XFOIL Version 6.96 Calculated polar for: EPPLER 331 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.4633 0.09003 0.08682 -0.0098 1.0000 0.0334 -8.500 -0.4687 0.08544 0.08227 -0.0138 1.0000 0.0335 -8.250 -0.4829 0.08092 0.07773 -0.0174 1.0000 0.0339 -8.000 -0.4953 0.07762 0.07439 -0.0173 1.0000 0.0341 -7.750 -0.5068 0.07434 0.07097 -0.0171 1.0000 0.0343 -7.500 -0.5180 0.07141 0.06778 -0.0154 1.0000 0.0345 -7.250 -0.5080 0.06608 0.06265 -0.0154 1.0000 0.0352 -7.000 -0.5011 0.06307 0.05969 -0.0143 1.0000 0.0359 -6.750 -0.4954 0.06024 0.05684 -0.0131 1.0000 0.0369 -6.500 -0.4897 0.05736 0.05389 -0.0118 1.0000 0.0383 -6.250 -0.4832 0.05447 0.05081 -0.0100 1.0000 0.0408 -6.000 -0.4849 0.05168 0.04754 -0.0061 1.0000 0.0428 -5.750 -0.4763 0.04808 0.04412 -0.0050 1.0000 0.0439 -5.500 -0.4410 0.04453 0.04047 -0.0088 0.9574 0.0468 -5.250 -0.4080 0.04057 0.03590 -0.0107 0.9100 0.0532 -5.000 -0.3832 0.03787 0.03308 -0.0111 0.8668 0.0561 -4.750 -0.3692 0.03673 0.03123 -0.0076 0.8324 0.0639 -4.500 -0.3522 0.03391 0.02842 -0.0066 0.8043 0.0673 -4.250 -0.3367 0.03238 0.02653 -0.0043 0.7804 0.0786 -4.000 -0.3197 0.03128 0.02506 -0.0021 0.7592 0.0913 -3.750 -0.2992 0.02910 0.02283 -0.0009 0.7404 0.0968 -3.500 -0.2608 0.02256 0.01483 0.0038 0.7274 0.0361 -3.250 -0.2322 0.02059 0.01251 0.0048 0.7107 0.0317 -3.000 -0.2022 0.01882 0.01028 0.0058 0.6949 0.0289 -2.750 -0.1738 0.01772 0.00898 0.0064 0.6793 0.0285 -2.500 -0.1470 0.01655 0.00776 0.0070 0.6645 0.0290 -2.250 -0.1227 0.01573 0.00689 0.0080 0.6503 0.0303 -2.000 -0.0994 0.01510 0.00618 0.0093 0.6370 0.0335 -1.750 -0.0770 0.01455 0.00558 0.0106 0.6248 0.0420 -1.500 0.0999 0.01410 0.00802 -0.0131 0.6004 0.9678 -1.250 0.2118 0.01325 0.00671 -0.0297 0.5808 1.0000 -1.000 0.2342 0.01317 0.00648 -0.0289 0.5692 1.0000 -0.750 0.2568 0.01312 0.00630 -0.0282 0.5584 1.0000 -0.500 0.2794 0.01311 0.00612 -0.0275 0.5491 1.0000 -0.250 0.3023 0.01307 0.00599 -0.0268 0.5387 1.0000 0.000 0.3254 0.01307 0.00587 -0.0261 0.5297 1.0000 0.250 0.3486 0.01309 0.00577 -0.0254 0.5211 1.0000 0.500 0.3720 0.01310 0.00571 -0.0247 0.5123 1.0000 0.750 0.3953 0.01315 0.00563 -0.0240 0.5045 1.0000 1.000 0.4189 0.01318 0.00563 -0.0234 0.4961 1.0000 1.250 0.4424 0.01325 0.00559 -0.0228 0.4892 1.0000 1.500 0.4661 0.01330 0.00563 -0.0222 0.4812 1.0000 1.750 0.4898 0.01338 0.00562 -0.0215 0.4742 1.0000 2.000 0.5136 0.01347 0.00570 -0.0209 0.4671 1.0000 2.250 0.5374 0.01355 0.00573 -0.0203 0.4601 1.0000 2.500 0.5612 0.01368 0.00582 -0.0197 0.4537 1.0000 2.750 0.5851 0.01377 0.00592 -0.0191 0.4468 1.0000 3.000 0.6090 0.01394 0.00599 -0.0185 0.4412 1.0000 3.250 0.6328 0.01403 0.00615 -0.0179 0.4339 1.0000 3.500 0.6566 0.01416 0.00623 -0.0173 0.4280 1.0000 3.750 0.6804 0.01433 0.00645 -0.0167 0.4218 1.0000 4.000 0.7041 0.01446 0.00659 -0.0160 0.4153 1.0000 4.250 0.7280 0.01465 0.00673 -0.0154 0.4098 1.0000 4.500 0.7515 0.01479 0.00698 -0.0148 0.4028 1.0000 4.750 0.7753 0.01495 0.00710 -0.0142 0.3970 1.0000 5.000 0.7987 0.01514 0.00737 -0.0135 0.3905 1.0000 5.250 0.8221 0.01528 0.00754 -0.0128 0.3840 1.0000 5.500 0.8455 0.01550 0.00778 -0.0122 0.3781 1.0000 5.750 0.8685 0.01566 0.00804 -0.0114 0.3710 1.0000 6.000 0.8920 0.01587 0.00820 -0.0108 0.3652 1.0000 6.250 0.9144 0.01604 0.00854 -0.0100 0.3576 1.0000 6.500 0.9375 0.01621 0.00870 -0.0092 0.3513 1.0000 6.750 0.9596 0.01642 0.00904 -0.0084 0.3437 1.0000 7.000 0.9821 0.01658 0.00923 -0.0075 0.3367 1.0000 7.250 1.0037 0.01680 0.00956 -0.0066 0.3288 1.0000 7.500 1.0256 0.01695 0.00973 -0.0057 0.3211 1.0000 7.750 1.0465 0.01716 0.01009 -0.0046 0.3125 1.0000 8.000 1.0679 0.01735 0.01026 -0.0036 0.3047 1.0000 8.250 1.0877 0.01754 0.01064 -0.0024 0.2951 1.0000 8.500 1.1076 0.01776 0.01093 -0.0012 0.2859 1.0000 8.750 1.1270 0.01796 0.01119 0.0001 0.2762 1.0000 9.000 1.1454 0.01819 0.01158 0.0015 0.2650 1.0000 9.250 1.1631 0.01847 0.01196 0.0030 0.2534 1.0000 9.500 1.1797 0.01878 0.01236 0.0047 0.2411 1.0000 9.750 1.1951 0.01916 0.01281 0.0065 0.2277 1.0000 10.000 1.2089 0.01960 0.01332 0.0085 0.2132 1.0000 10.250 1.2209 0.02015 0.01393 0.0107 0.1980 1.0000 10.500 1.2301 0.02080 0.01462 0.0133 0.1820 1.0000 10.750 1.2362 0.02157 0.01541 0.0163 0.1665 1.0000 11.000 1.2385 0.02246 0.01629 0.0198 0.1519 1.0000 11.250 1.2371 0.02341 0.01725 0.0238 0.1391 1.0000 11.500 1.2315 0.02443 0.01828 0.0283 0.1280 1.0000 11.750 1.2155 0.02547 0.01928 0.0344 0.1216 1.0000 12.000 1.2053 0.02666 0.02053 0.0388 0.1132 1.0000 12.250 1.1942 0.02841 0.02230 0.0419 0.1061 1.0000 12.500 1.1850 0.03057 0.02448 0.0438 0.0990 1.0000 12.750 1.1772 0.03306 0.02703 0.0449 0.0920 1.0000 13.000 1.1678 0.03598 0.02994 0.0454 0.0862 1.0000 13.250 1.1613 0.03887 0.03292 0.0456 0.0802 1.0000 13.500 1.1521 0.04217 0.03623 0.0454 0.0751 1.0000 13.750 1.1443 0.04542 0.03955 0.0453 0.0702 1.0000 14.000 1.1369 0.04881 0.04301 0.0447 0.0656 1.0000 14.250 1.1279 0.05219 0.04633 0.0445 0.0621 1.0000 14.500 1.1222 0.05562 0.04992 0.0437 0.0581 1.0000 14.750 1.1142 0.05924 0.05357 0.0429 0.0547 1.0000 15.000 1.1078 0.06263 0.05696 0.0424 0.0514 1.0000 15.250 1.1023 0.06630 0.06077 0.0413 0.0481 1.0000 15.500 1.0963 0.07007 0.06455 0.0401 0.0454 1.0000 15.750 1.0918 0.07351 0.06802 0.0394 0.0424 1.0000 16.000 1.0871 0.07739 0.07203 0.0380 0.0400 1.0000 16.250 1.0834 0.08105 0.07572 0.0368 0.0379 1.0000 16.500 1.0827 0.08393 0.07858 0.0365 0.0354 1.0000 16.750 1.0755 0.08855 0.08339 0.0344 0.0336 1.0000 17.000 1.0711 0.09264 0.08756 0.0328 0.0318 1.0000 17.250 1.0717 0.09554 0.09041 0.0321 0.0298 1.0000 17.500 1.0664 0.09983 0.09484 0.0305 0.0285 1.0000 17.750 1.0581 0.10494 0.10013 0.0281 0.0272 1.0000 18.000 1.0530 0.10946 0.10478 0.0261 0.0263 1.0000 18.250 1.0519 0.11312 0.10842 0.0245 0.0247 1.0000 18.500 1.0502 0.11664 0.11199 0.0235 0.0236 1.0000 18.750 1.0384 0.12280 0.11835 0.0202 0.0232 1.0000 19.000 1.0238 0.12977 0.12552 0.0163 0.0226 1.0000 19.250 1.0106 0.13652 0.13245 0.0127 0.0225 1.0000