XFOIL Version 6.94 Calculated polar for: NACA 6412 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.6549 0.00937 0.00267 -0.1394 0.6558 0.2719 0.500 0.7057 0.00934 0.00274 -0.1383 0.6333 0.3425 2.500 0.9339 0.00910 0.00349 -0.1396 0.5611 0.9999 3.000 0.9853 0.00948 0.00373 -0.1387 0.5470 0.9999 3.500 1.0369 0.00980 0.00400 -0.1379 0.5338 0.9999 4.000 1.0886 0.01015 0.00432 -0.1371 0.5222 0.9999 5.000 1.1905 0.01090 0.00503 -0.1353 0.4995 0.9999 5.500 1.2407 0.01136 0.00545 -0.1344 0.4882 0.9999 6.000 1.2893 0.01173 0.00585 -0.1331 0.4760 0.9999 6.500 1.3368 0.01214 0.00631 -0.1316 0.4626 0.9999 7.000 1.3794 0.01255 0.00673 -0.1292 0.4429 0.9999 7.500 1.4214 0.01302 0.00723 -0.1267 0.4244 0.9999 8.000 1.4597 0.01353 0.00778 -0.1236 0.4052 0.9999 8.500 1.4950 0.01417 0.00843 -0.1200 0.3825 0.9999 9.000 1.5269 0.01503 0.00926 -0.1160 0.3544 0.9999 9.500 1.5515 0.01632 0.01044 -0.1112 0.3128 0.9999 10.000 1.5660 0.01833 0.01220 -0.1053 0.2594 0.9999 11.000 1.5693 0.02472 0.01797 -0.0923 0.1425 0.9999 11.500 1.5663 0.02875 0.02178 -0.0866 0.1006 0.9999 12.000 1.5654 0.03299 0.02594 -0.0820 0.0743 0.9999 12.500 1.5663 0.03743 0.03041 -0.0783 0.0588 0.9999 13.000 1.5666 0.04234 0.03539 -0.0753 0.0490 0.9999 13.500 1.5644 0.04783 0.04099 -0.0729 0.0422 0.9999 14.000 1.5567 0.05431 0.04757 -0.0710 0.0372 0.9999 14.500 1.5564 0.06023 0.05368 -0.0698 0.0337 0.9999 15.000 1.5439 0.06785 0.06143 -0.0690 0.0308 0.9999 15.500 1.5375 0.07499 0.06878 -0.0686 0.0287 0.9999 16.000 1.5314 0.08219 0.07615 -0.0687 0.0268 0.9999 16.500 1.5164 0.09073 0.08481 -0.0691 0.0253 0.9999 17.000 1.5088 0.09836 0.09264 -0.0697 0.0240 0.9999 17.500 1.5052 0.10552 0.09998 -0.0706 0.0228 0.9999 18.000 1.5009 0.11288 0.10748 -0.0719 0.0217 0.9999 18.500 1.4952 0.12035 0.11505 -0.0733 0.0207 0.9999 19.000 1.4931 0.12704 0.12189 -0.0745 0.0199 0.9999 19.500 1.4932 0.13381 0.12887 -0.0763 0.0193 0.9999 20.000 1.4932 0.14071 0.13596 -0.0786 0.0186 0.9999 20.500 1.4932 0.14771 0.14313 -0.0813 0.0179 0.9999 21.000 1.4938 0.15470 0.15024 -0.0844 0.0173 0.9999 21.500 1.4950 0.16125 0.15690 -0.0874 0.0166 0.9999 22.000 1.4918 0.16860 0.16447 -0.0909 0.0161 0.9999 22.500 1.4836 0.17797 0.17413 -0.0965 0.0159 0.9999 23.000 1.4726 0.18826 0.18471 -0.1031 0.0156 0.9999 23.500 1.4574 0.20003 0.19678 -0.1110 0.0153 0.9999 24.000 1.4340 0.21474 0.21182 -0.1214 0.0151 0.9999