XFOIL Version 6.96 Calculated polar for: NACA 63 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 ------ -------- --------- --------- -------- -------- -------- -16.000 -0.6517 0.10280 0.09862 -0.0575 1.0000 0.0490 -15.750 -0.6982 0.09056 0.08622 -0.0650 1.0000 0.0484 -15.500 -0.7383 0.08088 0.07635 -0.0708 1.0000 0.0477 -15.250 -0.7759 0.07285 0.06809 -0.0753 1.0000 0.0474 -15.000 -0.8048 0.06664 0.06166 -0.0783 1.0000 0.0472 -14.750 -0.8287 0.06146 0.05626 -0.0803 1.0000 0.0472 -14.500 -0.8479 0.05704 0.05161 -0.0814 1.0000 0.0472 -14.250 -0.8627 0.05333 0.04769 -0.0819 1.0000 0.0474 -14.000 -0.8737 0.05006 0.04421 -0.0820 1.0000 0.0476 -13.750 -0.8832 0.04718 0.04111 -0.0816 1.0000 0.0481 -13.500 -0.8889 0.04469 0.03840 -0.0809 1.0000 0.0484 -13.250 -0.8945 0.04248 0.03598 -0.0797 1.0000 0.0489 -13.000 -0.9007 0.04067 0.03395 -0.0781 1.0000 0.0493 -12.750 -0.8796 0.03862 0.03193 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0.01625 0.00929 -0.0708 0.6472 0.6975 1.750 0.5124 0.01633 0.00939 -0.0710 0.6417 0.7041 2.000 0.5409 0.01633 0.00939 -0.0711 0.6372 0.7090 2.250 0.5702 0.01639 0.00942 -0.0712 0.6336 0.7138 2.500 0.5955 0.01657 0.00970 -0.0711 0.6277 0.7203 2.750 0.6233 0.01662 0.00978 -0.0712 0.6224 0.7265 3.000 0.6514 0.01665 0.00983 -0.0711 0.6183 0.7313 3.250 0.6796 0.01677 0.00996 -0.0712 0.6137 0.7374 3.500 0.7055 0.01691 0.01018 -0.0712 0.6076 0.7441 3.750 0.7322 0.01695 0.01028 -0.0708 0.6027 0.7493 4.000 0.7626 0.01699 0.01028 -0.0712 0.5987 0.7560 4.250 0.7869 0.01718 0.01059 -0.0709 0.5924 0.7626 4.500 0.8124 0.01724 0.01073 -0.0704 0.5867 0.7680 4.750 0.8427 0.01724 0.01070 -0.0708 0.5822 0.7752 5.000 0.8668 0.01740 0.01097 -0.0703 0.5758 0.7818 5.250 0.8918 0.01741 0.01108 -0.0697 0.5691 0.7882 5.500 0.9243 0.01734 0.01091 -0.0704 0.5636 0.7960 5.750 0.9438 0.01743 0.01120 -0.0689 0.5553 0.8020 6.000 0.9719 0.01735 0.01112 -0.0688 0.5487 0.8098 6.250 0.9956 0.01740 0.01127 -0.0681 0.5409 0.8172 6.500 1.0203 0.01728 0.01119 -0.0673 0.5323 0.8246 6.750 1.0437 0.01721 0.01119 -0.0665 0.5220 0.8329 7.000 1.0685 0.01701 0.01096 -0.0655 0.5121 0.8406 7.250 1.0879 0.01702 0.01111 -0.0641 0.5007 0.8499 7.500 1.1085 0.01699 0.01115 -0.0627 0.4910 0.8585 7.750 1.1290 0.01698 0.01120 -0.0613 0.4801 0.8681 8.000 1.1453 0.01703 0.01137 -0.0593 0.4683 0.8789 8.250 1.1612 0.01705 0.01144 -0.0570 0.4560 0.8900 8.500 1.1755 0.01708 0.01151 -0.0546 0.4423 0.9031 8.750 1.1865 0.01715 0.01162 -0.0516 0.4271 0.9190 9.000 1.1940 0.01724 0.01177 -0.0482 0.4103 0.9413 9.250 1.2087 0.01744 0.01206 -0.0467 0.3876 1.0000 9.500 1.2212 0.01812 0.01263 -0.0456 0.3614 1.0000 9.750 1.2283 0.01909 0.01348 -0.0439 0.3310 1.0000 10.000 1.2295 0.02042 0.01463 -0.0416 0.3000 1.0000 10.250 1.2271 0.02207 0.01610 -0.0392 0.2697 1.0000 10.500 1.2222 0.02401 0.01788 -0.0369 0.2404 1.0000 10.750 1.2155 0.02624 0.01994 -0.0347 0.2127 1.0000 11.000 1.2082 0.02870 0.02223 -0.0328 0.1870 1.0000 11.250 1.2019 0.03125 0.02464 -0.0311 0.1639 1.0000 11.500 1.1958 0.03391 0.02718 -0.0298 0.1447 1.0000 11.750 1.1906 0.03663 0.02980 -0.0286 0.1293 1.0000 12.000 1.1876 0.03926 0.03236 -0.0277 0.1168 1.0000 12.250 1.1862 0.04186 0.03492 -0.0270 0.1067 1.0000 12.500 1.1838 0.04461 0.03760 -0.0264 0.0992 1.0000 12.750 1.1866 0.04699 0.04000 -0.0260 0.0921 1.0000 13.000 1.1876 0.04959 0.04256 -0.0256 0.0865 1.0000 13.250 1.1924 0.05188 0.04488 -0.0254 0.0814 1.0000 13.500 1.1947 0.05439 0.04731 -0.0250 0.0773 1.0000 13.750 1.2019 0.05653 0.04954 -0.0249 0.0733 1.0000 14.000 1.2075 0.05883 0.05183 -0.0249 0.0699 1.0000 14.250 1.2152 0.06086 0.05385 -0.0245 0.0668 1.0000 14.500 1.2232 0.06300 0.05607 -0.0246 0.0639 1.0000 14.750 1.2311 0.06512 0.05818 -0.0246 0.0613 1.0000 15.000 1.2437 0.06661 0.05960 -0.0241 0.0589 1.0000 15.250 1.2516 0.06888 0.06201 -0.0242 0.0568 1.0000 15.500 1.2606 0.07098 0.06417 -0.0243 0.0548 1.0000 15.750 1.2718 0.07276 0.06592 -0.0243 0.0530 1.0000 16.000 1.2871 0.07411 0.06725 -0.0239 0.0511 1.0000 16.250 1.2929 0.07672 0.07004 -0.0242 0.0498 1.0000 16.500 1.3001 0.07918 0.07262 -0.0246 0.0484 1.0000 16.750 1.3085 0.08145 0.07496 -0.0249 0.0471 1.0000 17.000 1.3206 0.08323 0.07671 -0.0250 0.0458 1.0000 17.250 1.3357 0.08484 0.07834 -0.0247 0.0444 1.0000 17.500 1.3335 0.08859 0.08231 -0.0257 0.0436 1.0000 17.750 1.3333 0.09215 0.08607 -0.0267 0.0428 1.0000