XFOIL Version 6.94 Calculated polar for: FX S 03-182 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4692 0.01166 0.00560 -0.1100 0.6787 0.6692 0.500 0.5275 0.01176 0.00572 -0.1112 0.6757 0.6720 1.000 0.5850 0.01184 0.00584 -0.1122 0.6722 0.6749 1.500 0.6443 0.01194 0.00593 -0.1137 0.6691 0.6782 2.000 0.7042 0.01205 0.00605 -0.1152 0.6664 0.6808 2.500 0.7595 0.01215 0.00627 -0.1157 0.6613 0.6833 3.000 0.8196 0.01209 0.00618 -0.1170 0.6542 0.6865 3.500 0.8723 0.01175 0.00587 -0.1166 0.6394 0.6902 4.000 0.9238 0.01139 0.00554 -0.1159 0.6224 0.6929 4.500 0.9753 0.01125 0.00546 -0.1154 0.6075 0.6961 5.000 1.0243 0.01120 0.00553 -0.1144 0.5899 0.7003 5.500 1.0684 0.01116 0.00554 -0.1125 0.5581 0.7041 6.000 1.0869 0.01186 0.00589 -0.1058 0.4609 0.7080 6.500 1.0614 0.01425 0.00762 -0.0921 0.3386 0.7130 7.000 1.0424 0.01723 0.01012 -0.0816 0.2352 0.7177 7.500 1.0331 0.02054 0.01303 -0.0742 0.1505 0.7231 8.500 1.0487 0.02649 0.01856 -0.0658 0.0542 0.7342 9.000 1.0681 0.02902 0.02104 -0.0633 0.0325 0.7404 9.500 1.0919 0.03135 0.02342 -0.0614 0.0239 0.7481 10.000 1.1183 0.03353 0.02573 -0.0598 0.0173 0.7554 10.500 1.1411 0.03611 0.02837 -0.0581 0.0135 0.7639 11.000 1.1644 0.03876 0.03114 -0.0567 0.0116 0.7737 11.500 1.1894 0.04135 0.03389 -0.0555 0.0099 0.7848 12.000 1.2143 0.04401 0.03675 -0.0544 0.0084 0.7977 12.500 1.2380 0.04685 0.03979 -0.0534 0.0065 0.8127 13.000 1.2571 0.05019 0.04329 -0.0523 0.0040 0.8311 13.500 1.2736 0.05379 0.04710 -0.0511 0.0037 0.8548 14.000 1.2855 0.05744 0.05105 -0.0491 0.0035 0.8979 14.500 1.2929 0.06137 0.05524 -0.0472 0.0033 1.0000 15.000 1.3054 0.06630 0.06035 -0.0472 0.0032 1.0000 15.500 1.3159 0.07158 0.06582 -0.0475 0.0031 1.0000 16.000 1.3207 0.07776 0.07222 -0.0480 0.0031 1.0000 16.500 1.3194 0.08502 0.07971 -0.0490 0.0030 1.0000 17.000 1.3168 0.09272 0.08766 -0.0507 0.0030 1.0000 17.500 1.3102 0.10135 0.09653 -0.0530 0.0030 1.0000 18.000 1.3016 0.11056 0.10600 -0.0561 0.0030 1.0000 18.500 1.2927 0.12014 0.11584 -0.0601 0.0030 1.0000 19.000 1.2824 0.13017 0.12611 -0.0648 0.0030 1.0000 19.500 1.2730 0.14032 0.13651 -0.0702 0.0030 1.0000 20.000 1.2637 0.15065 0.14708 -0.0764 0.0030 1.0000 20.500 1.2543 0.16124 0.15790 -0.0831 0.0030 1.0000 21.000 1.2447 0.17214 0.16902 -0.0905 0.0030 1.0000 21.500 1.2353 0.18325 0.18036 -0.0984 0.0031 1.0000 22.000 1.2248 0.19490 0.19224 -0.1069 0.0031 1.0000 22.500 1.2131 0.20730 0.20489 -0.1160 0.0032 1.0000 23.000 1.1910 0.22331 0.22120 -0.1274 0.0033 1.0000