-attack range from 0° to 6°. For angles of attack from 6° to 20°, and increase of Reynolds number from 12.6 X 106 to 18.3 X 106 likewise had no effect on the force data.
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