XFOIL Version 6.96 Calculated polar for: WORTMANN FX 08-S-176 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.500 -0.1096 0.09676 0.09234 -0.0873 0.5725 0.0080 -11.250 -0.1128 0.09192 0.08753 -0.0893 0.5721 0.0081 -11.000 -0.1225 0.08591 0.08156 -0.0918 0.5716 0.0082 -10.750 -0.1239 0.08206 0.07774 -0.0938 0.5708 0.0085 -10.500 -0.1287 0.07752 0.07323 -0.0961 0.5702 0.0086 -10.250 -0.1306 0.07365 0.06940 -0.0983 0.5695 0.0087 -10.000 -0.1544 0.06566 0.06149 -0.1035 0.5691 0.0087 -9.750 -0.2233 0.05308 0.04889 -0.1102 0.5690 0.0086 -9.500 -0.3010 0.04340 0.03896 -0.1047 0.5688 0.0087 -9.250 -0.3714 0.02984 0.02454 -0.0969 0.5687 0.0092 -9.000 -0.3588 0.02827 0.02277 -0.0954 0.5678 0.0096 -8.750 -0.3491 0.02597 0.02013 -0.0935 0.5670 0.0101 -8.500 -0.3353 0.02400 0.01781 -0.0920 0.5662 0.0108 -8.250 -0.3177 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1.1966 0.01180 0.00620 -0.0888 0.4914 0.8977 6.500 1.2219 0.01185 0.00632 -0.0888 0.4847 0.8992 6.750 1.2467 0.01186 0.00632 -0.0887 0.4764 0.9005 7.000 1.2709 0.01194 0.00643 -0.0886 0.4656 0.9016 7.250 1.2927 0.01210 0.00655 -0.0880 0.4505 0.9028 7.500 1.3085 0.01247 0.00681 -0.0865 0.4246 0.9042 7.750 1.3129 0.01319 0.00737 -0.0830 0.3941 0.9061 8.000 1.3107 0.01394 0.00803 -0.0783 0.3704 0.9083 8.250 1.3045 0.01492 0.00895 -0.0733 0.3512 0.9109 8.500 1.2980 0.01608 0.01008 -0.0688 0.3348 0.9136 8.750 1.2893 0.01761 0.01159 -0.0649 0.3215 0.9169 9.000 1.2667 0.02048 0.01445 -0.0608 0.3016 0.9202 9.250 1.2545 0.02321 0.01720 -0.0583 0.2879 0.9229 9.500 1.2288 0.02707 0.02101 -0.0552 0.2637 0.9262 9.750 1.2020 0.03100 0.02484 -0.0520 0.2368 0.9298 10.250 1.1506 0.03874 0.03236 -0.0463 0.1818 0.9352 10.500 1.1233 0.04306 0.03648 -0.0437 0.1415 0.9379 10.750 1.0986 0.04752 0.04071 -0.0418 0.0951 0.9405 11.000 1.0781 0.05190 0.04487 -0.0403 0.0479 0.9428 11.250 1.0665 0.05569 0.04852 -0.0395 0.0131 0.9451 11.750 1.0803 0.05977 0.05270 -0.0392 0.0081 0.9502 12.000 1.0885 0.06177 0.05477 -0.0392 0.0074 0.9537 12.250 1.0969 0.06382 0.05689 -0.0394 0.0070 0.9581 12.500 1.1034 0.06624 0.05941 -0.0397 0.0063 0.9645 12.750 1.1115 0.06857 0.06184 -0.0402 0.0060 0.9752 13.250 1.1247 0.07323 0.06664 -0.0408 0.0057 1.0000 13.500 1.1317 0.07562 0.06909 -0.0411 0.0056 1.0000 13.750 1.1375 0.07817 0.07172 -0.0415 0.0053 1.0000 14.000 1.1425 0.08087 0.07449 -0.0419 0.0051 1.0000 14.250 1.1485 0.08345 0.07713 -0.0424 0.0048 1.0000 14.500 1.1522 0.08639 0.08015 -0.0430 0.0046 1.0000 14.750 1.1559 0.08935 0.08318 -0.0435 0.0044 1.0000 15.000 1.1588 0.09243 0.08634 -0.0442 0.0043 1.0000 15.250 1.1613 0.09560 0.08958 -0.0448 0.0042 1.0000 15.500 1.1623 0.09904 0.09309 -0.0456 0.0041 1.0000 15.750 1.1637 0.10244 0.09656 -0.0464 0.0040 1.0000 16.000 1.1620 0.10633 0.10052 -0.0474 0.0039 1.0000