XFOIL Version 6.94 Calculated polar for: FX 62-K-153/20 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.6852 0.01182 0.00685 -0.1647 0.7723 0.7089 0.500 0.7449 0.01171 0.00668 -0.1658 0.7653 0.7151 1.000 0.8072 0.01166 0.00658 -0.1676 0.7603 0.7198 1.500 0.8601 0.01179 0.00678 -0.1674 0.7545 0.7239 2.000 0.9137 0.01180 0.00687 -0.1674 0.7475 0.7284 2.500 0.9749 0.01164 0.00672 -0.1688 0.7404 0.7332 3.000 1.0306 0.01150 0.00662 -0.1691 0.7290 0.7383 3.500 1.0869 0.01122 0.00639 -0.1694 0.7190 0.7420 4.000 1.1376 0.01114 0.00644 -0.1686 0.7065 0.7460 4.500 1.1863 0.01091 0.00625 -0.1671 0.6856 0.7509 5.000 1.2222 0.01081 0.00595 -0.1629 0.6317 0.7557 5.500 1.2570 0.01124 0.00623 -0.1591 0.5834 0.7598 6.000 1.2729 0.01196 0.00677 -0.1514 0.5278 0.7645 6.500 1.2603 0.01377 0.00808 -0.1390 0.4328 0.7694 7.000 1.2495 0.01616 0.00999 -0.1284 0.3364 0.7744 7.500 1.2452 0.01901 0.01235 -0.1202 0.2492 0.7787 8.000 1.2505 0.02170 0.01468 -0.1141 0.1724 0.7835 8.500 1.2631 0.02430 0.01702 -0.1095 0.1186 0.7877 9.000 1.2835 0.02663 0.01922 -0.1061 0.0861 0.7921 9.500 1.3008 0.02936 0.02177 -0.1028 0.0523 0.7963 10.000 1.3239 0.03179 0.02417 -0.1003 0.0353 0.8007 10.500 1.3459 0.03432 0.02674 -0.0978 0.0228 0.8053 11.000 1.3664 0.03716 0.02962 -0.0954 0.0135 0.8098 11.500 1.3827 0.04059 0.03309 -0.0929 0.0035 0.8143 12.000 1.4006 0.04411 0.03674 -0.0909 0.0017 0.8185 12.500 1.4190 0.04761 0.04047 -0.0891 0.0014 0.8240 13.000 1.4347 0.05159 0.04470 -0.0875 0.0013 0.8294 13.500 1.4490 0.05600 0.04935 -0.0862 0.0012 0.8346 14.000 1.4611 0.06090 0.05452 -0.0853 0.0012 0.8398 14.500 1.4693 0.06641 0.06033 -0.0846 0.0012 0.8456 15.000 1.4734 0.07285 0.06707 -0.0844 0.0012 0.8520 16.000 1.4689 0.08857 0.08344 -0.0862 0.0012 0.8663 16.500 1.4600 0.09800 0.09321 -0.0884 0.0012 0.8752 17.000 1.4477 0.10820 0.10375 -0.0915 0.0012 0.8864 17.500 1.4310 0.11873 0.11465 -0.0948 0.0012 0.9086 18.500 1.3937 0.14153 0.13806 -0.1051 0.0012 1.0000 19.000 1.3774 0.15428 0.15109 -0.1128 0.0012 1.0000 19.500 1.3606 0.16738 0.16445 -0.1214 0.0012 1.0000 20.000 1.3440 0.18073 0.17806 -0.1305 0.0012 1.0000 20.500 1.3282 0.19421 0.19177 -0.1399 0.0012 1.0000 21.000 1.3130 0.20789 0.20566 -0.1497 0.0012 1.0000 21.500 1.2993 0.22166 0.21962 -0.1594 0.0013 1.0000 22.000 1.2894 0.23489 0.23302 -0.1687 0.0013 1.0000 22.500 1.2810 0.24826 0.24654 -0.1779 0.0013 1.0000