XFOIL Version 6.96 Calculated polar for: EPPLER 550 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -14.500 -0.6287 0.08307 0.08012 -0.0557 1.0000 0.0096 -14.250 -0.6478 0.07636 0.07330 -0.0592 1.0000 0.0095 -14.000 -0.6693 0.06993 0.06671 -0.0622 1.0000 0.0094 -13.750 -0.6920 0.06394 0.06055 -0.0645 1.0000 0.0094 -13.500 -0.7079 0.05936 0.05582 -0.0657 1.0000 0.0093 -13.250 -0.7243 0.05494 0.05124 -0.0665 1.0000 0.0092 -13.000 -0.7378 0.05104 0.04716 -0.0667 1.0000 0.0090 -12.750 -0.7501 0.04738 0.04332 -0.0665 1.0000 0.0089 -12.500 -0.7594 0.04417 0.03991 -0.0658 1.0000 0.0088 -12.250 -0.7683 0.04092 0.03643 -0.0647 1.0000 0.0087 -12.000 -0.7721 0.03829 0.03359 -0.0634 1.0000 0.0087 -11.750 -0.7719 0.03598 0.03109 -0.0619 1.0000 0.0086 -11.500 -0.7707 0.03401 0.02894 -0.0603 1.0000 0.0090 -11.250 -0.7649 0.03233 0.02713 -0.0586 1.0000 0.0089 -11.000 -0.7571 0.03086 0.02555 -0.0570 1.0000 0.0088 -10.750 -0.7503 0.02954 0.02410 -0.0551 1.0000 0.0091 -10.500 -0.7436 0.02834 0.02279 -0.0531 1.0000 0.0094 -10.250 -0.7097 0.02680 0.02111 -0.0557 0.9937 0.0096 -10.000 -0.6819 0.02531 0.01951 -0.0570 0.9574 0.0098 -9.750 -0.6192 0.02342 0.01757 -0.0655 0.9334 0.0103 -9.500 -0.5313 0.02173 0.01572 -0.0796 0.8969 0.0114 -9.250 -0.4970 0.02084 0.01452 -0.0825 0.8375 0.0119 -9.000 -0.4858 0.02018 0.01365 -0.0808 0.8011 0.0121 -8.750 -0.4807 0.01923 0.01255 -0.0784 0.7743 0.0127 -8.500 -0.4724 0.01847 0.01168 -0.0764 0.7530 0.0135 -8.250 -0.4627 0.01780 0.01091 -0.0744 0.7350 0.0142 -8.000 -0.4522 0.01724 0.01022 -0.0723 0.7194 0.0153 -7.750 -0.4523 0.01649 0.00939 -0.0687 0.7056 0.0164 -7.500 -0.4391 0.01602 0.00882 -0.0668 0.6930 0.0178 -7.250 -0.4262 0.01541 0.00816 -0.0649 0.6811 0.0199 -7.000 -0.4104 0.01488 0.00756 -0.0633 0.6703 0.0233 -6.500 -0.3766 0.01374 0.00643 -0.0606 0.6508 0.0445 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0.6172 -1.500 0.1367 0.01083 0.00441 -0.0572 0.5422 0.6186 -1.250 0.1654 0.01074 0.00431 -0.0575 0.5390 0.6199 -1.000 0.1941 0.01070 0.00426 -0.0578 0.5356 0.6213 -0.750 0.2228 0.01071 0.00423 -0.0580 0.5325 0.6228 -0.500 0.2516 0.01076 0.00422 -0.0583 0.5294 0.6243 -0.250 0.2805 0.01080 0.00423 -0.0587 0.5266 0.6257 0.000 0.3094 0.01079 0.00422 -0.0590 0.5240 0.6272 0.250 0.3382 0.01080 0.00421 -0.0593 0.5212 0.6288 0.500 0.3671 0.01082 0.00420 -0.0597 0.5183 0.6304 0.750 0.3959 0.01086 0.00420 -0.0600 0.5155 0.6321 1.000 0.4250 0.01097 0.00423 -0.0604 0.5129 0.6338 1.250 0.4540 0.01104 0.00428 -0.0608 0.5105 0.6352 1.500 0.4824 0.01100 0.00428 -0.0611 0.5080 0.6367 1.750 0.5109 0.01100 0.00431 -0.0613 0.5053 0.6382 2.000 0.5394 0.01103 0.00436 -0.0616 0.5027 0.6397 2.250 0.5681 0.01109 0.00441 -0.0619 0.5003 0.6413 2.500 0.5968 0.01117 0.00448 -0.0622 0.4977 0.6430 2.750 0.6257 0.01132 0.00461 -0.0626 0.4951 0.6448 3.000 0.6538 0.01135 0.00469 -0.0628 0.4928 0.6469 3.250 0.6821 0.01140 0.00477 -0.0631 0.4900 0.6490 3.500 0.7105 0.01146 0.00483 -0.0633 0.4871 0.6508 3.750 0.7388 0.01150 0.00488 -0.0636 0.4843 0.6525 4.000 0.7670 0.01157 0.00495 -0.0639 0.4814 0.6544 4.250 0.7952 0.01169 0.00510 -0.0641 0.4784 0.6563 4.500 0.8225 0.01171 0.00520 -0.0642 0.4754 0.6582 4.750 0.8501 0.01175 0.00530 -0.0643 0.4720 0.6604 5.000 0.8779 0.01180 0.00538 -0.0644 0.4687 0.6627 5.250 0.9058 0.01190 0.00547 -0.0646 0.4655 0.6650 5.500 0.9336 0.01204 0.00563 -0.0648 0.4620 0.6674 5.750 0.9601 0.01204 0.00573 -0.0647 0.4582 0.6699 6.000 0.9869 0.01206 0.00582 -0.0647 0.4542 0.6724 6.250 1.0138 0.01211 0.00590 -0.0647 0.4502 0.6749 6.500 1.0408 0.01224 0.00606 -0.0647 0.4462 0.6776 6.750 1.0666 0.01226 0.00619 -0.0645 0.4416 0.6804 7.000 1.0929 0.01231 0.00628 -0.0644 0.4369 0.6834 7.250 1.1193 0.01242 0.00639 -0.0644 0.4322 0.6862 7.500 1.1442 0.01243 0.00655 -0.0640 0.4270 0.6891 7.750 1.1692 0.01246 0.00666 -0.0636 0.4209 0.6923 8.000 1.1940 0.01258 0.00680 -0.0633 0.4149 0.6959 8.250 1.2185 0.01262 0.00695 -0.0629 0.4072 0.6999 8.500 1.2419 0.01273 0.00709 -0.0623 0.3996 0.7037 8.750 1.2654 0.01280 0.00727 -0.0617 0.3900 0.7077 9.000 1.2878 0.01294 0.00747 -0.0609 0.3792 0.7121 9.250 1.3088 0.01314 0.00770 -0.0600 0.3661 0.7168 9.500 1.3279 0.01339 0.00797 -0.0587 0.3499 0.7214 9.750 1.3434 0.01377 0.00834 -0.0568 0.3294 0.7264 10.000 1.3540 0.01432 0.00882 -0.0542 0.3063 0.7322 10.250 1.3582 0.01495 0.00939 -0.0505 0.2833 0.7380 10.500 1.3610 0.01572 0.01011 -0.0468 0.2628 0.7448 10.750 1.3634 0.01657 0.01092 -0.0432 0.2430 0.7524 11.000 1.3636 0.01753 0.01187 -0.0396 0.2251 0.7611 11.250 1.3619 0.01865 0.01298 -0.0360 0.2088 0.7713 11.750 1.3549 0.02146 0.01584 -0.0298 0.1794 0.7987 12.000 1.3501 0.02316 0.01761 -0.0271 0.1664 0.8189 12.250 1.3442 0.02500 0.01957 -0.0246 0.1549 0.8526 12.500 1.3410 0.02704 0.02181 -0.0233 0.1429 1.0000 12.750 1.3360 0.02959 0.02433 -0.0221 0.1320 1.0000 13.000 1.3321 0.03217 0.02689 -0.0213 0.1219 1.0000 13.250 1.3289 0.03476 0.02949 -0.0206 0.1127 1.0000 13.500 1.3238 0.03761 0.03232 -0.0200 0.1044 1.0000 13.750 1.3191 0.04048 0.03519 -0.0195 0.0964 1.0000 14.000 1.3157 0.04330 0.03803 -0.0192 0.0890 1.0000 14.250 1.3097 0.04647 0.04119 -0.0190 0.0820 1.0000 14.500 1.3077 0.04934 0.04409 -0.0189 0.0753 1.0000 14.750 1.3041 0.05246 0.04722 -0.0190 0.0696 1.0000 15.000 1.3012 0.05560 0.05037 -0.0192 0.0636 1.0000 15.250 1.2996 0.05866 0.05345 -0.0195 0.0587 1.0000 15.500 1.2964 0.06199 0.05679 -0.0200 0.0538 1.0000 15.750 1.2952 0.06517 0.06001 -0.0205 0.0496 1.0000 16.000 1.2929 0.06853 0.06338 -0.0211 0.0454 1.0000 16.250 1.2916 0.07186 0.06676 -0.0218 0.0421 1.0000 16.500 1.2904 0.07523 0.07015 -0.0226 0.0388 1.0000 16.750 1.2874 0.07891 0.07387 -0.0235 0.0360 1.0000 17.000 1.2876 0.08223 0.07725 -0.0245 0.0332 1.0000 17.250 1.2827 0.08629 0.08133 -0.0257 0.0307 1.0000 17.500 1.2840 0.08958 0.08470 -0.0267 0.0285 1.0000 17.750 1.2819 0.09339 0.08854 -0.0280 0.0266 1.0000 18.000 1.2780 0.09754 0.09275 -0.0295 0.0248 1.0000 18.250 1.2788 0.10102 0.09630 -0.0308 0.0230 1.0000 18.500 1.2745 0.10534 0.10066 -0.0325 0.0216 1.0000 18.750 1.2713 0.10955 0.10495 -0.0342 0.0203 1.0000 19.000 1.2709 0.11337 0.10885 -0.0358 0.0190 1.0000 19.250 1.2666 0.11785 0.11338 -0.0378 0.0178 1.0000