XFOIL Version 6.96 Calculated polar for: ONERA OA209 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 ------ -------- --------- --------- -------- -------- -------- -8.250 -0.5347 0.06327 0.06002 -0.0174 1.0000 0.0200 -8.000 -0.5417 0.05931 0.05604 -0.0182 1.0000 0.0203 -7.750 -0.6128 0.06657 0.06297 -0.0131 1.0000 0.0197 -7.500 -0.6045 0.06297 0.05930 -0.0143 1.0000 0.0193 -7.250 -0.5955 0.05848 0.05465 -0.0159 1.0000 0.0187 -7.000 -0.5848 0.05346 0.04941 -0.0172 1.0000 0.0180 -6.750 -0.5723 0.04805 0.04369 -0.0181 1.0000 0.0175 -6.500 -0.5574 0.04274 0.03800 -0.0183 1.0000 0.0171 -6.250 -0.5400 0.03816 0.03302 -0.0182 1.0000 0.0170 -6.000 -0.5200 0.03502 0.02959 -0.0180 1.0000 0.0174 -5.750 -0.4994 0.03222 0.02647 -0.0175 1.0000 0.0184 -5.500 -0.4796 0.02867 0.02242 -0.0164 1.0000 0.0191 -5.250 -0.4530 0.02547 0.01875 -0.0164 0.9954 0.0193 -5.000 -0.4219 0.02264 0.01541 -0.0170 0.9911 0.0197 -4.750 -0.3899 0.02059 0.01299 -0.0179 0.9874 0.0202 -4.500 -0.3581 0.01939 0.01169 -0.0189 0.9836 0.0209 -4.250 -0.3269 0.01862 0.01084 -0.0198 0.9791 0.0223 -4.000 -0.2949 0.01764 0.00967 -0.0205 0.9749 0.0240 -3.750 -0.2658 0.01664 0.00854 -0.0206 0.9674 0.0249 -3.500 -0.2391 0.01592 0.00784 -0.0203 0.9584 0.0260 -3.250 -0.2146 0.01539 0.00729 -0.0194 0.9485 0.0273 -3.000 -0.1913 0.01497 0.00681 -0.0181 0.9391 0.0294 -2.750 -0.1676 0.01444 0.00630 -0.0171 0.9293 0.0317 -2.500 -0.1439 0.01400 0.00587 -0.0160 0.9200 0.0340 -2.250 -0.1207 0.01362 0.00543 -0.0147 0.9109 0.0368 -2.000 -0.0955 0.01319 0.00503 -0.0141 0.9001 0.0416 -1.750 -0.0708 0.01283 0.00464 -0.0131 0.8889 0.0470 -1.500 -0.0463 0.01249 0.00428 -0.0121 0.8766 0.0566 -1.250 -0.0213 0.01208 0.00395 -0.0112 0.8643 0.0761 -1.000 0.0015 0.00982 0.00353 -0.0116 0.8520 0.5427 -0.750 0.0139 0.00911 0.00382 -0.0069 0.8391 0.8010 -0.500 0.0306 0.00916 0.00393 -0.0032 0.8246 0.8637 -0.250 0.0484 0.00921 0.00393 0.0001 0.8078 0.8993 0.000 0.0647 0.00918 0.00383 0.0037 0.7888 0.9263 0.250 0.0837 0.00907 0.00364 0.0068 0.7663 0.9508 0.500 0.1113 0.00900 0.00340 0.0076 0.7365 0.9638 0.750 0.1409 0.00900 0.00320 0.0075 0.6974 0.9692 1.000 0.1707 0.00910 0.00302 0.0074 0.6443 0.9742 1.250 0.2029 0.00934 0.00290 0.0065 0.5728 0.9781 1.500 0.2348 0.00972 0.00285 0.0055 0.4910 0.9825 1.750 0.2681 0.01011 0.00288 0.0040 0.4285 0.9863 2.000 0.3020 0.01042 0.00295 0.0025 0.3908 0.9899 2.250 0.3352 0.01067 0.00304 0.0011 0.3650 0.9942 2.500 0.3691 0.01091 0.00314 -0.0005 0.3446 0.9979 2.750 0.3977 0.01112 0.00325 -0.0009 0.3284 1.0000 3.000 0.4224 0.01130 0.00335 -0.0006 0.3144 1.0000 3.250 0.4478 0.01148 0.00348 -0.0003 0.3014 1.0000 3.500 0.4740 0.01169 0.00362 -0.0002 0.2892 1.0000 3.750 0.5008 0.01192 0.00380 -0.0003 0.2774 1.0000 4.000 0.5282 0.01214 0.00397 -0.0004 0.2659 1.0000 4.250 0.5559 0.01236 0.00417 -0.0006 0.2547 1.0000 4.500 0.5837 0.01261 0.00440 -0.0009 0.2440 1.0000 4.750 0.6117 0.01288 0.00463 -0.0012 0.2338 1.0000 5.000 0.6398 0.01313 0.00487 -0.0015 0.2231 1.0000 5.250 0.6679 0.01341 0.00516 -0.0018 0.2134 1.0000 5.500 0.6958 0.01372 0.00544 -0.0021 0.2037 1.0000 5.750 0.7239 0.01400 0.00574 -0.0024 0.1937 1.0000 6.000 0.7518 0.01433 0.00607 -0.0026 0.1846 1.0000 6.250 0.7795 0.01468 0.00642 -0.0029 0.1750 1.0000 6.500 0.8072 0.01501 0.00678 -0.0032 0.1652 1.0000 6.750 0.8346 0.01538 0.00715 -0.0035 0.1551 1.0000 7.000 0.8618 0.01578 0.00755 -0.0037 0.1446 1.0000 7.250 0.8890 0.01616 0.00797 -0.0039 0.1342 1.0000 7.500 0.9159 0.01658 0.00842 -0.0041 0.1244 1.0000 7.750 0.9425 0.01705 0.00891 -0.0043 0.1150 1.0000 8.000 0.9687 0.01755 0.00942 -0.0045 0.1050 1.0000 8.250 0.9950 0.01804 0.00996 -0.0046 0.0953 1.0000 8.500 1.0207 0.01860 0.01057 -0.0047 0.0857 1.0000 8.750 1.0458 0.01923 0.01123 -0.0047 0.0764 1.0000 9.000 1.0703 0.01995 0.01196 -0.0048 0.0673 1.0000 9.250 1.0942 0.02073 0.01276 -0.0047 0.0590 1.0000 9.500 1.1178 0.02152 0.01364 -0.0046 0.0527 1.0000 9.750 1.1400 0.02246 0.01463 -0.0044 0.0478 1.0000 10.000 1.1622 0.02336 0.01563 -0.0041 0.0436 1.0000 10.250 1.1822 0.02448 0.01680 -0.0038 0.0403 1.0000 10.500 1.2028 0.02546 0.01793 -0.0033 0.0378 1.0000 10.750 1.2218 0.02656 0.01916 -0.0028 0.0358 1.0000 11.000 1.2381 0.02787 0.02054 -0.0021 0.0340 1.0000 11.250 1.2536 0.02920 0.02200 -0.0013 0.0326 1.0000 11.500 1.2687 0.03047 0.02346 -0.0005 0.0311 1.0000 11.750 1.2817 0.03183 0.02496 0.0004 0.0298 1.0000 12.000 1.2919 0.03333 0.02658 0.0015 0.0288 1.0000 12.250 1.2959 0.03503 0.02839 0.0031 0.0281 1.0000 12.500 1.2964 0.03715 0.03060 0.0046 0.0274 1.0000 12.750 1.2986 0.03931 0.03292 0.0056 0.0269 1.0000 13.000 1.3001 0.04167 0.03550 0.0062 0.0264 1.0000 13.250 1.2998 0.04440 0.03841 0.0063 0.0258 1.0000 13.500 1.2976 0.04753 0.04173 0.0059 0.0253 1.0000 13.750 1.2938 0.05114 0.04552 0.0048 0.0248 1.0000 14.000 1.2882 0.05529 0.04984 0.0030 0.0244 1.0000 14.250 1.2808 0.06003 0.05476 0.0005 0.0240 1.0000 14.500 1.2717 0.06538 0.06027 -0.0026 0.0237 1.0000 14.750 1.2609 0.07128 0.06633 -0.0061 0.0235 1.0000 15.000 1.2485 0.07760 0.07280 -0.0099 0.0233 1.0000 15.250 1.2349 0.08418 0.07952 -0.0137 0.0231 1.0000 15.500 1.2199 0.09095 0.08642 -0.0175 0.0230 1.0000 15.750 1.2045 0.09787 0.09347 -0.0213 0.0229 1.0000 16.000 1.1886 0.10496 0.10068 -0.0252 0.0227 1.0000 16.250 1.1721 0.11236 0.10820 -0.0293 0.0226 1.0000 16.500 1.1556 0.12000 0.11596 -0.0335 0.0225 1.0000 16.750 1.1364 0.12852 0.12461 -0.0384 0.0225 1.0000 17.000 1.1142 0.13824 0.13448 -0.0441 0.0224 1.0000