XFOIL Version 6.94 Calculated polar for: EPPLER 1200 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 0.5041 0.01102 0.00587 -0.1097 0.7174 0.7189 0.500 0.5635 0.01093 0.00570 -0.1102 0.7089 0.7258 1.000 0.6170 0.01081 0.00561 -0.1097 0.7000 0.7320 1.500 0.6758 0.01070 0.00543 -0.1103 0.6919 0.7381 2.000 0.7328 0.01065 0.00536 -0.1108 0.6840 0.7431 2.500 0.7864 0.01053 0.00530 -0.1104 0.6743 0.7482 3.000 0.8434 0.01048 0.00522 -0.1106 0.6647 0.7540 3.500 0.8949 0.01039 0.00520 -0.1099 0.6523 0.7596 4.000 0.9475 0.01032 0.00514 -0.1094 0.6383 0.7648 4.500 0.9961 0.01026 0.00513 -0.1080 0.6203 0.7708 5.000 1.0410 0.01031 0.00520 -0.1059 0.5952 0.7769 5.500 1.0791 0.01054 0.00533 -0.1025 0.5581 0.7833 6.000 1.0969 0.01105 0.00563 -0.0953 0.5046 0.7904 6.500 1.0999 0.01204 0.00638 -0.0857 0.4486 0.7991 7.500 1.1101 0.01475 0.00875 -0.0695 0.3580 0.8176 8.500 1.1359 0.01789 0.01173 -0.0582 0.2951 0.8426 9.000 1.1543 0.01946 0.01329 -0.0539 0.2720 0.8583 9.500 1.1730 0.02102 0.01491 -0.0497 0.2526 0.8816 11.500 1.2777 0.02799 0.02198 -0.0409 0.1922 1.0000 12.000 1.3012 0.03015 0.02411 -0.0388 0.1788 1.0000 12.500 1.3227 0.03254 0.02648 -0.0368 0.1657 1.0000 13.000 1.3478 0.03475 0.02875 -0.0353 0.1539 1.0000 13.500 1.3702 0.03725 0.03127 -0.0338 0.1415 1.0000 14.000 1.3902 0.04005 0.03411 -0.0323 0.1311 1.0000 14.500 1.4080 0.04315 0.03725 -0.0309 0.1215 1.0000 15.000 1.4248 0.04646 0.04060 -0.0298 0.1123 1.0000 15.500 1.4417 0.04990 0.04414 -0.0289 0.1039 1.0000 16.000 1.4552 0.05383 0.04814 -0.0282 0.0952 1.0000 16.500 1.4660 0.05819 0.05258 -0.0278 0.0874 1.0000 17.000 1.4735 0.06313 0.05760 -0.0278 0.0804 1.0000 17.500 1.4795 0.06847 0.06305 -0.0281 0.0740 1.0000 18.000 1.4843 0.07417 0.06890 -0.0289 0.0678 1.0000 18.500 1.4846 0.08072 0.07559 -0.0302 0.0621 1.0000 19.000 1.4810 0.08806 0.08307 -0.0322 0.0568 1.0000 19.500 1.4723 0.09644 0.09160 -0.0350 0.0522 1.0000 20.000 1.4643 0.10497 0.10032 -0.0383 0.0477 1.0000 20.500 1.4534 0.11413 0.10967 -0.0423 0.0440 1.0000 21.000 1.4381 0.12416 0.11987 -0.0471 0.0405 1.0000 21.500 1.4230 0.13425 0.13015 -0.0524 0.0376 1.0000 22.000 1.4083 0.14428 0.14036 -0.0581 0.0346 1.0000 22.500 1.3899 0.15503 0.15127 -0.0645 0.0317 1.0000 23.000 1.3755 0.16500 0.16141 -0.0708 0.0292 1.0000 23.500 1.3595 0.17528 0.17184 -0.0776 0.0259 1.0000 24.000 1.3439 0.18553 0.18223 -0.0845 0.0234 1.0000 24.500 1.3260 0.19627 0.19309 -0.0920 0.0201 1.0000 25.000 1.3061 0.20752 0.20444 -0.0999 0.0162 1.0000 25.500 1.2864 0.21888 0.21590 -0.1080 0.0132 1.0000 26.000 1.2643 0.23097 0.22806 -0.1166 0.0100 1.0000 26.500 1.2515 0.24111 0.23829 -0.1239 0.0088 1.0000 27.000 1.2363 0.25204 0.24926 -0.1317 0.0071 1.0000 27.500 1.2337 0.25983 0.25708 -0.1377 0.0065 1.0000 28.000 1.2354 0.26648 0.26380 -0.1430 0.0060 1.0000 28.500 1.2377 0.27290 0.27026 -0.1482 0.0055 1.0000 29.000 1.2434 0.27821 0.27560 -0.1529 0.0053 1.0000 29.500 1.2521 0.28240 0.27977 -0.1572 0.0050 1.0000 30.000 1.2547 0.28844 0.28591 -0.1623 0.0048 1.0000 30.500 1.2566 0.29459 0.29217 -0.1675 0.0048 1.0000 31.000 1.2522 0.30274 0.30046 -0.1736 0.0047 1.0000 33.000 0.9329 0.47082 0.46967 -0.2027 0.0084 1.0000 33.500 0.9341 0.48378 0.48265 -0.2060 0.0076 1.0000 34.000 0.9361 0.49292 0.49180 -0.2090 0.0070 1.0000 36.000 0.9399 0.53258 0.53155 -0.2205 0.0052 1.0000 36.500 0.9402 0.53985 0.53884 -0.2232 0.0051 1.0000 37.000 0.9397 0.55328 0.55228 -0.2259 0.0049 1.0000 37.500 0.9395 0.56404 0.56306 -0.2286 0.0042 1.0000 38.000 0.9387 0.57251 0.57155 -0.2312 0.0039 1.0000 38.500 0.9375 0.57929 0.57836 -0.2338 0.0037 1.0000 39.000 0.9360 0.58773 0.58681 -0.2363 0.0036 1.0000 39.500 0.9347 0.60131 0.60041 -0.2388 0.0034 1.0000 40.000 0.9328 0.61040 0.60952 -0.2412 0.0029 1.0000 40.500 0.9304 0.61838 0.61752 -0.2437 0.0027 1.0000 41.000 0.9275 0.62488 0.62404 -0.2461 0.0025 1.0000 41.500 0.9244 0.63140 0.63058 -0.2484 0.0025 1.0000 42.000 0.9212 0.64173 0.64093 -0.2506 0.0024 1.0000 42.500 0.9183 0.65208 0.65130 -0.2527 0.0023 1.0000 43.000 0.9146 0.65990 0.65914 -0.2549 0.0021 1.0000 43.500 0.9106 0.66708 0.66634 -0.2570 0.0018 1.0000 44.000 0.9061 0.67324 0.67252 -0.2591 0.0017 1.0000 44.500 0.9011 0.67857 0.67787 -0.2612 0.0016 1.0000 45.000 0.8957 0.68304 0.68236 -0.2632 0.0015 1.0000 46.000 0.8857 0.69884 0.69819 -0.2669 0.0014 1.0000 46.500 0.8805 0.70572 0.70509 -0.2686 0.0013 1.0000 47.000 0.8745 0.71092 0.71030 -0.2704 0.0012 1.0000 47.500 0.8683 0.71554 0.71495 -0.2721 0.0011 1.0000 48.000 0.8617 0.71955 0.71897 -0.2738 0.0010 1.0000 48.500 0.8549 0.72316 0.72260 -0.2754 0.0009 1.0000 49.000 0.8477 0.72594 0.72540 -0.2771 0.0009 1.0000 49.500 0.8401 0.72790 0.72738 -0.2787 0.0008 1.0000 51.000 0.8170 0.73613 0.73565 -0.2830 0.0008 1.0000 51.500 0.8092 0.73868 0.73822 -0.2842 0.0008 1.0000 52.000 0.8013 0.74091 0.74047 -0.2854 0.0007 1.0000 52.500 0.7932 0.74254 0.74211 -0.2866 0.0007 1.0000 53.000 0.7847 0.74345 0.74303 -0.2877 0.0006 1.0000 53.500 0.7759 0.74356 0.74316 -0.2888 0.0005 1.0000 54.000 0.7667 0.74265 0.74227 -0.2899 0.0005 1.0000 54.500 0.7575 0.74177 0.74140 -0.2909 0.0005 1.0000 55.000 0.7481 0.74006 0.73971 -0.2919 0.0004 1.0000 55.500 0.7385 0.73792 0.73758 -0.2929 0.0004 1.0000 56.000 0.7286 0.73517 0.73484 -0.2938 0.0003 1.0000 56.500 0.7184 0.73173 0.73142 -0.2948 0.0003 1.0000 57.000 0.7079 0.72766 0.72737 -0.2957 0.0003 1.0000 58.500 0.6787 0.72084 0.72058 -0.2973 0.0002 1.0000 59.000 0.6683 0.71635 0.71610 -0.2978 0.0002 1.0000 59.500 0.6578 0.71150 0.71126 -0.2984 0.0002 1.0000 60.000 0.6471 0.70603 0.70580 -0.2988 0.0002 1.0000