XFOIL Version 6.94 Calculated polar for: FX 69-PR-281 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.6113 0.01780 0.00980 -0.1305 0.4219 0.2656 0.500 0.6542 0.01814 0.00996 -0.1281 0.4060 0.2720 1.000 0.7039 0.01843 0.01020 -0.1268 0.3949 0.2771 1.500 0.7517 0.01861 0.01033 -0.1254 0.3827 0.2850 2.000 0.7993 0.01916 0.01078 -0.1241 0.3692 0.2927 2.500 0.8452 0.01954 0.01123 -0.1225 0.3613 0.3003 3.000 0.8888 0.02021 0.01180 -0.1206 0.3516 0.3081 3.500 0.9380 0.02081 0.01237 -0.1198 0.3424 0.3207 4.000 0.9861 0.02152 0.01313 -0.1188 0.3363 0.3333 4.500 1.0288 0.02216 0.01389 -0.1172 0.3309 0.3472 5.000 1.0698 0.02298 0.01479 -0.1154 0.3248 0.3633 5.500 1.1121 0.02388 0.01574 -0.1140 0.3192 0.3832 6.000 1.1568 0.02505 0.01682 -0.1129 0.3109 0.4031 6.500 1.1956 0.02617 0.01815 -0.1114 0.3059 0.4272 7.000 1.2270 0.02746 0.01962 -0.1093 0.3010 0.4499 7.500 1.2611 0.02887 0.02114 -0.1075 0.2962 0.4747 8.500 1.3252 0.03213 0.02451 -0.1042 0.2846 0.5282 9.000 1.3636 0.03389 0.02639 -0.1031 0.2777 0.5613 9.500 1.3831 0.03629 0.02904 -0.1011 0.2744 0.5967 10.000 1.4018 0.03897 0.03199 -0.0994 0.2695 0.6393 10.500 1.4243 0.04162 0.03489 -0.0980 0.2653 0.6924 11.000 1.4443 0.04430 0.03786 -0.0965 0.2608 0.7731 11.500 1.4428 0.04629 0.04012 -0.0908 0.2564 1.0000 12.000 1.4710 0.04919 0.04295 -0.0898 0.2494 1.0000 12.500 1.4720 0.05425 0.04821 -0.0892 0.2473 1.0000 13.000 1.4648 0.06044 0.05459 -0.0888 0.2437 1.0000 13.500 1.4543 0.06728 0.06161 -0.0889 0.2394 1.0000 14.000 1.4473 0.07396 0.06841 -0.0894 0.2348 1.0000 14.500 1.4538 0.07908 0.07353 -0.0899 0.2302 1.0000 15.000 1.4713 0.08286 0.07725 -0.0900 0.2252 1.0000