XFOIL Version 6.94 Calculated polar for: EPPLER 1233 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 0.4747 0.01377 0.00705 -0.0866 0.4962 0.7571 0.500 0.5226 0.01409 0.00723 -0.0847 0.4832 0.7670 1.000 0.5739 0.01420 0.00725 -0.0841 0.4710 0.7768 1.500 0.6242 0.01446 0.00735 -0.0830 0.4599 0.7833 2.000 0.6716 0.01455 0.00746 -0.0815 0.4499 0.7909 2.500 0.7280 0.01493 0.00761 -0.0822 0.4392 0.7988 3.000 0.7707 0.01495 0.00772 -0.0797 0.4302 0.8051 3.500 0.8192 0.01521 0.00790 -0.0785 0.4215 0.8125 4.000 0.8720 0.01559 0.00824 -0.0785 0.4133 0.8200 4.500 0.9127 0.01569 0.00838 -0.0758 0.4051 0.8264 5.000 0.9675 0.01625 0.00880 -0.0761 0.3965 0.8337 5.500 1.0081 0.01647 0.00913 -0.0737 0.3902 0.8417 6.000 1.0490 0.01673 0.00944 -0.0713 0.3833 0.8486 6.500 1.1030 0.01736 0.00996 -0.0716 0.3754 0.8563 7.000 1.1380 0.01770 0.01047 -0.0683 0.3697 0.8653 7.500 1.1754 0.01807 0.01093 -0.0654 0.3635 0.8741 8.000 1.2227 0.01865 0.01148 -0.0647 0.3573 0.8840 8.500 1.2586 0.01920 0.01218 -0.0617 0.3514 0.8954 9.000 1.2898 0.01969 0.01283 -0.0581 0.3457 0.9094 9.500 1.3235 0.02014 0.01339 -0.0549 0.3403 0.9304 10.000 1.3820 0.02097 0.01425 -0.0568 0.3337 0.9824 10.500 1.4148 0.02186 0.01535 -0.0547 0.3285 1.0000 11.000 1.4521 0.02278 0.01637 -0.0532 0.3228 1.0000 11.500 1.4944 0.02370 0.01725 -0.0525 0.3169 1.0000 12.000 1.5247 0.02501 0.01871 -0.0502 0.3114 1.0000 12.500 1.5397 0.02636 0.02024 -0.0457 0.3056 1.0000 13.000 1.5644 0.02754 0.02148 -0.0429 0.2995 1.0000 13.500 1.5940 0.02903 0.02302 -0.0410 0.2930 1.0000 14.000 1.5928 0.03134 0.02559 -0.0360 0.2872 1.0000 14.500 1.6060 0.03332 0.02768 -0.0330 0.2808 1.0000 15.000 1.6307 0.03521 0.02960 -0.0314 0.2740 1.0000 15.500 1.6152 0.03923 0.03393 -0.0274 0.2677 1.0000 16.000 1.6211 0.04231 0.03709 -0.0255 0.2602 1.0000 16.500 1.6158 0.04671 0.04165 -0.0238 0.2522 1.0000 17.000 1.6008 0.05235 0.04749 -0.0227 0.2436 1.0000 17.500 1.5935 0.05781 0.05305 -0.0224 0.2342 1.0000 18.000 1.5724 0.06529 0.06071 -0.0231 0.2241 1.0000 18.500 1.5527 0.07316 0.06875 -0.0244 0.2144 1.0000 19.000 1.5435 0.08006 0.07569 -0.0261 0.2035 1.0000 19.500 1.5027 0.09170 0.08761 -0.0296 0.1919 1.0000 20.000 1.4807 0.10106 0.09707 -0.0328 0.1801 1.0000 20.500 1.4669 0.10937 0.10540 -0.0360 0.1675 1.0000 21.000 1.4493 0.11835 0.11439 -0.0398 0.1542 1.0000 21.500 1.4260 0.12835 0.12447 -0.0444 0.1412 1.0000 22.000 1.4092 0.13733 0.13351 -0.0488 0.1290 1.0000 22.500 1.3960 0.14571 0.14193 -0.0531 0.1177 1.0000 23.000 1.3879 0.15323 0.14947 -0.0573 0.1073 1.0000 23.500 1.3817 0.16038 0.15662 -0.0614 0.0981 1.0000 24.000 1.3781 0.16700 0.16321 -0.0655 0.0894 1.0000 24.500 1.3745 0.17360 0.16981 -0.0697 0.0815 1.0000 25.000 1.3673 0.18087 0.17719 -0.0744 0.0748 1.0000 25.500 1.3661 0.18698 0.18335 -0.0786 0.0686 1.0000 26.000 1.3664 0.19273 0.18909 -0.0828 0.0631 1.0000 26.500 1.3616 0.19941 0.19581 -0.0876 0.0576 1.0000 27.000 1.3550 0.20638 0.20292 -0.0927 0.0528 1.0000 27.500 1.3499 0.21301 0.20960 -0.0977 0.0481 1.0000 28.000 1.3461 0.21933 0.21595 -0.1027 0.0437 1.0000 28.500 1.3382 0.22639 0.22308 -0.1081 0.0394 1.0000 29.000 1.3279 0.23392 0.23074 -0.1139 0.0351 1.0000 30.000 1.3000 0.25057 0.24753 -0.1266 0.0251 1.0000 30.500 1.2845 0.25932 0.25631 -0.1332 0.0200 1.0000 32.000 1.2643 0.28008 0.27713 -0.1500 0.0118 1.0000 32.500 1.2625 0.28582 0.28290 -0.1550 0.0104 1.0000 33.000 1.2663 0.28999 0.28704 -0.1593 0.0093 1.0000 33.500 1.2644 0.29562 0.29274 -0.1643 0.0082 1.0000 34.000 1.2687 0.29940 0.29652 -0.1685 0.0074 1.0000 34.500 1.2612 0.30650 0.30379 -0.1742 0.0070 1.0000 35.000 1.2654 0.31010 0.30738 -0.1784 0.0064 1.0000 37.000 0.9179 0.52597 0.52474 -0.2163 0.0073 1.0000 37.500 0.9177 0.53513 0.53392 -0.2190 0.0067 1.0000 38.000 0.9173 0.54263 0.54145 -0.2216 0.0063 1.0000 38.500 0.9170 0.54920 0.54804 -0.2239 0.0062 1.0000 39.000 0.9147 0.56215 0.56101 -0.2267 0.0059 1.0000 39.500 0.9133 0.57124 0.57012 -0.2292 0.0054 1.0000 40.000 0.9114 0.57886 0.57777 -0.2316 0.0051 1.0000 40.500 0.9093 0.58533 0.58426 -0.2340 0.0049 1.0000 41.000 0.9069 0.59205 0.59100 -0.2363 0.0048 1.0000 41.500 0.9039 0.60352 0.60249 -0.2386 0.0045 1.0000 42.000 0.9009 0.61120 0.61020 -0.2409 0.0042 1.0000 42.500 0.8976 0.61792 0.61694 -0.2431 0.0039 1.0000 43.000 0.8939 0.62345 0.62251 -0.2453 0.0037 1.0000 43.500 0.8898 0.62930 0.62837 -0.2473 0.0036 1.0000 44.000 0.8855 0.63768 0.63677 -0.2494 0.0035 1.0000 44.500 0.8813 0.64546 0.64457 -0.2514 0.0033 1.0000 45.000 0.8766 0.65158 0.65071 -0.2533 0.0031 1.0000 45.500 0.8716 0.65692 0.65608 -0.2552 0.0029 1.0000 46.000 0.8662 0.66149 0.66067 -0.2571 0.0028 1.0000 46.500 0.8605 0.66544 0.66465 -0.2589 0.0026 1.0000 47.000 0.8544 0.66859 0.66782 -0.2607 0.0026 1.0000 48.000 0.8422 0.67874 0.67800 -0.2640 0.0025 1.0000 48.500 0.8359 0.68319 0.68248 -0.2655 0.0024 1.0000 49.000 0.8292 0.68672 0.68604 -0.2671 0.0022 1.0000 49.500 0.8222 0.68932 0.68865 -0.2685 0.0021 1.0000 50.000 0.8150 0.69159 0.69094 -0.2700 0.0019 1.0000 50.500 0.8074 0.69321 0.69259 -0.2714 0.0018 1.0000 51.000 0.7996 0.69409 0.69349 -0.2728 0.0017 1.0000 51.500 0.7914 0.69411 0.69353 -0.2742 0.0016 1.0000 53.000 0.7668 0.69723 0.69670 -0.2776 0.0015 1.0000 53.500 0.7584 0.69749 0.69697 -0.2787 0.0015 1.0000 54.000 0.7497 0.69701 0.69651 -0.2797 0.0014 1.0000 54.500 0.7408 0.69599 0.69551 -0.2806 0.0013 1.0000 55.000 0.7317 0.69440 0.69394 -0.2816 0.0012 1.0000 55.500 0.7224 0.69241 0.69197 -0.2824 0.0011 1.0000 56.000 0.7129 0.68972 0.68929 -0.2832 0.0010 1.0000 56.500 0.7032 0.68660 0.68619 -0.2840 0.0010 1.0000 57.000 0.6933 0.68280 0.68240 -0.2848 0.0009 1.0000 57.500 0.6832 0.67839 0.67801 -0.2856 0.0009 1.0000 59.000 0.6532 0.66749 0.66715 -0.2871 0.0008 1.0000 59.500 0.6431 0.66287 0.66255 -0.2874 0.0008 1.0000 60.000 0.6328 0.65807 0.65775 -0.2878 0.0008 1.0000