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 = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.500 -0.0586 0.08835 0.08473 -0.0959 0.5728 0.0131 -10.250 -0.0657 0.08179 0.07822 -0.0996 0.5723 0.0142 -10.000 -0.0656 0.07792 0.07436 -0.1014 0.5716 0.0142 -9.750 -0.0695 0.07321 0.06967 -0.1039 0.5709 0.0142 -9.500 -0.0783 0.06739 0.06389 -0.1076 0.5701 0.0143 -9.250 -0.3732 0.02749 0.02290 -0.0980 0.5723 0.0101 -9.000 -0.3698 0.02469 0.01970 -0.0952 0.5714 0.0105 -8.750 -0.3526 0.02370 0.01851 -0.0940 0.5703 0.0107 -8.500 -0.3487 0.02047 0.01484 -0.0913 0.5693 0.0113 -8.250 -0.3268 0.01988 0.01419 -0.0907 0.5688 0.0115 -8.000 -0.3028 0.01962 0.01391 -0.0903 0.5682 0.0119 -7.750 -0.2790 0.01927 0.01350 -0.0899 0.5676 0.0123 -7.500 -0.2551 0.01880 0.01295 -0.0895 0.5669 0.0128 -7.250 -0.2315 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1.3336 0.00939 0.00498 -0.0952 0.4684 0.9073 7.500 1.3551 0.00957 0.00512 -0.0945 0.4481 0.9088 7.750 1.3709 0.01004 0.00545 -0.0929 0.4182 0.9105 8.000 1.3777 0.01092 0.00612 -0.0898 0.3779 0.9122 8.250 1.3768 0.01202 0.00700 -0.0855 0.3391 0.9142 8.500 1.3662 0.01311 0.00792 -0.0795 0.3060 0.9168 8.750 1.3461 0.01459 0.00923 -0.0724 0.2715 0.9197 9.000 1.3124 0.01688 0.01142 -0.0648 0.2389 0.9237 9.250 1.2891 0.01988 0.01442 -0.0607 0.2201 0.9273 9.500 1.2596 0.02403 0.01852 -0.0572 0.1970 0.9307 9.750 1.2264 0.02841 0.02280 -0.0535 0.1697 0.9334 10.000 1.2052 0.03176 0.02609 -0.0505 0.1485 0.9362 10.250 1.1826 0.03527 0.02952 -0.0476 0.1228 0.9391 10.500 1.1583 0.03910 0.03321 -0.0449 0.0900 0.9419 10.750 1.1312 0.04361 0.03752 -0.0426 0.0457 0.9442 11.000 1.1256 0.04655 0.04038 -0.0417 0.0254 0.9459 11.250 1.1214 0.04942 0.04322 -0.0408 0.0098 0.9479 11.500 1.1275 0.05137 0.04523 -0.0404 0.0085 0.9502 11.750 1.1353 0.05316 0.04708 -0.0401 0.0078 0.9526 12.000 1.1429 0.05504 0.04902 -0.0399 0.0076 0.9556 12.250 1.1491 0.05711 0.05116 -0.0397 0.0071 0.9589 12.500 1.1572 0.05907 0.05318 -0.0397 0.0068 0.9644 12.750 1.1624 0.06161 0.05580 -0.0400 0.0064 0.9713 13.000 1.1695 0.06410 0.05836 -0.0407 0.0062 0.9926 13.250 1.1727 0.06677 0.06110 -0.0408 0.0060 1.0000 13.500 1.1732 0.06986 0.06426 -0.0410 0.0058 1.0000 13.750 1.1760 0.07273 0.06720 -0.0413 0.0057 1.0000 14.000 1.1824 0.07523 0.06975 -0.0417 0.0056 1.0000 14.250 1.1878 0.07787 0.07245 -0.0421 0.0055 1.0000 14.500 1.1916 0.08073 0.07537 -0.0426 0.0054 1.0000 14.750 1.1947 0.08373 0.07843 -0.0431 0.0053 1.0000 15.000 1.1978 0.08676 0.08153 -0.0437 0.0051 1.0000 15.250 1.1996 0.09002 0.08486 -0.0443 0.0050 1.0000 15.500 1.2024 0.09315 0.08805 -0.0450 0.0049 1.0000