XFOIL Version 6.94 Calculated polar for: E197 (13.49%) 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 0.2888 0.00980 0.00369 -0.0605 0.6604 0.7549 0.500 0.3397 0.00968 0.00382 -0.0591 0.6509 0.8240 1.000 0.3965 0.00971 0.00400 -0.0586 0.6424 0.9025 1.500 0.4747 0.00987 0.00416 -0.0629 0.6327 0.9553 2.000 0.5616 0.01007 0.00432 -0.0696 0.6234 0.9830 2.500 0.6508 0.01016 0.00436 -0.0769 0.6134 1.0000 3.000 0.6941 0.01036 0.00457 -0.0749 0.6034 1.0000 3.500 0.7415 0.01058 0.00473 -0.0734 0.5935 1.0000 4.000 0.7880 0.01071 0.00490 -0.0716 0.5807 1.0000 4.500 0.8353 0.01088 0.00513 -0.0699 0.5674 1.0000 5.000 0.8830 0.01104 0.00533 -0.0683 0.5533 1.0000 5.500 0.9307 0.01117 0.00552 -0.0667 0.5376 1.0000 6.000 0.9780 0.01130 0.00574 -0.0649 0.5190 1.0000 6.500 1.0248 0.01146 0.00597 -0.0631 0.4978 1.0000 7.000 1.0693 0.01169 0.00630 -0.0610 0.4685 1.0000 7.500 1.1106 0.01211 0.00671 -0.0583 0.4301 1.0000 8.000 1.1412 0.01302 0.00739 -0.0540 0.3560 1.0000 8.500 1.1515 0.01496 0.00878 -0.0469 0.2521 1.0000 9.000 1.1540 0.01698 0.01042 -0.0389 0.1802 1.0000 9.500 1.1574 0.01913 0.01233 -0.0318 0.1288 1.0000 10.000 1.1627 0.02161 0.01465 -0.0263 0.0927 1.0000 10.500 1.1676 0.02457 0.01751 -0.0218 0.0619 1.0000 11.000 1.1577 0.02915 0.02187 -0.0173 0.0293 1.0000 11.500 1.1550 0.03371 0.02654 -0.0143 0.0213 1.0000 12.000 1.1596 0.03795 0.03097 -0.0122 0.0183 1.0000 12.500 1.1616 0.04263 0.03581 -0.0106 0.0166 1.0000 13.000 1.1559 0.04830 0.04163 -0.0092 0.0155 1.0000 13.500 1.1581 0.05345 0.04697 -0.0080 0.0147 1.0000 14.000 1.1660 0.05823 0.05196 -0.0071 0.0142 1.0000 14.500 1.1745 0.06322 0.05717 -0.0066 0.0135 1.0000 15.000 1.1816 0.06863 0.06285 -0.0066 0.0130 1.0000 15.500 1.1841 0.07480 0.06920 -0.0077 0.0120 1.0000 16.000 1.1847 0.08160 0.07626 -0.0088 0.0118 1.0000 16.500 1.1793 0.08960 0.08456 -0.0108 0.0115 1.0000 17.000 1.1673 0.09912 0.09441 -0.0140 0.0114 1.0000 17.500 1.1479 0.11043 0.10608 -0.0189 0.0113 1.0000 18.000 1.1191 0.12458 0.12070 -0.0263 0.0116 1.0000 18.500 1.0817 0.14180 0.13834 -0.0364 0.0118 1.0000 19.000 0.9420 0.19473 0.19189 -0.0668 0.0144 1.0000 19.500 0.7147 0.20717 0.20487 -0.0759 0.0301 1.0000 20.000 0.7206 0.21780 0.21550 -0.0794 0.0289 1.0000 20.500 0.7260 0.22662 0.22434 -0.0839 0.0287 1.0000 21.000 0.7244 0.23620 0.23391 -0.0902 0.0260 1.0000 21.500 0.7329 0.24416 0.24189 -0.0939 0.0237 1.0000 22.000 0.7433 0.25129 0.24905 -0.0970 0.0224 1.0000 22.500 0.7584 0.25777 0.25556 -0.0990 0.0214 1.0000