XFOIL Version 6.94 Calculated polar for: EPPLER 694 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 ------- -------- --------- --------- -------- ------- ------- 0.500 0.6494 0.01310 0.00861 -0.1583 0.8070 0.8147 1.000 0.7210 0.01271 0.00820 -0.1614 0.8054 0.8216 3.000 0.9203 0.01251 0.00802 -0.1577 0.7770 0.8527 3.500 1.0047 0.01197 0.00747 -0.1640 0.7710 0.8562 4.000 1.0610 0.01199 0.00753 -0.1646 0.7633 0.8604 4.500 1.1072 0.01211 0.00773 -0.1631 0.7537 0.8655 5.000 1.1637 0.01215 0.00781 -0.1637 0.7416 0.8704 5.500 1.2258 0.01208 0.00774 -0.1654 0.7258 0.8749 6.000 1.2364 0.01220 0.00795 -0.1565 0.7063 0.8810 6.500 1.2223 0.01301 0.00888 -0.1433 0.6755 0.8873 7.000 1.2344 0.01378 0.00946 -0.1356 0.6188 0.8925 7.500 1.2457 0.01519 0.01055 -0.1283 0.5539 0.8962 8.000 1.2482 0.01706 0.01218 -0.1199 0.4918 0.9005 8.500 1.2477 0.01946 0.01428 -0.1117 0.4252 0.9050 9.000 1.2462 0.02233 0.01677 -0.1041 0.3474 0.9102 10.000 1.2640 0.02793 0.02176 -0.0935 0.2167 0.9181 10.500 1.2764 0.03081 0.02433 -0.0893 0.1556 0.9226 11.000 1.2891 0.03394 0.02717 -0.0855 0.1012 0.9271 11.500 1.3004 0.03747 0.03042 -0.0821 0.0526 0.9314 12.000 1.3055 0.04159 0.03432 -0.0782 0.0151 0.9368 12.500 1.3214 0.04484 0.03768 -0.0753 0.0098 0.9451 13.000 1.3386 0.04820 0.04122 -0.0731 0.0084 0.9575 13.500 1.3560 0.05184 0.04506 -0.0715 0.0079 1.0000 14.000 1.3714 0.05628 0.04969 -0.0703 0.0075 1.0000 14.500 1.3826 0.06130 0.05492 -0.0693 0.0072 1.0000 15.000 1.3897 0.06702 0.06084 -0.0686 0.0071 1.0000 15.500 1.3931 0.07343 0.06746 -0.0683 0.0069 1.0000 16.000 1.3943 0.08038 0.07462 -0.0685 0.0069 1.0000 16.500 1.3940 0.08780 0.08225 -0.0693 0.0068 1.0000 17.000 1.3939 0.09532 0.08998 -0.0705 0.0067 1.0000 17.500 1.3952 0.10275 0.09762 -0.0721 0.0067 1.0000 18.000 1.3976 0.11003 0.10512 -0.0740 0.0067 1.0000 18.500 1.4001 0.11728 0.11261 -0.0762 0.0067 1.0000 19.000 1.4013 0.12476 0.12035 -0.0789 0.0068 1.0000 19.500 1.3992 0.13284 0.12873 -0.0823 0.0068 1.0000 20.000 1.3924 0.14179 0.13802 -0.0866 0.0070 1.0000 20.500 1.3773 0.15247 0.14910 -0.0925 0.0071 1.0000 21.000 1.3531 0.16540 0.16246 -0.1005 0.0073 1.0000 21.500 1.3260 0.17952 0.17696 -0.1100 0.0075 1.0000 22.000 1.2954 0.19527 0.19304 -0.1212 0.0078 1.0000 22.500 1.2617 0.21291 0.21097 -0.1338 0.0080 1.0000 23.000 1.2324 0.23024 0.22845 -0.1456 0.0083 1.0000