XFOIL Version 6.96 Calculated polar for: EPPLER 547 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 ------ -------- --------- --------- -------- -------- -------- -16.500 -0.2822 0.15269 0.15047 -0.0336 1.0000 0.0167 -16.250 -0.2807 0.14996 0.14774 -0.0352 1.0000 0.0173 -10.000 -0.6686 0.03224 0.02742 -0.0633 0.9579 0.0108 -9.750 -0.6378 0.02846 0.02332 -0.0660 0.9508 0.0103 -9.500 -0.5982 0.02481 0.01921 -0.0686 0.9460 0.0094 -9.250 -0.5530 0.02263 0.01674 -0.0719 0.9399 0.0091 -9.000 -0.5072 0.02119 0.01517 -0.0759 0.9293 0.0093 -8.750 -0.4655 0.02003 0.01387 -0.0793 0.9136 0.0096 -8.500 -0.4356 0.01913 0.01283 -0.0805 0.8936 0.0099 -8.250 -0.4157 0.01846 0.01203 -0.0797 0.8740 0.0100 -8.000 -0.3998 0.01782 0.01126 -0.0782 0.8574 0.0107 -7.750 -0.3843 0.01727 0.01060 -0.0765 0.8426 0.0111 -7.500 -0.3756 0.01643 0.00966 -0.0740 0.8290 0.0116 -7.250 -0.3638 0.01582 0.00897 -0.0718 0.8170 0.0122 -7.000 -0.3512 0.01528 0.00837 -0.0697 0.8051 0.0134 -6.750 -0.3380 0.01481 0.00781 -0.0675 0.7945 0.0143 -6.500 -0.3296 0.01422 0.00716 -0.0646 0.7846 0.0168 -6.250 -0.3214 0.01378 0.00668 -0.0613 0.7744 0.0203 -6.000 -0.3097 0.01334 0.00622 -0.0587 0.7653 0.0289 -5.750 -0.2991 0.01275 0.00574 -0.0560 0.7566 0.0518 -5.500 -0.2862 0.01220 0.00535 -0.0538 0.7482 0.0870 -5.250 -0.2727 0.01164 0.00496 -0.0517 0.7404 0.1360 -5.000 -0.2633 0.01078 0.00450 -0.0491 0.7323 0.2253 -4.750 -0.2595 0.00947 0.00381 -0.0458 0.7247 0.3787 -4.500 -0.2544 0.00823 0.00347 -0.0423 0.7170 0.5901 -4.250 -0.2282 0.00841 0.00362 -0.0419 0.7100 0.6345 -4.000 -0.2009 0.00865 0.00379 -0.0416 0.7031 0.6546 -3.750 -0.1734 0.00889 0.00393 -0.0414 0.6961 0.6670 -3.500 -0.1451 0.00912 0.00412 -0.0413 0.6895 0.6742 -3.250 -0.1178 0.00932 0.00420 -0.0411 0.6823 0.6829 -3.000 -0.0892 0.00966 0.00454 -0.0409 0.6761 0.6903 -2.750 -0.0616 0.00997 0.00481 -0.0406 0.6693 0.6999 -2.500 -0.0330 0.01054 0.00540 -0.0400 0.6632 0.7088 -2.250 -0.0056 0.01076 0.00557 -0.0398 0.6569 0.7158 -2.000 0.0221 0.01077 0.00552 -0.0398 0.6504 0.7175 -1.750 0.0501 0.01078 0.00545 -0.0399 0.6447 0.7189 -1.500 0.0779 0.01073 0.00536 -0.0401 0.6386 0.7203 -1.250 0.1057 0.01071 0.00526 -0.0403 0.6328 0.7218 -1.000 0.1336 0.01067 0.00517 -0.0406 0.6271 0.7232 -0.750 0.1614 0.01062 0.00506 -0.0408 0.6211 0.7247 -0.500 0.1894 0.01061 0.00495 -0.0411 0.6159 0.7263 -0.250 0.2173 0.01056 0.00486 -0.0414 0.6104 0.7276 0.000 0.2453 0.01051 0.00476 -0.0417 0.6049 0.7287 0.250 0.2735 0.01053 0.00468 -0.0421 0.5999 0.7300 0.500 0.3010 0.01045 0.00461 -0.0423 0.5946 0.7310 0.750 0.3288 0.01042 0.00456 -0.0425 0.5894 0.7319 1.000 0.3568 0.01045 0.00452 -0.0427 0.5846 0.7328 1.250 0.3845 0.01043 0.00452 -0.0429 0.5796 0.7338 1.500 0.4123 0.01043 0.00451 -0.0432 0.5746 0.7348 1.750 0.4403 0.01048 0.00450 -0.0434 0.5700 0.7359 2.000 0.4680 0.01050 0.00453 -0.0436 0.5653 0.7372 2.250 0.4957 0.01051 0.00455 -0.0439 0.5603 0.7385 2.500 0.5236 0.01055 0.00455 -0.0441 0.5557 0.7397 2.750 0.5514 0.01059 0.00458 -0.0444 0.5511 0.7408 3.000 0.5789 0.01060 0.00461 -0.0446 0.5460 0.7420 3.250 0.6066 0.01064 0.00462 -0.0449 0.5413 0.7432 3.500 0.6344 0.01072 0.00467 -0.0452 0.5365 0.7443 3.750 0.6616 0.01074 0.00472 -0.0453 0.5310 0.7453 4.000 0.6884 0.01074 0.00472 -0.0454 0.5258 0.7465 4.250 0.7153 0.01080 0.00479 -0.0454 0.5206 0.7477 4.500 0.7416 0.01081 0.00487 -0.0454 0.5148 0.7489 4.750 0.7682 0.01089 0.00494 -0.0454 0.5095 0.7502 5.000 0.7947 0.01095 0.00504 -0.0454 0.5041 0.7514 5.250 0.8209 0.01099 0.00514 -0.0453 0.4982 0.7527 5.500 0.8473 0.01111 0.00522 -0.0453 0.4926 0.7540 5.750 0.8730 0.01115 0.00534 -0.0452 0.4863 0.7555 6.000 0.8985 0.01122 0.00543 -0.0450 0.4798 0.7569 6.250 0.9238 0.01131 0.00555 -0.0448 0.4729 0.7584 6.500 0.9487 0.01139 0.00565 -0.0445 0.4654 0.7598 6.750 0.9733 0.01149 0.00579 -0.0442 0.4581 0.7611 7.000 0.9969 0.01156 0.00590 -0.0437 0.4496 0.7627 7.250 1.0203 0.01165 0.00606 -0.0431 0.4409 0.7643 7.500 1.0424 0.01180 0.00622 -0.0423 0.4318 0.7660 7.750 1.0647 0.01191 0.00640 -0.0415 0.4206 0.7677 8.000 1.0859 0.01207 0.00659 -0.0406 0.4088 0.7695 8.250 1.1055 0.01226 0.00680 -0.0394 0.3950 0.7714 8.500 1.1229 0.01251 0.00704 -0.0378 0.3779 0.7733 8.750 1.1356 0.01281 0.00730 -0.0353 0.3589 0.7753 9.000 1.1458 0.01318 0.00762 -0.0325 0.3375 0.7772 9.250 1.1523 0.01374 0.00810 -0.0291 0.3126 0.7794 9.500 1.1584 0.01439 0.00867 -0.0258 0.2871 0.7816 9.750 1.1629 0.01514 0.00934 -0.0225 0.2636 0.7842 10.000 1.1660 0.01601 0.01013 -0.0192 0.2405 0.7871 10.250 1.1697 0.01692 0.01097 -0.0162 0.2202 0.7901 10.500 1.1728 0.01791 0.01190 -0.0133 0.2006 0.7929 10.750 1.1750 0.01899 0.01295 -0.0105 0.1829 0.7958 11.000 1.1773 0.02017 0.01410 -0.0080 0.1671 0.7989 11.250 1.1792 0.02148 0.01537 -0.0056 0.1512 0.8024 11.500 1.1817 0.02285 0.01671 -0.0036 0.1374 0.8059 11.750 1.1834 0.02432 0.01816 -0.0016 0.1237 0.8094 12.000 1.1845 0.02590 0.01975 0.0003 0.1113 0.8133 12.250 1.1859 0.02756 0.02140 0.0019 0.0996 0.8176 12.500 1.1886 0.02923 0.02308 0.0032 0.0898 0.8222 12.750 1.1899 0.03100 0.02489 0.0046 0.0807 0.8270 13.000 1.1895 0.03299 0.02689 0.0059 0.0722 0.8329 13.250 1.1906 0.03495 0.02888 0.0069 0.0646 0.8393 13.500 1.1920 0.03691 0.03090 0.0078 0.0578 0.8470 13.750 1.1898 0.03925 0.03328 0.0088 0.0513 0.8561 14.000 1.1918 0.04127 0.03538 0.0095 0.0458 0.8685 14.250 1.1894 0.04364 0.03787 0.0104 0.0417 0.8891 14.500 1.2010 0.04614 0.04056 0.0083 0.0365 0.9458 14.750 1.2013 0.04874 0.04320 0.0082 0.0330 1.0000 15.000 1.2042 0.05121 0.04571 0.0080 0.0302 1.0000 15.250 1.2014 0.05433 0.04883 0.0078 0.0272 1.0000 15.500 1.2065 0.05667 0.05124 0.0074 0.0252 1.0000 15.750 1.2070 0.05956 0.05417 0.0070 0.0232 1.0000 16.000 1.2035 0.06298 0.05762 0.0065 0.0214 1.0000 16.250 1.2062 0.06573 0.06047 0.0060 0.0200 1.0000 16.500 1.2080 0.06862 0.06338 0.0053 0.0181 1.0000 16.750 1.2028 0.07249 0.06732 0.0044 0.0171 1.0000 17.000 1.2054 0.07542 0.07034 0.0036 0.0158 1.0000 17.250 1.2037 0.07896 0.07396 0.0025 0.0147 1.0000 17.500 1.2003 0.08282 0.07787 0.0013 0.0138 1.0000 17.750 1.1960 0.08688 0.08202 0.0000 0.0128 1.0000 18.000 1.1949 0.09057 0.08580 -0.0013 0.0118 1.0000 18.250 1.1919 0.09457 0.08988 -0.0028 0.0110 1.0000 18.500 1.1830 0.09956 0.09494 -0.0048 0.0104 1.0000