XFOIL Version 6.96 Calculated polar for: ONERA OA212 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.250 -0.7608 0.07094 0.06870 -0.0095 0.9136 0.0286 -10.000 -0.9357 0.03793 0.03406 -0.0124 0.9039 0.0270 -9.750 -0.9375 0.03362 0.02920 -0.0097 0.9005 0.0273 -9.500 -0.9244 0.03054 0.02570 -0.0088 0.8962 0.0277 -9.250 -0.9079 0.02835 0.02314 -0.0076 0.8921 0.0282 -9.000 -0.8894 0.02681 0.02128 -0.0064 0.8886 0.0285 -8.750 -0.8719 0.02497 0.01915 -0.0049 0.8857 0.0290 -8.500 -0.8481 0.02361 0.01773 -0.0047 0.8819 0.0295 -8.250 -0.8229 0.02286 0.01693 -0.0045 0.8778 0.0301 -8.000 -0.7985 0.02218 0.01616 -0.0040 0.8742 0.0308 -7.750 -0.7750 0.02144 0.01531 -0.0032 0.8711 0.0316 -7.500 -0.7512 0.02064 0.01435 -0.0023 0.8681 0.0323 -7.250 -0.7232 0.01987 0.01342 -0.0024 0.8638 0.0329 -7.000 -0.6980 0.01866 0.01211 -0.0021 0.8599 0.0338 -6.750 -0.6726 0.01800 0.01144 -0.0017 0.8563 0.0346 -6.500 -0.6475 0.01748 0.01087 -0.0010 0.8532 0.0355 -6.250 -0.6205 0.01696 0.01028 -0.0008 0.8497 0.0366 -6.000 -0.5918 0.01650 0.00973 -0.0009 0.8454 0.0377 -5.750 -0.5655 0.01573 0.00893 -0.0007 0.8413 0.0391 -5.500 -0.5392 0.01531 0.00851 -0.0003 0.8377 0.0405 -5.250 -0.5129 0.01493 0.00807 0.0002 0.8345 0.0421 -5.000 -0.4834 0.01459 0.00766 0.0000 0.8302 0.0435 -4.750 -0.4559 0.01393 0.00706 0.0000 0.8256 0.0456 -4.500 -0.4284 0.01364 0.00674 0.0002 0.8215 0.0480 -4.250 -0.4014 0.01329 0.00633 0.0006 0.8178 0.0504 -4.000 -0.3730 0.01289 0.00598 0.0005 0.8122 0.0534 -3.750 -0.3449 0.01261 0.00565 0.0007 0.8055 0.0565 -3.500 -0.3184 0.01220 0.00524 0.0011 0.7999 0.0604 -3.250 -0.2889 0.01200 0.00503 0.0009 0.7930 0.0647 -3.000 -0.2609 0.01164 0.00470 0.0010 0.7862 0.0701 -2.750 -0.2329 0.01144 0.00445 0.0012 0.7805 0.0754 -2.500 -0.2032 0.01118 0.00425 0.0008 0.7741 0.0825 -2.250 -0.1743 0.01093 0.00401 0.0008 0.7682 0.0898 -2.000 -0.1457 0.01079 0.00384 0.0008 0.7630 0.0971 -1.750 -0.1157 0.01053 0.00366 0.0003 0.7565 0.1068 -1.500 -0.0865 0.01034 0.00348 0.0002 0.7501 0.1169 -1.250 -0.0574 0.01018 0.00332 0.0000 0.7440 0.1287 -1.000 -0.0274 0.00995 0.00318 -0.0004 0.7370 0.1463 -0.750 0.0016 0.00970 0.00302 -0.0006 0.7303 0.1751 -0.500 0.0311 0.00926 0.00291 -0.0011 0.7229 0.2553 -0.250 0.0554 0.00721 0.00269 -0.0014 0.7155 0.7393 0.000 0.0737 0.00716 0.00303 0.0018 0.7085 0.8808 0.250 0.0982 0.00729 0.00316 0.0031 0.6997 0.9067 0.500 0.1215 0.00740 0.00322 0.0048 0.6913 0.9231 0.750 0.1445 0.00745 0.00325 0.0064 0.6815 0.9363 1.000 0.1676 0.00748 0.00322 0.0080 0.6723 0.9477 1.250 0.1904 0.00745 0.00315 0.0097 0.6614 0.9583 1.500 0.2166 0.00740 0.00305 0.0105 0.6493 0.9669 1.750 0.2470 0.00739 0.00299 0.0103 0.6361 0.9749 2.000 0.2872 0.00749 0.00302 0.0081 0.6202 0.9836 2.250 0.3509 0.00778 0.00321 0.0007 0.5965 0.9882 2.500 0.4129 0.00810 0.00339 -0.0063 0.5675 0.9958 2.750 0.4577 0.00831 0.00344 -0.0100 0.5333 0.9990 3.000 0.4917 0.00851 0.00347 -0.0116 0.4960 0.9998 3.250 0.5229 0.00873 0.00352 -0.0126 0.4617 1.0000 3.750 0.5819 0.00916 0.00367 -0.0140 0.4134 1.0000 4.000 0.6105 0.00934 0.00377 -0.0145 0.3972 1.0000 4.250 0.6386 0.00952 0.00387 -0.0148 0.3836 1.0000 4.500 0.6660 0.00966 0.00398 -0.0149 0.3725 1.0000 4.750 0.6932 0.00985 0.00411 -0.0151 0.3623 1.0000 5.000 0.7199 0.00999 0.00424 -0.0151 0.3529 1.0000 5.250 0.7463 0.01018 0.00439 -0.0151 0.3442 1.0000 5.500 0.7724 0.01032 0.00453 -0.0150 0.3357 1.0000 5.750 0.7983 0.01053 0.00470 -0.0149 0.3272 1.0000 6.000 0.8238 0.01067 0.00485 -0.0146 0.3177 1.0000 6.250 0.8490 0.01086 0.00500 -0.0144 0.3057 1.0000 6.500 0.8739 0.01108 0.00516 -0.0142 0.2937 1.0000 6.750 0.8986 0.01123 0.00532 -0.0138 0.2843 1.0000 7.000 0.9229 0.01145 0.00552 -0.0134 0.2752 1.0000 7.250 0.9469 0.01164 0.00571 -0.0130 0.2652 1.0000 7.500 0.9708 0.01185 0.00592 -0.0125 0.2552 1.0000 7.750 0.9942 0.01212 0.00616 -0.0120 0.2440 1.0000 8.000 1.0178 0.01238 0.00640 -0.0115 0.2311 1.0000 8.250 1.0421 0.01269 0.00667 -0.0113 0.2162 1.0000 8.500 1.0667 0.01310 0.00701 -0.0112 0.1986 1.0000 8.750 1.0915 0.01356 0.00739 -0.0113 0.1767 1.0000 9.000 1.1149 0.01424 0.00791 -0.0113 0.1485 1.0000 9.250 1.1363 0.01517 0.00862 -0.0112 0.1147 1.0000 9.500 1.1562 0.01624 0.00948 -0.0110 0.0827 1.0000 10.000 1.1953 0.01823 0.01126 -0.0104 0.0512 1.0000 10.250 1.2146 0.01915 0.01217 -0.0100 0.0452 1.0000 10.500 1.2326 0.02012 0.01313 -0.0096 0.0411 1.0000 10.750 1.2499 0.02099 0.01406 -0.0091 0.0383 1.0000 11.000 1.2627 0.02200 0.01510 -0.0079 0.0362 1.0000 11.250 1.2731 0.02328 0.01642 -0.0067 0.0345 1.0000 11.500 1.2872 0.02431 0.01752 -0.0059 0.0331 1.0000 11.750 1.2996 0.02551 0.01876 -0.0051 0.0318 1.0000 12.000 1.3070 0.02713 0.02043 -0.0041 0.0306 1.0000 12.250 1.3148 0.02879 0.02215 -0.0033 0.0296 1.0000 12.500 1.3259 0.03019 0.02364 -0.0027 0.0287 1.0000 12.750 1.3350 0.03180 0.02532 -0.0021 0.0278 1.0000 13.000 1.3422 0.03363 0.02721 -0.0016 0.0271 1.0000 13.250 1.3458 0.03583 0.02947 -0.0011 0.0265 1.0000 13.500 1.3434 0.03869 0.03238 -0.0006 0.0259 1.0000 13.750 1.3472 0.04102 0.03481 -0.0004 0.0255 1.0000 14.000 1.3520 0.04332 0.03722 -0.0003 0.0250 1.0000 14.250 1.3551 0.04583 0.03983 -0.0003 0.0246 1.0000 14.500 1.3570 0.04854 0.04263 -0.0005 0.0242 1.0000 14.750 1.3584 0.05141 0.04558 -0.0008 0.0237 1.0000 15.000 1.3590 0.05442 0.04868 -0.0013 0.0234 1.0000 15.250 1.3591 0.05759 0.05192 -0.0018 0.0230 1.0000 15.500 1.3583 0.06093 0.05531 -0.0025 0.0227 1.0000 15.750 1.3559 0.06443 0.05887 -0.0032 0.0223 1.0000 16.000 1.3517 0.06794 0.06241 -0.0034 0.0219 1.0000 16.250 1.3519 0.07148 0.06608 -0.0045 0.0217 1.0000 16.500 1.3513 0.07511 0.06983 -0.0057 0.0215 1.0000 16.750 1.3500 0.07885 0.07368 -0.0069 0.0212 1.0000 17.000 1.3484 0.08264 0.07758 -0.0081 0.0209 1.0000 17.250 1.3466 0.08651 0.08155 -0.0094 0.0207 1.0000 17.500 1.3445 0.09044 0.08558 -0.0108 0.0204 1.0000 17.750 1.3420 0.09445 0.08968 -0.0122 0.0202 1.0000 18.000 1.3394 0.09850 0.09382 -0.0138 0.0200 1.0000