XFOIL Version 6.94 Calculated polar for: E207 (12.04%) 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 0.2379 0.00734 0.00216 -0.0446 0.6003 0.8508 0.500 0.3050 0.00742 0.00232 -0.0462 0.5867 0.9348 1.000 0.3850 0.00765 0.00246 -0.0510 0.5733 0.9712 1.500 0.4705 0.00784 0.00253 -0.0573 0.5602 0.9881 2.000 0.5557 0.00798 0.00256 -0.0638 0.5470 0.9997 2.500 0.6034 0.00808 0.00264 -0.0623 0.5345 1.0000 3.000 0.6507 0.00823 0.00278 -0.0607 0.5215 1.0000 3.500 0.6984 0.00841 0.00293 -0.0591 0.5077 1.0000 4.000 0.7463 0.00860 0.00312 -0.0575 0.4929 1.0000 4.500 0.7943 0.00881 0.00333 -0.0559 0.4771 1.0000 5.000 0.8424 0.00903 0.00359 -0.0543 0.4602 1.0000 5.500 0.8903 0.00927 0.00386 -0.0527 0.4410 1.0000 6.000 0.9374 0.00957 0.00416 -0.0510 0.4187 1.0000 6.500 0.9842 0.00991 0.00454 -0.0492 0.3910 1.0000 7.000 1.0286 0.01042 0.00498 -0.0472 0.3517 1.0000 7.500 1.0672 0.01135 0.00567 -0.0443 0.2798 1.0000 8.000 1.0988 0.01286 0.00677 -0.0407 0.1955 1.0000 10.000 1.1970 0.01914 0.01229 -0.0224 0.0326 1.0000 10.500 1.1966 0.02175 0.01486 -0.0150 0.0158 1.0000 11.000 1.2056 0.02423 0.01748 -0.0102 0.0127 1.0000 12.000 1.2114 0.03157 0.02524 -0.0038 0.0103 1.0000 12.500 1.2145 0.03600 0.02987 -0.0023 0.0093 1.0000 13.000 1.2147 0.04108 0.03515 -0.0014 0.0091 1.0000 13.500 1.2111 0.04680 0.04107 -0.0011 0.0088 1.0000 14.000 1.2035 0.05326 0.04771 -0.0013 0.0083 1.0000 14.500 1.1979 0.05982 0.05448 -0.0019 0.0081 1.0000 15.000 1.1896 0.06703 0.06191 -0.0027 0.0079 1.0000 15.500 1.1776 0.07522 0.07039 -0.0040 0.0076 1.0000 16.000 1.1690 0.08363 0.07909 -0.0065 0.0076 1.0000 16.500 1.1585 0.09300 0.08876 -0.0104 0.0074 1.0000 17.000 1.1407 0.10409 0.10019 -0.0152 0.0074 1.0000 17.500 1.1197 0.11649 0.11290 -0.0215 0.0074 1.0000 18.000 1.0937 0.13080 0.12752 -0.0294 0.0074 1.0000 18.500 1.0628 0.14718 0.14420 -0.0389 0.0075 1.0000 19.500 1.0102 0.18189 0.17937 -0.0598 0.0078 1.0000 21.500 0.7444 0.24395 0.24208 -0.0914 0.0160 1.0000 22.000 0.7512 0.25267 0.25081 -0.0956 0.0159 1.0000 22.500 0.7546 0.26261 0.26077 -0.1009 0.0137 1.0000 23.000 0.7639 0.27012 0.26830 -0.1043 0.0125 1.0000 23.500 0.7740 0.27708 0.27529 -0.1074 0.0118 1.0000 24.000 0.7841 0.28627 0.28449 -0.1101 0.0113 1.0000 24.500 0.7871 0.29689 0.29511 -0.1152 0.0106 1.0000 25.000 0.7950 0.30582 0.30406 -0.1189 0.0097 1.0000 25.500 0.8029 0.31432 0.31258 -0.1224 0.0090 1.0000 26.000 0.8107 0.32241 0.32069 -0.1258 0.0083 1.0000 26.500 0.8185 0.33056 0.32888 -0.1292 0.0081 1.0000 27.000 0.8283 0.33902 0.33736 -0.1314 0.0077 1.0000 27.500 0.8342 0.34819 0.34655 -0.1350 0.0076 1.0000 28.000 0.8394 0.35743 0.35581 -0.1388 0.0076 1.0000 28.500 0.8440 0.36732 0.36571 -0.1428 0.0075 1.0000 29.000 0.8499 0.37721 0.37562 -0.1465 0.0069 1.0000 29.500 0.8558 0.38634 0.38477 -0.1499 0.0062 1.0000 30.000 0.8611 0.39540 0.39387 -0.1532 0.0058 1.0000 30.500 0.8661 0.40419 0.40268 -0.1565 0.0055 1.0000 31.000 0.8710 0.41229 0.41080 -0.1596 0.0050 1.0000