XFOIL Version 6.94 Calculated polar for: EPPLER 587 AIRFOIL 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 0.6145 0.01419 0.00841 -0.1413 0.7378 0.7276 0.500 0.6819 0.01418 0.00821 -0.1444 0.7311 0.7335 1.000 0.7259 0.01416 0.00829 -0.1424 0.7219 0.7379 1.500 0.7842 0.01409 0.00817 -0.1433 0.7137 0.7430 2.000 0.8413 0.01415 0.00820 -0.1441 0.7053 0.7483 2.500 0.8955 0.01409 0.00814 -0.1444 0.6950 0.7540 3.000 0.9564 0.01404 0.00805 -0.1457 0.6865 0.7584 3.500 1.0002 0.01405 0.00820 -0.1438 0.6751 0.7635 4.000 1.0627 0.01398 0.00807 -0.1455 0.6647 0.7690 4.500 1.1064 0.01395 0.00816 -0.1436 0.6513 0.7751 5.000 1.1562 0.01393 0.00822 -0.1426 0.6388 0.7802 5.500 1.2036 0.01390 0.00824 -0.1413 0.6240 0.7862 6.000 1.2432 0.01400 0.00845 -0.1385 0.6068 0.7928 6.500 1.2784 0.01408 0.00864 -0.1347 0.5881 0.7994 7.000 1.3067 0.01426 0.00888 -0.1296 0.5672 0.8071 7.500 1.3337 0.01466 0.00932 -0.1246 0.5430 0.8149 8.000 1.3548 0.01521 0.00990 -0.1185 0.5160 0.8232 8.500 1.3725 0.01607 0.01078 -0.1123 0.4854 0.8340 9.000 1.3817 0.01721 0.01193 -0.1050 0.4514 0.8453 9.500 1.3887 0.01876 0.01347 -0.0981 0.4152 0.8586 10.000 1.3906 0.02076 0.01542 -0.0909 0.3793 0.8758 10.500 1.3910 0.02293 0.01762 -0.0840 0.3436 0.9041 11.000 1.3932 0.02548 0.02018 -0.0786 0.3083 1.0000 11.500 1.3991 0.02890 0.02346 -0.0750 0.2717 1.0000 12.000 1.4053 0.03248 0.02695 -0.0717 0.2367 1.0000 12.500 1.4109 0.03632 0.03073 -0.0686 0.2052 1.0000 13.000 1.4134 0.04068 0.03500 -0.0659 0.1758 1.0000 13.500 1.4184 0.04511 0.03940 -0.0637 0.1475 1.0000 14.000 1.4199 0.05016 0.04440 -0.0619 0.1218 1.0000 14.500 1.4196 0.05571 0.04992 -0.0606 0.0987 1.0000 15.000 1.4181 0.06176 0.05595 -0.0598 0.0782 1.0000 15.500 1.4148 0.06839 0.06260 -0.0595 0.0614 1.0000 16.000 1.4088 0.07573 0.06998 -0.0599 0.0487 1.0000 16.500 1.4038 0.08334 0.07771 -0.0609 0.0390 1.0000 17.000 1.3942 0.09196 0.08644 -0.0626 0.0323 1.0000 17.500 1.3864 0.10064 0.09531 -0.0649 0.0268 1.0000 18.000 1.3767 0.10984 0.10468 -0.0679 0.0226 1.0000 18.500 1.3669 0.11925 0.11426 -0.0715 0.0192 1.0000 19.000 1.3576 0.12868 0.12388 -0.0756 0.0164 1.0000 19.500 1.3485 0.13807 0.13343 -0.0801 0.0142 1.0000 20.000 1.3412 0.14716 0.14266 -0.0849 0.0125 1.0000 20.500 1.3357 0.15592 0.15164 -0.0897 0.0109 1.0000 21.000 1.3321 0.16391 0.15967 -0.0943 0.0099 1.0000 21.500 1.3279 0.17252 0.16857 -0.0996 0.0089 1.0000 22.000 1.3254 0.18061 0.17679 -0.1050 0.0081 1.0000 22.500 1.3234 0.18834 0.18466 -0.1101 0.0075 1.0000 23.000 1.3150 0.19795 0.19456 -0.1168 0.0069 1.0000 23.500 1.3079 0.20730 0.20412 -0.1236 0.0065 1.0000 24.000 1.3037 0.21586 0.21280 -0.1300 0.0061 1.0000 24.500 1.2969 0.22484 0.22192 -0.1367 0.0057 1.0000 25.000 1.2796 0.23733 0.23470 -0.1457 0.0057 1.0000 25.500 1.2537 0.25307 0.25072 -0.1563 0.0057 1.0000 27.500 0.9443 0.39699 0.39560 -0.1886 0.0099 1.0000 28.000 0.9481 0.40896 0.40759 -0.1921 0.0098 1.0000 28.500 0.9514 0.42238 0.42101 -0.1960 0.0088 1.0000 29.000 0.9559 0.43287 0.43151 -0.1992 0.0082 1.0000 29.500 0.9609 0.44193 0.44060 -0.2020 0.0078 1.0000 30.000 0.9637 0.45475 0.45343 -0.2055 0.0076 1.0000 30.500 0.9669 0.46703 0.46572 -0.2088 0.0071 1.0000 31.000 0.9700 0.47795 0.47667 -0.2119 0.0066 1.0000 31.500 0.9728 0.48852 0.48726 -0.2149 0.0063 1.0000 32.000 0.9754 0.49824 0.49700 -0.2178 0.0059 1.0000 32.500 0.9779 0.50807 0.50684 -0.2203 0.0058 1.0000 33.000 0.9790 0.52063 0.51943 -0.2236 0.0057 1.0000 33.500 0.9805 0.53214 0.53095 -0.2266 0.0055 1.0000 34.000 0.9817 0.54342 0.54226 -0.2294 0.0052 1.0000 34.500 0.9826 0.55391 0.55277 -0.2321 0.0049 1.0000 35.000 0.9830 0.56413 0.56302 -0.2349 0.0047 1.0000 35.500 0.9831 0.57413 0.57304 -0.2375 0.0045 1.0000 36.000 0.9827 0.58371 0.58265 -0.2401 0.0043 1.0000 36.500 0.9819 0.59272 0.59169 -0.2426 0.0042 1.0000 38.000 0.9778 0.62239 0.62142 -0.2501 0.0041 1.0000 38.500 0.9760 0.63204 0.63109 -0.2525 0.0041 1.0000 39.000 0.9740 0.64177 0.64084 -0.2549 0.0040 1.0000 39.500 0.9716 0.65094 0.65005 -0.2572 0.0039 1.0000 40.000 0.9689 0.65985 0.65897 -0.2594 0.0036 1.0000 40.500 0.9657 0.66835 0.66750 -0.2616 0.0034 1.0000 41.000 0.9622 0.67621 0.67539 -0.2638 0.0033 1.0000 41.500 0.9584 0.68418 0.68338 -0.2659 0.0031 1.0000 42.000 0.9542 0.69156 0.69078 -0.2679 0.0030 1.0000 42.500 0.9495 0.69827 0.69752 -0.2700 0.0028 1.0000 44.500 0.9285 0.72536 0.72469 -0.2775 0.0027 1.0000 45.000 0.9230 0.73190 0.73125 -0.2792 0.0026 1.0000 45.500 0.9170 0.73744 0.73681 -0.2809 0.0026 1.0000 46.000 0.9108 0.74258 0.74197 -0.2826 0.0026 1.0000 46.500 0.9042 0.74720 0.74662 -0.2842 0.0026 1.0000 47.000 0.8975 0.75186 0.75130 -0.2857 0.0025 1.0000 47.500 0.8904 0.75574 0.75520 -0.2872 0.0024 1.0000 48.000 0.8830 0.75927 0.75875 -0.2887 0.0022 1.0000 48.500 0.8754 0.76245 0.76195 -0.2901 0.0021 1.0000 49.000 0.8675 0.76486 0.76438 -0.2914 0.0020 1.0000 49.500 0.8595 0.76731 0.76685 -0.2928 0.0019 1.0000 50.000 0.8511 0.76900 0.76856 -0.2940 0.0018 1.0000 50.500 0.8425 0.77014 0.76972 -0.2952 0.0017 1.0000 51.000 0.8336 0.77084 0.77043 -0.2964 0.0017 1.0000 51.500 0.8244 0.77097 0.77059 -0.2976 0.0016 1.0000 52.000 0.8147 0.77061 0.77025 -0.2987 0.0016 1.0000