XFOIL Version 6.96 Calculated polar for: DAE-11 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 ------ -------- --------- --------- -------- -------- -------- -9.750 -0.0664 0.10642 0.10221 -0.0765 0.7797 0.0375 -9.500 -0.0707 0.10465 0.10047 -0.0802 0.7773 0.0379 -9.250 -0.0643 0.10098 0.09681 -0.0814 0.7752 0.0382 -9.000 -0.0444 0.09737 0.09315 -0.0798 0.7734 0.0391 -8.750 -0.0339 0.09493 0.09069 -0.0802 0.7716 0.0400 -8.500 -0.0245 0.09253 0.08833 -0.0814 0.7692 0.0420 -8.250 -0.0178 0.09005 0.08589 -0.0831 0.7667 0.0431 -8.000 -0.0214 0.08808 0.08399 -0.0871 0.7637 0.0451 -7.750 -0.0279 0.08609 0.08205 -0.0912 0.7606 0.0455 -7.500 -0.0262 0.08263 0.07862 -0.0922 0.7584 0.0459 -7.250 -0.0044 0.07935 0.07529 -0.0901 0.7569 0.0468 -7.000 0.0060 0.07721 0.07313 -0.0899 0.7552 0.0479 -6.750 0.0116 0.07526 0.07126 -0.0908 0.7522 0.0490 -6.500 0.0181 0.07301 0.06905 -0.0928 0.7489 0.0505 -6.250 0.0256 0.07023 0.06628 -0.0970 0.7460 0.0527 -6.000 0.0381 0.06387 0.05975 -0.1142 0.7430 0.0550 -5.750 0.0485 0.06172 0.05767 -0.1105 0.7413 0.0559 -5.500 0.0622 0.06001 0.05595 -0.1092 0.7396 0.0572 -5.250 0.0788 0.05787 0.05384 -0.1112 0.7360 0.0593 -5.000 0.1077 0.05179 0.04726 -0.1244 0.7321 0.0662 -4.750 0.1228 0.04929 0.04491 -0.1234 0.7296 0.0675 -4.500 0.1410 0.04796 0.04362 -0.1228 0.7275 0.0702 -4.250 0.1693 0.04392 0.03909 -0.1280 0.7255 0.0799 -4.000 0.1893 0.04209 0.03730 -0.1275 0.7238 0.0822 -3.750 0.2117 0.04072 0.03589 -0.1287 0.7196 0.0872 -3.500 0.2368 0.03829 0.03320 -0.1309 0.7160 0.0960 -3.250 0.2612 0.03686 0.03169 -0.1313 0.7132 0.1018 -3.000 0.3004 0.02858 0.02191 -0.1327 0.7113 0.0511 -2.750 0.3290 0.02665 0.01955 -0.1325 0.7096 0.0498 -2.500 0.3572 0.02555 0.01815 -0.1322 0.7080 0.0512 -2.250 0.3814 0.02506 0.01749 -0.1322 0.7036 0.0514 -2.000 0.4064 0.02459 0.01687 -0.1320 0.6993 0.0525 -1.750 0.4338 0.02403 0.01615 -0.1317 0.6966 0.0544 -1.500 0.4612 0.02319 0.01534 -0.1315 0.6947 0.0596 -1.250 0.4898 0.02267 0.01474 -0.1312 0.6931 0.0649 -1.000 0.5177 0.02205 0.01414 -0.1310 0.6916 0.0743 -0.750 0.5360 0.02265 0.01489 -0.1308 0.6845 0.0874 -0.500 0.5621 0.02219 0.01466 -0.1307 0.6814 0.1444 -0.250 0.5866 0.02100 0.01464 -0.1305 0.6793 0.4899 0.000 0.6186 0.01968 0.01439 -0.1301 0.6778 1.0000 0.250 0.6483 0.01963 0.01411 -0.1301 0.6763 1.0000 0.500 0.6656 0.02079 0.01524 -0.1297 0.6692 1.0000 0.750 0.6917 0.02102 0.01535 -0.1295 0.6657 1.0000 1.000 0.7209 0.02097 0.01516 -0.1295 0.6636 1.0000 1.250 0.7513 0.02081 0.01486 -0.1295 0.6620 1.0000 1.500 0.7815 0.02067 0.01459 -0.1295 0.6606 1.0000 1.750 0.7946 0.02208 0.01604 -0.1287 0.6523 1.0000 2.000 0.8225 0.02210 0.01598 -0.1286 0.6494 1.0000 2.250 0.8529 0.02192 0.01571 -0.1286 0.6476 1.0000 2.500 0.8838 0.02169 0.01540 -0.1287 0.6461 1.0000 2.750 0.9153 0.02144 0.01505 -0.1289 0.6448 1.0000 3.000 0.9250 0.02294 0.01665 -0.1276 0.6355 1.0000 3.250 0.9554 0.02271 0.01636 -0.1276 0.6333 1.0000 3.500 0.9872 0.02237 0.01595 -0.1278 0.6316 1.0000 3.750 1.0196 0.02199 0.01552 -0.1281 0.6302 1.0000 4.000 1.0518 0.02166 0.01513 -0.1284 0.6286 1.0000 4.250 1.0609 0.02300 0.01659 -0.1267 0.6191 1.0000 4.500 1.0928 0.02260 0.01615 -0.1270 0.6171 1.0000 4.750 1.1264 0.02210 0.01562 -0.1274 0.6155 1.0000 5.000 1.1608 0.02158 0.01505 -0.1279 0.6140 1.0000 5.250 1.1693 0.02280 0.01640 -0.1260 0.6047 1.0000 5.500 1.2024 0.02228 0.01587 -0.1264 0.6023 1.0000 5.750 1.2372 0.02166 0.01523 -0.1270 0.6004 1.0000 6.000 1.2546 0.02222 0.01587 -0.1258 0.5938 1.0000 6.250 1.2817 0.02205 0.01574 -0.1256 0.5893 1.0000 6.500 1.3164 0.02141 0.01509 -0.1262 0.5866 1.0000 6.750 1.3530 0.02071 0.01435 -0.1270 0.5844 1.0000 7.000 1.3641 0.02145 0.01524 -0.1251 0.5755 1.0000 7.250 1.3986 0.02079 0.01459 -0.1257 0.5718 1.0000 7.500 1.4230 0.02076 0.01461 -0.1251 0.5659 1.0000 7.750 1.4470 0.02066 0.01457 -0.1245 0.5592 1.0000 8.000 1.4843 0.01992 0.01381 -0.1255 0.5551 1.0000 8.250 1.4966 0.02041 0.01444 -0.1235 0.5456 1.0000 8.500 1.5328 0.01976 0.01375 -0.1243 0.5402 1.0000 8.750 1.5443 0.02022 0.01434 -0.1221 0.5299 1.0000 9.000 1.5666 0.02022 0.01438 -0.1213 0.5212 1.0000 9.250 1.5903 0.02013 0.01430 -0.1206 0.5118 1.0000 9.500 1.6007 0.02059 0.01486 -0.1182 0.5005 1.0000 9.750 1.6139 0.02091 0.01522 -0.1161 0.4893 1.0000 10.000 1.6262 0.02122 0.01553 -0.1138 0.4778 1.0000 10.250 1.6363 0.02167 0.01596 -0.1114 0.4654 1.0000 10.500 1.6370 0.02262 0.01695 -0.1082 0.4521 1.0000 10.750 1.6381 0.02374 0.01809 -0.1054 0.4381 1.0000 11.000 1.6398 0.02497 0.01932 -0.1028 0.4235 1.0000 11.250 1.6411 0.02634 0.02067 -0.1004 0.4083 1.0000 11.500 1.6418 0.02784 0.02216 -0.0981 0.3930 1.0000 11.750 1.6415 0.02950 0.02378 -0.0959 0.3773 1.0000 12.000 1.6407 0.03129 0.02555 -0.0937 0.3616 1.0000 12.250 1.6387 0.03322 0.02745 -0.0916 0.3457 1.0000 12.500 1.6357 0.03534 0.02956 -0.0896 0.3298 1.0000 12.750 1.6321 0.03757 0.03177 -0.0877 0.3139 1.0000 13.000 1.6282 0.03992 0.03411 -0.0860 0.2981 1.0000 13.250 1.6238 0.04245 0.03662 -0.0843 0.2819 1.0000 13.500 1.6198 0.04508 0.03923 -0.0829 0.2661 1.0000 13.750 1.6152 0.04788 0.04201 -0.0816 0.2501 1.0000 14.000 1.6101 0.05084 0.04496 -0.0805 0.2342 1.0000 14.250 1.6049 0.05394 0.04803 -0.0794 0.2188 1.0000 14.500 1.5991 0.05722 0.05128 -0.0786 0.2035 1.0000 14.750 1.5931 0.06061 0.05465 -0.0779 0.1886 1.0000 15.000 1.5865 0.06420 0.05820 -0.0773 0.1741 1.0000 15.250 1.5800 0.06790 0.06188 -0.0769 0.1602 1.0000 15.500 1.5729 0.07176 0.06572 -0.0766 0.1467 1.0000 15.750 1.5658 0.07574 0.06969 -0.0765 0.1339 1.0000 16.000 1.5586 0.07983 0.07377 -0.0765 0.1219 1.0000 16.250 1.5514 0.08402 0.07796 -0.0766 0.1108 1.0000 16.500 1.5436 0.08834 0.08228 -0.0769 0.1009 1.0000 16.750 1.5345 0.09295 0.08684 -0.0774 0.0925 1.0000 17.000 1.5293 0.09712 0.09106 -0.0779 0.0840 1.0000