XFOIL Version 6.96 Calculated polar for: EPPLER EA 6(-1)-012 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -14.500 -0.9907 0.07311 0.06853 -0.0276 1.0000 0.0394 -14.250 -1.0288 0.06467 0.05980 -0.0324 1.0000 0.0395 -14.000 -1.0551 0.05880 0.05368 -0.0348 1.0000 0.0399 -13.750 -1.0759 0.05411 0.04873 -0.0358 1.0000 0.0403 -13.500 -1.0919 0.05035 0.04470 -0.0358 1.0000 0.0408 -13.250 -1.1047 0.04721 0.04130 -0.0352 1.0000 0.0413 -13.000 -1.1141 0.04471 0.03852 -0.0339 1.0000 0.0418 -12.750 -1.1189 0.04252 0.03612 -0.0323 1.0000 0.0423 -12.500 -1.1138 0.04080 0.03434 -0.0310 1.0000 0.0430 -12.250 -1.1066 0.03961 0.03312 -0.0294 1.0000 0.0436 -12.000 -1.0991 0.03857 0.03202 -0.0276 1.0000 0.0442 -11.750 -1.0910 0.03747 0.03080 -0.0259 1.0000 0.0450 -11.500 -1.0806 0.03622 0.02942 -0.0244 1.0000 0.0457 -11.250 -1.0687 0.03493 0.02797 -0.0230 1.0000 0.0466 -11.000 -1.0553 0.03356 0.02642 -0.0218 1.0000 0.0475 -10.750 -1.0403 0.03229 0.02496 -0.0206 1.0000 0.0484 -10.500 -1.0242 0.03111 0.02358 -0.0195 1.0000 0.0494 -10.250 -1.0069 0.03004 0.02229 -0.0184 1.0000 0.0503 -10.000 -0.9881 0.02902 0.02107 -0.0175 1.0000 0.0509 -9.750 -0.9669 0.02760 0.01960 -0.0170 1.0000 0.0517 -9.500 -0.9454 0.02655 0.01853 -0.0165 1.0000 0.0525 -9.250 -0.9238 0.02566 0.01762 -0.0159 1.0000 0.0533 -9.000 -0.9020 0.02485 0.01677 -0.0153 1.0000 0.0542 -8.750 -0.8800 0.02410 0.01595 -0.0147 1.0000 0.0553 -8.500 -0.8578 0.02336 0.01516 -0.0141 1.0000 0.0566 -8.250 -0.8352 0.02262 0.01434 -0.0135 1.0000 0.0576 -8.000 -0.8124 0.02190 0.01356 -0.0129 1.0000 0.0585 -7.750 -0.7896 0.02123 0.01283 -0.0123 1.0000 0.0593 -7.500 -0.7639 0.02050 0.01206 -0.0123 0.9812 0.0601 -7.000 -0.6960 0.01888 0.01043 -0.0159 0.9207 0.0628 -6.750 -0.6670 0.01831 0.00981 -0.0164 0.9033 0.0642 -6.500 -0.6408 0.01785 0.00928 -0.0163 0.8898 0.0660 -6.250 -0.6158 0.01744 0.00878 -0.0160 0.8789 0.0678 -6.000 -0.5914 0.01704 0.00832 -0.0154 0.8698 0.0693 -5.500 -0.5451 0.01607 0.00732 -0.0141 0.8552 0.0728 -5.250 -0.5210 0.01572 0.00692 -0.0135 0.8489 0.0749 -5.000 -0.4966 0.01540 0.00655 -0.0130 0.8430 0.0773 -4.750 -0.4722 0.01507 0.00619 -0.0124 0.8369 0.0801 -4.500 -0.4482 0.01473 0.00584 -0.0117 0.8316 0.0841 -4.250 -0.4232 0.01444 0.00554 -0.0113 0.8263 0.0898 -4.000 -0.3988 0.01408 0.00525 -0.0107 0.8212 0.0999 -3.750 -0.3748 0.01369 0.00496 -0.0101 0.8168 0.1209 -3.500 -0.3518 0.01315 0.00467 -0.0095 0.8122 0.1705 -3.250 -0.3291 0.01257 0.00440 -0.0089 0.8073 0.2345 -3.000 -0.3076 0.01195 0.00416 -0.0081 0.8027 0.3221 -2.750 -0.2846 0.01149 0.00396 -0.0073 0.7985 0.3913 -2.500 -0.2624 0.01100 0.00385 -0.0063 0.7935 0.4639 -2.250 -0.2396 0.01072 0.00395 -0.0052 0.7893 0.5586 -2.000 -0.2141 0.01068 0.00403 -0.0044 0.7855 0.6081 -1.750 -0.1881 0.01068 0.00414 -0.0037 0.7806 0.6423 -1.500 -0.1618 0.01072 0.00425 -0.0030 0.7746 0.6649 -1.250 -0.1354 0.01080 0.00434 -0.0023 0.7696 0.6849 -1.000 -0.1089 0.01090 0.00448 -0.0017 0.7639 0.7046 -0.750 -0.0822 0.01100 0.00460 -0.0011 0.7586 0.7197 -0.500 -0.0551 0.01107 0.00467 -0.0005 0.7542 0.7293 -0.250 -0.0276 0.01109 0.00467 -0.0003 0.7484 0.7375 0.000 0.0000 0.01109 0.00470 0.0000 0.7425 0.7425 0.250 0.0276 0.01109 0.00467 0.0003 0.7376 0.7484 0.500 0.0551 0.01107 0.00467 0.0005 0.7293 0.7543 0.750 0.0822 0.01100 0.00460 0.0011 0.7197 0.7586 1.000 0.1089 0.01090 0.00448 0.0017 0.7048 0.7638 1.250 0.1354 0.01080 0.00434 0.0023 0.6847 0.7696 1.500 0.1618 0.01072 0.00425 0.0030 0.6649 0.7747 1.750 0.1881 0.01068 0.00414 0.0037 0.6425 0.7806 2.000 0.2141 0.01068 0.00403 0.0044 0.6085 0.7855 2.250 0.2396 0.01072 0.00395 0.0052 0.5586 0.7893 2.500 0.2624 0.01100 0.00385 0.0064 0.4637 0.7935 2.750 0.2846 0.01150 0.00396 0.0073 0.3911 0.7985 3.000 0.3076 0.01195 0.00416 0.0081 0.3222 0.8027 3.250 0.3291 0.01257 0.00440 0.0089 0.2346 0.8073 3.500 0.3518 0.01315 0.00467 0.0095 0.1708 0.8122 3.750 0.3748 0.01369 0.00496 0.0101 0.1211 0.8168 4.000 0.3988 0.01408 0.00525 0.0107 0.1000 0.8212 4.250 0.4232 0.01444 0.00554 0.0112 0.0899 0.8263 4.500 0.4483 0.01473 0.00585 0.0117 0.0841 0.8316 4.750 0.4723 0.01507 0.00619 0.0124 0.0802 0.8369 5.000 0.4966 0.01540 0.00655 0.0129 0.0774 0.8430 5.250 0.5210 0.01572 0.00693 0.0135 0.0750 0.8489 5.500 0.5451 0.01607 0.00732 0.0141 0.0728 0.8552 6.000 0.5914 0.01705 0.00832 0.0154 0.0692 0.8698 6.250 0.6159 0.01744 0.00878 0.0159 0.0678 0.8789 6.500 0.6409 0.01785 0.00928 0.0163 0.0660 0.8898 6.750 0.6670 0.01832 0.00982 0.0164 0.0643 0.9034 7.000 0.6961 0.01887 0.01043 0.0159 0.0628 0.9208 7.500 0.7640 0.02050 0.01206 0.0123 0.0601 0.9814 7.750 0.7897 0.02122 0.01282 0.0123 0.0593 1.0000 8.000 0.8125 0.02190 0.01356 0.0129 0.0585 1.0000 8.250 0.8353 0.02262 0.01435 0.0135 0.0576 1.0000 8.500 0.8578 0.02336 0.01516 0.0141 0.0565 1.0000 8.750 0.8801 0.02410 0.01595 0.0147 0.0553 1.0000 9.000 0.9021 0.02484 0.01676 0.0153 0.0542 1.0000 9.250 0.9238 0.02565 0.01760 0.0159 0.0532 1.0000 9.500 0.9455 0.02655 0.01853 0.0165 0.0525 1.0000 9.750 0.9670 0.02760 0.01960 0.0170 0.0517 1.0000 10.000 0.9882 0.02902 0.02106 0.0175 0.0509 1.0000 10.250 1.0070 0.03002 0.02228 0.0184 0.0503 1.0000 10.500 1.0244 0.03111 0.02358 0.0195 0.0495 1.0000 10.750 1.0405 0.03229 0.02496 0.0206 0.0484 1.0000 11.000 1.0554 0.03356 0.02642 0.0218 0.0474 1.0000 11.250 1.0689 0.03492 0.02796 0.0230 0.0466 1.0000 11.500 1.0808 0.03623 0.02943 0.0244 0.0457 1.0000 11.750 1.0912 0.03747 0.03081 0.0258 0.0449 1.0000 12.000 1.0994 0.03859 0.03204 0.0276 0.0442 1.0000 12.250 1.1070 0.03961 0.03311 0.0294 0.0436 1.0000 12.500 1.1145 0.04077 0.03431 0.0309 0.0429 1.0000 12.750 1.1193 0.04252 0.03613 0.0322 0.0423 1.0000 13.000 1.1143 0.04470 0.03852 0.0339 0.0418 1.0000 13.250 1.1051 0.04725 0.04133 0.0351 0.0414 1.0000 13.500 1.0923 0.05036 0.04472 0.0358 0.0408 1.0000 13.750 1.0759 0.05419 0.04881 0.0357 0.0403 1.0000 14.000 1.0553 0.05887 0.05375 0.0346 0.0399 1.0000 14.250 1.0284 0.06483 0.05998 0.0322 0.0396 1.0000 14.500 0.9907 0.07325 0.06867 0.0274 0.0395 1.0000