XFOIL Version 6.94 Calculated polar for: S2027 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 0.2951 0.00980 0.00365 -0.0547 0.6389 0.7400 0.500 0.3498 0.00982 0.00365 -0.0543 0.6225 0.7633 1.000 0.4043 0.00987 0.00368 -0.0538 0.6060 0.7887 1.500 0.4578 0.00991 0.00375 -0.0531 0.5897 0.8148 2.000 0.5105 0.00998 0.00385 -0.0523 0.5733 0.8449 2.500 0.5609 0.01004 0.00397 -0.0509 0.5572 0.8792 3.000 0.6104 0.01010 0.00410 -0.0492 0.5409 0.9213 3.500 0.6789 0.01025 0.00424 -0.0517 0.5234 0.9659 4.000 0.7654 0.01050 0.00442 -0.0585 0.5046 0.9989 4.500 0.8110 0.01080 0.00466 -0.0572 0.4880 1.0000 5.000 0.8611 0.01115 0.00496 -0.0565 0.4707 1.0000 5.500 0.9120 0.01154 0.00533 -0.0559 0.4533 1.0000 6.000 0.9626 0.01197 0.00573 -0.0553 0.4355 1.0000 6.500 1.0125 0.01246 0.00619 -0.0545 0.4173 1.0000 7.000 1.0615 0.01295 0.00674 -0.0537 0.3988 1.0000 7.500 1.1094 0.01349 0.00733 -0.0526 0.3803 1.0000 8.000 1.1556 0.01408 0.00799 -0.0514 0.3606 1.0000 8.500 1.1985 0.01472 0.00866 -0.0496 0.3384 1.0000 9.000 1.2373 0.01549 0.00944 -0.0473 0.3149 1.0000 9.500 1.2742 0.01628 0.01032 -0.0447 0.2926 1.0000 10.000 1.3002 0.01727 0.01131 -0.0405 0.2683 1.0000 10.500 1.3200 0.01851 0.01256 -0.0357 0.2397 1.0000 11.000 1.3338 0.02031 0.01432 -0.0311 0.2068 1.0000 11.500 1.3447 0.02263 0.01660 -0.0270 0.1753 1.0000 12.000 1.3483 0.02579 0.01967 -0.0232 0.1419 1.0000 12.500 1.3438 0.03001 0.02378 -0.0199 0.1090 1.0000 13.500 1.3233 0.04106 0.03473 -0.0161 0.0586 1.0000 14.000 1.3055 0.04825 0.04196 -0.0157 0.0425 1.0000 14.500 1.2854 0.05647 0.05027 -0.0164 0.0316 1.0000 15.000 1.2672 0.06515 0.05909 -0.0181 0.0262 1.0000 15.500 1.2506 0.07422 0.06838 -0.0203 0.0230 1.0000 16.000 1.2391 0.08298 0.07733 -0.0229 0.0209 1.0000 16.500 1.2240 0.09263 0.08713 -0.0263 0.0193 1.0000 17.000 1.2133 0.10151 0.09616 -0.0291 0.0181 1.0000 17.500 1.2131 0.10923 0.10410 -0.0320 0.0171 1.0000 18.000 1.2124 0.11713 0.11218 -0.0352 0.0160 1.0000 18.500 1.2118 0.12514 0.12034 -0.0389 0.0150 1.0000 19.000 1.2121 0.13288 0.12822 -0.0425 0.0142 1.0000 19.500 1.2133 0.13985 0.13536 -0.0451 0.0134 1.0000 20.000 1.2071 0.14945 0.14524 -0.0504 0.0131 1.0000 20.500 1.1985 0.15976 0.15585 -0.0565 0.0130 1.0000 21.000 1.1845 0.17169 0.16809 -0.0639 0.0129 1.0000 21.500 1.1633 0.18597 0.18268 -0.0731 0.0129 1.0000 22.000 1.1290 0.20481 0.20186 -0.0853 0.0130 1.0000