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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.250 -0.5930 0.08780 0.08461 0.0039 1.0000 0.0406 -8.000 -0.5952 0.08232 0.07912 -0.0022 1.0000 0.0411 -7.750 -0.5933 0.07722 0.07397 -0.0068 1.0000 0.0420 -7.500 -0.5887 0.07210 0.06873 -0.0111 1.0000 0.0433 -7.250 -0.5845 0.06773 0.06377 -0.0167 1.0000 0.0458 -7.000 -0.5780 0.06180 0.05763 -0.0181 1.0000 0.0465 -6.750 -0.5632 0.05704 0.05300 -0.0187 1.0000 0.0474 -6.500 -0.5475 0.05384 0.04979 -0.0191 1.0000 0.0487 -6.250 -0.5307 0.05079 0.04664 -0.0196 1.0000 0.0506 -6.000 -0.5078 0.05051 0.04563 -0.0195 1.0000 0.0565 -5.750 -0.4956 0.04408 0.03911 -0.0201 1.0000 0.0582 -5.500 -0.4785 0.04096 0.03607 -0.0199 1.0000 0.0599 -5.250 -0.4618 0.03876 0.03377 -0.0191 1.0000 0.0629 -5.000 -0.4459 0.03720 0.03163 -0.0173 1.0000 0.0711 -4.750 -0.4342 0.02125 0.01629 -0.0134 1.0000 0.0729 -4.500 -0.4202 0.01960 0.01461 -0.0121 1.0000 0.0772 -4.250 -0.4055 0.01785 0.01248 -0.0106 1.0000 0.0866 -3.500 -0.3231 0.02278 0.01535 -0.0076 1.0000 0.0462 -3.250 -0.3001 0.02087 0.01324 -0.0067 1.0000 0.0464 -3.000 -0.2740 0.01908 0.01131 -0.0064 0.9995 0.0469 -2.750 -0.2298 0.01735 0.00947 -0.0093 0.9955 0.0472 -2.500 -0.1869 0.01603 0.00817 -0.0122 0.9908 0.0496 -2.250 -0.1404 0.01526 0.00741 -0.0158 0.9863 0.0551 -2.000 -0.0966 0.01405 0.00626 -0.0190 0.9808 0.0600 -1.750 -0.0477 0.01324 0.00551 -0.0232 0.9757 0.0717 -1.500 -0.0084 0.01254 0.00489 -0.0255 0.9668 0.0948 -1.250 0.0010 0.00977 0.00510 -0.0212 0.9581 0.8255 -1.000 0.0107 0.01033 0.00570 -0.0149 0.9460 0.9039 -0.750 0.0217 0.01054 0.00589 -0.0092 0.9341 0.9402 -0.500 0.0672 0.01059 0.00584 -0.0105 0.9267 0.9745 -0.250 0.1593 0.01056 0.00569 -0.0222 0.9215 1.0000 0.000 0.1756 0.01040 0.00548 -0.0197 0.9051 1.0000 0.250 0.1926 0.01020 0.00522 -0.0173 0.8887 1.0000 0.500 0.2103 0.00996 0.00493 -0.0149 0.8714 1.0000 0.750 0.2284 0.00970 0.00462 -0.0126 0.8527 1.0000 1.000 0.2466 0.00945 0.00431 -0.0102 0.8320 1.0000 1.250 0.2662 0.00924 0.00402 -0.0081 0.8052 1.0000 1.500 0.2856 0.00908 0.00374 -0.0059 0.7719 1.0000 1.750 0.3059 0.00901 0.00348 -0.0039 0.7237 1.0000 2.000 0.3273 0.00913 0.00325 -0.0022 0.6468 1.0000 2.250 0.3505 0.00958 0.00315 -0.0012 0.5398 1.0000 2.500 0.3750 0.01012 0.00322 -0.0009 0.4622 1.0000 2.750 0.3995 0.01057 0.00337 -0.0006 0.4216 1.0000 3.000 0.4241 0.01095 0.00355 -0.0003 0.3944 1.0000 3.250 0.4492 0.01131 0.00375 -0.0001 0.3735 1.0000 3.500 0.4752 0.01164 0.00398 0.0000 0.3552 1.0000 3.750 0.5018 0.01198 0.00423 0.0000 0.3389 1.0000 4.000 0.5288 0.01233 0.00449 -0.0001 0.3242 1.0000 4.250 0.5562 0.01268 0.00475 -0.0003 0.3101 1.0000 4.500 0.5839 0.01301 0.00504 -0.0005 0.2967 1.0000 4.750 0.6120 0.01331 0.00534 -0.0007 0.2836 1.0000 5.000 0.6400 0.01364 0.00565 -0.0010 0.2709 1.0000 5.250 0.6679 0.01402 0.00599 -0.0013 0.2593 1.0000 5.500 0.6956 0.01442 0.00633 -0.0015 0.2480 1.0000 5.750 0.7237 0.01472 0.00667 -0.0018 0.2362 1.0000 6.000 0.7516 0.01510 0.00707 -0.0021 0.2250 1.0000 6.250 0.7792 0.01552 0.00749 -0.0023 0.2144 1.0000 6.500 0.8065 0.01594 0.00785 -0.0025 0.2037 1.0000 6.750 0.8342 0.01624 0.00824 -0.0028 0.1921 1.0000 7.000 0.8614 0.01663 0.00868 -0.0030 0.1810 1.0000 7.250 0.8883 0.01707 0.00911 -0.0032 0.1705 1.0000 7.500 0.9148 0.01752 0.00953 -0.0034 0.1598 1.0000 7.750 0.9417 0.01787 0.01001 -0.0036 0.1488 1.0000 8.000 0.9679 0.01835 0.01055 -0.0037 0.1378 1.0000 8.250 0.9936 0.01889 0.01112 -0.0038 0.1266 1.0000 8.500 1.0188 0.01948 0.01174 -0.0038 0.1146 1.0000 8.750 1.0433 0.02017 0.01245 -0.0038 0.1022 1.0000 9.000 1.0670 0.02100 0.01330 -0.0037 0.0900 1.0000 9.250 1.0893 0.02204 0.01431 -0.0034 0.0795 1.0000 9.500 1.1123 0.02292 0.01532 -0.0031 0.0715 1.0000 9.750 1.1331 0.02421 0.01667 -0.0026 0.0654 1.0000 10.000 1.1541 0.02527 0.01776 -0.0022 0.0603 1.0000 10.250 1.1730 0.02688 0.01946 -0.0016 0.0567 1.0000 10.500 1.1928 0.02816 0.02091 -0.0009 0.0536 1.0000 10.750 1.2115 0.02948 0.02226 -0.0003 0.0509 1.0000 11.000 1.2274 0.03165 0.02449 0.0005 0.0485 1.0000 11.250 1.2438 0.03313 0.02624 0.0013 0.0466 1.0000 11.500 1.2586 0.03488 0.02822 0.0023 0.0450 1.0000 11.750 1.2719 0.03668 0.03018 0.0033 0.0436 1.0000 12.000 1.2843 0.03854 0.03214 0.0042 0.0423 1.0000 12.250 1.2937 0.04134 0.03502 0.0052 0.0410 1.0000 12.500 1.2939 0.04433 0.03831 0.0068 0.0403 1.0000 12.750 1.2885 0.04664 0.04092 0.0089 0.0397 1.0000 13.000 1.2806 0.04953 0.04408 0.0103 0.0392 1.0000 13.250 1.2699 0.05299 0.04782 0.0109 0.0388 1.0000 13.500 1.2560 0.05717 0.05227 0.0106 0.0385 1.0000 13.750 1.2386 0.06222 0.05757 0.0090 0.0384 1.0000 14.000 1.2173 0.06843 0.06404 0.0058 0.0384 1.0000 14.250 1.1915 0.07618 0.07205 0.0008 0.0385 1.0000 14.500 1.1600 0.08598 0.08208 -0.0063 0.0389 1.0000 14.750 1.1210 0.09828 0.09459 -0.0152 0.0394 1.0000 15.000 1.0741 0.11283 0.10929 -0.0248 0.0402 1.0000