XFOIL Version 6.94 Calculated polar for: S3010-103-84 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 0.3076 0.00748 0.00259 -0.0551 0.6870 0.9978 0.500 0.3607 0.00763 0.00251 -0.0545 0.6592 1.0000 1.000 0.4138 0.00784 0.00246 -0.0537 0.6321 1.0000 1.500 0.4678 0.00805 0.00249 -0.0531 0.6029 1.0000 2.000 0.5222 0.00831 0.00257 -0.0526 0.5743 1.0000 2.500 0.5764 0.00862 0.00268 -0.0520 0.5461 1.0000 3.000 0.6309 0.00892 0.00288 -0.0516 0.5169 1.0000 3.500 0.6851 0.00927 0.00310 -0.0512 0.4879 1.0000 4.000 0.7387 0.00969 0.00338 -0.0507 0.4583 1.0000 4.500 0.7924 0.01009 0.00371 -0.0502 0.4276 1.0000 5.000 0.8455 0.01055 0.00411 -0.0497 0.3964 1.0000 5.500 0.8979 0.01108 0.00458 -0.0491 0.3643 1.0000 6.000 0.9495 0.01167 0.00509 -0.0485 0.3311 1.0000 6.500 1.0002 0.01235 0.00571 -0.0478 0.2973 1.0000 7.000 1.0497 0.01313 0.00641 -0.0469 0.2638 1.0000 7.500 1.0979 0.01401 0.00724 -0.0460 0.2315 1.0000 8.000 1.1445 0.01500 0.00816 -0.0448 0.2008 1.0000 8.500 1.1893 0.01610 0.00921 -0.0435 0.1722 1.0000 9.000 1.2330 0.01724 0.01039 -0.0421 0.1473 1.0000 9.500 1.2721 0.01867 0.01178 -0.0401 0.1253 1.0000 10.000 1.3092 0.02011 0.01328 -0.0379 0.1053 1.0000 10.500 1.3424 0.02164 0.01487 -0.0354 0.0883 1.0000 11.000 1.3675 0.02334 0.01663 -0.0318 0.0748 1.0000 11.500 1.3820 0.02551 0.01890 -0.0274 0.0654 1.0000 12.000 1.3967 0.02797 0.02147 -0.0240 0.0572 1.0000 12.500 1.4109 0.03079 0.02450 -0.0214 0.0498 1.0000 13.000 1.4159 0.03475 0.02859 -0.0195 0.0429 1.0000 13.500 1.4148 0.03983 0.03379 -0.0187 0.0350 1.0000 14.000 1.4089 0.04613 0.04029 -0.0191 0.0284 1.0000 14.500 1.3956 0.05389 0.04832 -0.0205 0.0244 1.0000 15.000 1.3753 0.06326 0.05787 -0.0235 0.0220 1.0000 15.500 1.3526 0.07369 0.06854 -0.0273 0.0207 1.0000 16.000 1.3374 0.08378 0.07891 -0.0315 0.0194 1.0000 16.500 1.3214 0.09451 0.08988 -0.0364 0.0184 1.0000 17.000 1.3056 0.10559 0.10117 -0.0417 0.0176 1.0000 17.500 1.2909 0.11679 0.11256 -0.0474 0.0169 1.0000 18.000 1.2769 0.12757 0.12350 -0.0525 0.0162 1.0000 18.500 1.2611 0.14013 0.13634 -0.0598 0.0158 1.0000 19.000 1.2430 0.15363 0.15014 -0.0680 0.0155 1.0000 19.500 1.2198 0.16899 0.16580 -0.0777 0.0154 1.0000 20.000 1.1851 0.18875 0.18588 -0.0905 0.0155 1.0000