XFOIL Version 6.96 Calculated polar for: EPPLER 1230 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.250 -0.5804 0.13644 0.13434 -0.0322 1.0000 0.0102 -17.000 -0.6934 0.10809 0.10562 -0.0467 1.0000 0.0099 -16.750 -0.7410 0.09519 0.09253 -0.0537 1.0000 0.0098 -16.500 -0.7762 0.08498 0.08216 -0.0593 1.0000 0.0097 -16.250 -0.8054 0.07614 0.07317 -0.0642 1.0000 0.0097 -16.000 -0.8290 0.06856 0.06544 -0.0685 1.0000 0.0096 -15.750 -0.8494 0.06204 0.05877 -0.0720 1.0000 0.0096 -15.500 -0.8665 0.05654 0.05314 -0.0747 1.0000 0.0096 -15.250 -0.8809 0.05188 0.04835 -0.0765 1.0000 0.0096 -15.000 -0.8931 0.04786 0.04422 -0.0776 1.0000 0.0096 -14.750 -0.9032 0.04440 0.04065 -0.0780 1.0000 0.0096 -14.500 -0.9119 0.04134 0.03748 -0.0780 1.0000 0.0097 -14.250 -0.9191 0.03864 0.03468 -0.0775 1.0000 0.0097 -14.000 -0.9246 0.03627 0.03221 -0.0766 1.0000 0.0097 -13.750 -0.9293 0.03410 0.02996 -0.0754 1.0000 0.0097 -13.500 -0.9334 0.03215 0.02791 -0.0740 1.0000 0.0098 -13.250 -0.9377 0.03041 0.02609 -0.0720 1.0000 0.0098 -13.000 -0.9431 0.02893 0.02452 -0.0694 1.0000 0.0099 -12.750 -0.9508 0.02774 0.02326 -0.0656 1.0000 0.0099 -12.500 -0.9634 0.02686 0.02231 -0.0603 1.0000 0.0099 -12.250 -0.9448 0.02579 0.02114 -0.0604 0.9980 0.0100 -12.000 -0.9156 0.02471 0.01997 -0.0622 0.9958 0.0100 -11.750 -0.8891 0.02313 0.01828 -0.0639 0.9937 0.0102 -11.500 -0.8663 0.02144 0.01649 -0.0648 0.9900 0.0105 -11.250 -0.8349 0.02042 0.01542 -0.0667 0.9879 0.0107 -11.000 -0.8002 0.01963 0.01460 -0.0689 0.9866 0.0110 -10.750 -0.7728 0.01892 0.01385 -0.0694 0.9824 0.0113 -10.500 -0.7390 0.01818 0.01307 -0.0711 0.9799 0.0116 -10.250 -0.7028 0.01744 0.01228 -0.0734 0.9782 0.0119 -10.000 -0.6785 0.01679 0.01159 -0.0730 0.9719 0.0121 -9.750 -0.6433 0.01614 0.01090 -0.0749 0.9689 0.0124 -9.500 -0.6229 0.01564 0.01035 -0.0735 0.9583 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0.5549 0.1039 -4.000 -0.0472 0.00947 0.00284 -0.0668 0.5441 0.1177 -3.750 -0.0218 0.00933 0.00272 -0.0663 0.5340 0.1350 -3.500 0.0032 0.00919 0.00261 -0.0657 0.5232 0.1577 -3.250 0.0279 0.00896 0.00250 -0.0651 0.5139 0.1960 -3.000 0.0511 0.00866 0.00237 -0.0643 0.5043 0.2543 -2.750 0.0743 0.00830 0.00224 -0.0635 0.4962 0.3282 -2.500 0.0967 0.00790 0.00211 -0.0625 0.4875 0.4164 -2.250 0.1196 0.00758 0.00204 -0.0616 0.4794 0.5042 -2.000 0.1452 0.00748 0.00205 -0.0610 0.4708 0.5528 -1.750 0.1715 0.00749 0.00207 -0.0606 0.4622 0.5806 -1.500 0.1990 0.00752 0.00209 -0.0604 0.4542 0.5982 -1.250 0.2261 0.00761 0.00213 -0.0601 0.4458 0.6115 -1.000 0.2542 0.00766 0.00216 -0.0600 0.4395 0.6223 -0.750 0.2818 0.00775 0.00221 -0.0598 0.4320 0.6307 -0.500 0.3096 0.00786 0.00227 -0.0597 0.4250 0.6389 -0.250 0.3376 0.00795 0.00232 -0.0596 0.4182 0.6449 0.000 0.3649 0.00809 0.00239 -0.0594 0.4106 0.6510 0.250 0.3931 0.00821 0.00245 -0.0593 0.4050 0.6570 0.500 0.4206 0.00829 0.00252 -0.0592 0.3989 0.6633 0.750 0.4476 0.00845 0.00261 -0.0589 0.3922 0.6703 1.000 0.4753 0.00848 0.00264 -0.0588 0.3874 0.6760 1.250 0.5028 0.00855 0.00269 -0.0587 0.3817 0.6809 1.500 0.5299 0.00867 0.00276 -0.0585 0.3753 0.6850 1.750 0.5576 0.00874 0.00280 -0.0584 0.3704 0.6881 2.000 0.5855 0.00876 0.00282 -0.0584 0.3658 0.6911 2.250 0.6128 0.00884 0.00287 -0.0583 0.3607 0.6936 2.500 0.6396 0.00896 0.00295 -0.0581 0.3550 0.6961 2.750 0.6677 0.00901 0.00301 -0.0581 0.3516 0.6984 3.000 0.6953 0.00910 0.00307 -0.0581 0.3470 0.7006 3.250 0.7222 0.00922 0.00315 -0.0580 0.3420 0.7027 3.500 0.7488 0.00933 0.00323 -0.0578 0.3372 0.7055 3.750 0.7766 0.00937 0.00331 -0.0578 0.3342 0.7080 4.000 0.8038 0.00946 0.00339 -0.0577 0.3305 0.7103 4.250 0.8305 0.00958 0.00349 -0.0576 0.3265 0.7127 4.500 0.8564 0.00975 0.00362 -0.0573 0.3215 0.7153 4.750 0.8837 0.00984 0.00372 -0.0572 0.3186 0.7176 5.000 0.9109 0.00994 0.00382 -0.0572 0.3155 0.7196 5.250 0.9375 0.01003 0.00392 -0.0570 0.3122 0.7222 5.500 0.9634 0.01016 0.00406 -0.0568 0.3087 0.7250 5.750 0.9885 0.01035 0.00422 -0.0564 0.3045 0.7278 6.000 1.0151 0.01045 0.00435 -0.0562 0.3020 0.7306 6.250 1.0419 0.01055 0.00447 -0.0562 0.2994 0.7331 6.500 1.0681 0.01068 0.00461 -0.0560 0.2964 0.7354 6.750 1.0935 0.01082 0.00476 -0.0557 0.2933 0.7383 7.000 1.1180 0.01099 0.00494 -0.0552 0.2899 0.7416 7.250 1.1420 0.01120 0.00515 -0.0547 0.2865 0.7453 7.500 1.1681 0.01129 0.00530 -0.0545 0.2848 0.7491 7.750 1.1937 0.01140 0.00545 -0.0543 0.2825 0.7533 8.000 1.2180 0.01152 0.00562 -0.0538 0.2798 0.7588 8.250 1.2412 0.01167 0.00581 -0.0531 0.2769 0.7655 8.500 1.2631 0.01185 0.00604 -0.0522 0.2739 0.7787 8.750 1.2832 0.01201 0.00635 -0.0510 0.2704 0.8203 9.000 1.3222 0.01195 0.00666 -0.0536 0.2687 1.0000 9.250 1.3452 0.01211 0.00684 -0.0529 0.2665 1.0000 9.500 1.3675 0.01230 0.00705 -0.0521 0.2640 1.0000 9.750 1.3889 0.01253 0.00729 -0.0512 0.2612 1.0000 10.000 1.4087 0.01283 0.00758 -0.0500 0.2576 1.0000 10.250 1.4279 0.01317 0.00791 -0.0488 0.2541 1.0000 10.500 1.4512 0.01334 0.00813 -0.0483 0.2521 1.0000 10.750 1.4734 0.01355 0.00837 -0.0476 0.2496 1.0000 11.000 1.4942 0.01382 0.00866 -0.0467 0.2467 1.0000 11.250 1.5135 0.01415 0.00900 -0.0456 0.2434 1.0000 11.500 1.5296 0.01463 0.00946 -0.0441 0.2390 1.0000 11.750 1.5519 0.01485 0.00974 -0.0435 0.2369 1.0000 12.000 1.5730 0.01513 0.01006 -0.0428 0.2342 1.0000 12.250 1.5920 0.01549 0.01045 -0.0418 0.2309 1.0000 12.500 1.6088 0.01596 0.01092 -0.0406 0.2272 1.0000 12.750 1.6240 0.01652 0.01149 -0.0392 0.2233 1.0000 13.000 1.6444 0.01685 0.01188 -0.0385 0.2206 1.0000 13.250 1.6622 0.01731 0.01238 -0.0375 0.2172 1.0000 13.500 1.6773 0.01792 0.01301 -0.0363 0.2132 1.0000 13.750 1.6893 0.01872 0.01381 -0.0349 0.2088 1.0000 14.000 1.7075 0.01921 0.01437 -0.0341 0.2057 1.0000 14.250 1.7221 0.01993 0.01511 -0.0331 0.2012 1.0000 14.500 1.7320 0.02096 0.01614 -0.0317 0.1961 1.0000 14.750 1.7455 0.02181 0.01704 -0.0308 0.1919 1.0000 15.000 1.7569 0.02283 0.01809 -0.0298 0.1866 1.0000 15.250 1.7620 0.02435 0.01961 -0.0285 0.1806 1.0000 15.500 1.7731 0.02549 0.02080 -0.0277 0.1756 1.0000 15.750 1.7766 0.02726 0.02259 -0.0266 0.1692 1.0000 16.000 1.7811 0.02904 0.02440 -0.0258 0.1634 1.0000 16.250 1.7812 0.03126 0.02663 -0.0249 0.1565 1.0000 16.500 1.7800 0.03368 0.02908 -0.0241 0.1501 1.0000 16.750 1.7731 0.03672 0.03214 -0.0234 0.1427 1.0000 17.000 1.7667 0.03981 0.03528 -0.0229 0.1361 1.0000 17.250 1.7519 0.04385 0.03934 -0.0225 0.1292 1.0000 17.500 1.7409 0.04762 0.04316 -0.0223 0.1231 1.0000 17.750 1.7212 0.05244 0.04802 -0.0223 0.1174 1.0000 18.000 1.7063 0.05683 0.05248 -0.0225 0.1124 1.0000 18.250 1.6857 0.06202 0.05772 -0.0229 0.1077 1.0000 18.500 1.6643 0.06738 0.06315 -0.0235 0.1036 1.0000 18.750 1.6462 0.07246 0.06830 -0.0241 0.0995 1.0000 19.000 1.6224 0.07833 0.07423 -0.0251 0.0957 1.0000 19.250 1.6021 0.08385 0.07982 -0.0261 0.0922 1.0000