XFOIL Version 6.94 Calculated polar for: SD8040 (10%) 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 0.3313 0.00723 0.00287 -0.0657 0.7955 0.9826 0.500 0.4040 0.00720 0.00260 -0.0689 0.7623 1.0000 1.000 0.4501 0.00733 0.00248 -0.0666 0.7251 1.0000 1.500 0.4982 0.00755 0.00246 -0.0647 0.6856 1.0000 2.000 0.5478 0.00784 0.00251 -0.0631 0.6445 1.0000 2.500 0.5981 0.00818 0.00263 -0.0617 0.6007 1.0000 3.000 0.6484 0.00858 0.00281 -0.0604 0.5552 1.0000 3.500 0.6987 0.00904 0.00307 -0.0591 0.5090 1.0000 4.000 0.7487 0.00956 0.00337 -0.0579 0.4624 1.0000 4.500 0.7985 0.01011 0.00376 -0.0567 0.4167 1.0000 5.000 0.8477 0.01075 0.00421 -0.0555 0.3723 1.0000 5.500 0.8966 0.01142 0.00474 -0.0543 0.3303 1.0000 6.500 0.9924 0.01294 0.00601 -0.0517 0.2507 1.0000 7.000 1.0387 0.01382 0.00678 -0.0503 0.2145 1.0000 7.500 1.0839 0.01478 0.00763 -0.0487 0.1814 1.0000 8.000 1.1280 0.01580 0.00861 -0.0470 0.1531 1.0000 8.500 1.1689 0.01703 0.00975 -0.0450 0.1284 1.0000 9.000 1.2099 0.01818 0.01095 -0.0429 0.1075 1.0000 9.500 1.2464 0.01958 0.01233 -0.0402 0.0892 1.0000 10.000 1.2780 0.02119 0.01397 -0.0370 0.0747 1.0000 10.500 1.3034 0.02285 0.01571 -0.0328 0.0639 1.0000 11.000 1.3225 0.02489 0.01787 -0.0281 0.0563 1.0000 11.500 1.3332 0.02772 0.02073 -0.0233 0.0502 1.0000 12.000 1.3538 0.02989 0.02316 -0.0200 0.0458 1.0000 12.500 1.3614 0.03335 0.02669 -0.0165 0.0419 1.0000 13.000 1.3724 0.03689 0.03052 -0.0138 0.0393 1.0000 13.500 1.3810 0.04074 0.03459 -0.0120 0.0366 1.0000 14.000 1.3825 0.04583 0.03978 -0.0107 0.0342 1.0000 14.500 1.3825 0.05150 0.04579 -0.0102 0.0327 1.0000 15.000 1.3794 0.05787 0.05248 -0.0109 0.0312 1.0000 15.500 1.3735 0.06499 0.05986 -0.0127 0.0298 1.0000 16.000 1.3664 0.07276 0.06783 -0.0153 0.0285 1.0000 16.500 1.3479 0.08290 0.07821 -0.0187 0.0273 1.0000 17.000 1.3232 0.09498 0.09070 -0.0252 0.0269 1.0000 17.500 1.2921 0.10929 0.10542 -0.0335 0.0266 1.0000 18.000 1.2518 0.12667 0.12319 -0.0443 0.0264 1.0000 18.500 1.1939 0.14988 0.14679 -0.0596 0.0267 1.0000