XFOIL Version 6.96 Calculated polar for: FX 60-157 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.750 -0.4903 0.10576 0.09865 -0.0585 1.0000 0.0457 -11.500 -0.5072 0.10006 0.09299 -0.0602 1.0000 0.0455 -11.250 -0.5251 0.09492 0.08788 -0.0614 1.0000 0.0451 -11.000 -0.5491 0.08969 0.08265 -0.0624 1.0000 0.0448 -10.750 -0.5736 0.08522 0.07816 -0.0626 1.0000 0.0445 -10.500 -0.5998 0.08124 0.07415 -0.0619 1.0000 0.0442 -10.250 -0.6277 0.07775 0.07060 -0.0603 1.0000 0.0439 -10.000 -0.6554 0.07491 0.06770 -0.0578 1.0000 0.0437 -9.750 -0.6824 0.07253 0.06528 -0.0543 1.0000 0.0433 -9.500 -0.7097 0.07014 0.06278 -0.0506 1.0000 0.0432 -9.250 -0.7295 0.06737 0.05983 -0.0475 1.0000 0.0432 -9.000 -0.7458 0.06434 0.05657 -0.0446 1.0000 0.0436 -8.500 -0.7637 0.05796 0.04949 -0.0394 1.0000 0.0446 -8.250 -0.7649 0.05478 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0.03618 0.02533 -0.0068 0.7988 0.8849 1.750 0.1081 0.03609 0.02523 -0.0059 0.7874 0.8899 2.000 0.1433 0.03584 0.02496 -0.0073 0.7803 0.8943 2.250 0.1643 0.03574 0.02484 -0.0068 0.7688 0.8993 2.500 0.1872 0.03566 0.02476 -0.0066 0.7579 0.9035 2.750 0.2228 0.03538 0.02449 -0.0081 0.7507 0.9067 3.000 0.2432 0.03536 0.02449 -0.0076 0.7383 0.9111 3.250 0.2704 0.03518 0.02432 -0.0079 0.7278 0.9153 3.500 0.3047 0.03478 0.02396 -0.0089 0.7188 0.9187 3.750 0.3275 0.03473 0.02396 -0.0086 0.7058 0.9225 4.000 0.3554 0.03455 0.02382 -0.0090 0.6950 0.9265 4.250 0.3901 0.03404 0.02337 -0.0099 0.6862 0.9305 4.500 0.4151 0.03388 0.02330 -0.0098 0.6728 0.9347 4.750 0.4437 0.03357 0.02306 -0.0100 0.6603 0.9389 5.000 0.4846 0.03270 0.02226 -0.0114 0.6523 0.9427 5.250 0.5104 0.03257 0.02224 -0.0113 0.6379 0.9474 5.500 0.5398 0.03233 0.02210 -0.0118 0.6239 0.9519 5.750 0.5718 0.03194 0.02180 -0.0124 0.6100 0.9567 6.000 0.6068 0.03144 0.02141 -0.0133 0.5953 0.9612 6.250 0.6423 0.03098 0.02104 -0.0143 0.5792 0.9660 6.500 0.6769 0.03063 0.02078 -0.0153 0.5623 0.9715 6.750 0.7138 0.03032 0.02056 -0.0167 0.5448 0.9768 7.000 0.7486 0.03008 0.02039 -0.0178 0.5258 0.9837 7.250 0.7799 0.02983 0.02018 -0.0184 0.5059 0.9972 7.500 0.8070 0.02986 0.02019 -0.0184 0.4849 1.0000 7.750 0.8289 0.03025 0.02061 -0.0181 0.4630 1.0000 8.000 0.8529 0.03069 0.02108 -0.0182 0.4422 1.0000 8.250 0.8788 0.03114 0.02153 -0.0184 0.4227 1.0000 8.500 0.9049 0.03165 0.02203 -0.0188 0.4037 1.0000 8.750 0.9249 0.03248 0.02292 -0.0187 0.3842 1.0000 9.000 0.9441 0.03334 0.02383 -0.0185 0.3647 1.0000 9.250 0.9639 0.03422 0.02473 -0.0184 0.3460 1.0000 9.500 0.9841 0.03518 0.02575 -0.0184 0.3288 1.0000 9.750 1.0048 0.03621 0.02685 -0.0185 0.3129 1.0000 10.000 1.0266 0.03726 0.02797 -0.0188 0.2987 1.0000 10.250 1.0488 0.03833 0.02910 -0.0190 0.2849 1.0000 10.500 1.0685 0.03947 0.03029 -0.0191 0.2708 1.0000 10.750 1.0830 0.04081 0.03174 -0.0187 0.2567 1.0000 11.000 1.0941 0.04233 0.03338 -0.0182 0.2431 1.0000 11.250 1.1058 0.04390 0.03507 -0.0178 0.2305 1.0000 11.500 1.1199 0.04544 0.03672 -0.0175 0.2191 1.0000 11.750 1.1342 0.04692 0.03822 -0.0173 0.2080 1.0000 12.000 1.1387 0.04906 0.04061 -0.0167 0.1969 1.0000 12.250 1.1436 0.05112 0.04280 -0.0161 0.1862 1.0000 12.500 1.1484 0.05309 0.04477 -0.0157 0.1758 1.0000 12.750 1.1471 0.05575 0.04761 -0.0153 0.1653 1.0000 13.000 1.1455 0.05860 0.05065 -0.0151 0.1556 1.0000 13.250 1.1463 0.06119 0.05326 -0.0151 0.1468 1.0000 13.500 1.1436 0.06456 0.05688 -0.0153 0.1383 1.0000 13.750 1.1439 0.06754 0.05990 -0.0157 0.1308 1.0000 14.000 1.1387 0.07143 0.06400 -0.0164 0.1230 1.0000 14.250 1.1350 0.07519 0.06782 -0.0173 0.1159 1.0000 14.500 1.1269 0.07982 0.07268 -0.0188 0.1090 1.0000 14.750 1.1218 0.08409 0.07702 -0.0203 0.1029 1.0000 15.000 1.1131 0.08923 0.08236 -0.0224 0.0973 1.0000 15.250 1.1145 0.09257 0.08560 -0.0238 0.0922 1.0000 15.500 1.0992 0.09942 0.09281 -0.0269 0.0882 1.0000 15.750 1.0886 0.10549 0.09906 -0.0299 0.0843 1.0000 16.000 1.0952 0.10811 0.10159 -0.0310 0.0800 1.0000 16.250 1.0720 0.11725 0.11106 -0.0360 0.0780 1.0000 16.500 1.0400 0.12884 0.12294 -0.0428 0.0766 1.0000 16.750 0.9860 0.14711 0.14138 -0.0538 0.0758 1.0000