XFOIL Version 6.94 Calculated polar for: woubair3 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.005 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.0778 0.06381 0.03377 -0.0028 0.9988 1.0012 -2.750 -0.0549 0.06386 0.03355 -0.0026 0.9988 1.0012 -2.500 -0.0315 0.06394 0.03339 -0.0025 0.9988 1.0012 -2.250 -0.0079 0.06407 0.03328 -0.0024 0.9988 1.0012 -2.000 0.0161 0.06424 0.03321 -0.0024 0.9988 1.0012 -1.750 0.0403 0.06445 0.03322 -0.0024 0.9988 1.0012 -1.500 0.0646 0.06469 0.03330 -0.0025 0.9988 1.0012 -1.250 0.0892 0.06497 0.03345 -0.0025 0.9988 1.0012 -1.000 0.1139 0.06528 0.03368 -0.0026 0.9988 1.0012 -0.750 0.1386 0.06563 0.03400 -0.0027 0.9988 1.0012 -0.500 0.1634 0.06601 0.03442 -0.0029 0.9988 1.0012 -0.250 0.1883 0.06643 0.03494 -0.0030 0.9988 1.0012 0.000 0.2133 0.06688 0.03557 -0.0032 0.9988 1.0012 0.250 0.2383 0.06738 0.03633 -0.0034 0.9988 1.0012 0.500 0.2634 0.06792 0.03722 -0.0036 0.9988 1.0012 0.750 0.2885 0.06853 0.03828 -0.0040 0.9988 1.0012 1.000 0.3135 0.06924 0.03956 -0.0045 0.9988 1.0012 1.250 0.3382 0.07010 0.04110 -0.0052 0.9988 1.0012 1.500 0.3616 0.07125 0.04307 -0.0063 0.9988 1.0012 1.750 0.3811 0.07304 0.04576 -0.0080 0.9988 1.0012 2.250 0.3865 0.08078 0.05456 -0.0122 0.9988 1.0012 2.500 0.3796 0.08570 0.05939 -0.0142 0.9988 1.0012 2.750 0.3767 0.09017 0.06377 -0.0162 0.9988 1.0012 3.000 0.3773 0.09427 0.06778 -0.0182 0.9988 1.0012 3.250 0.3803 0.09818 0.07159 -0.0203 0.9988 1.0012 3.500 0.3849 0.10191 0.07525 -0.0223 0.9988 1.0012 3.750 0.3905 0.10552 0.07879 -0.0243 0.9988 1.0012 4.000 0.3971 0.10905 0.08225 -0.0262 0.9988 1.0012 4.250 0.4043 0.11250 0.08565 -0.0281 0.9988 1.0012 4.500 0.4122 0.11590 0.08899 -0.0300 0.9988 1.0012 4.750 0.4205 0.11926 0.09231 -0.0319 0.9988 1.0012 5.000 0.4292 0.12259 0.09560 -0.0338 0.9988 1.0012