XFOIL Version 6.96 Calculated polar for: NACA 63012A 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 ------ -------- --------- --------- -------- -------- -------- -13.750 -0.8479 0.09228 0.08836 -0.0103 1.0000 0.0164 -13.500 -0.8729 0.08305 0.07899 -0.0165 1.0000 0.0162 -13.250 -0.8963 0.07509 0.07085 -0.0217 1.0000 0.0162 -13.000 -0.9185 0.06820 0.06375 -0.0257 1.0000 0.0162 -12.750 -0.9388 0.06231 0.05763 -0.0286 1.0000 0.0162 -12.500 -0.9570 0.05726 0.05232 -0.0303 1.0000 0.0162 -12.250 -0.9729 0.05299 0.04777 -0.0309 1.0000 0.0163 -12.000 -0.9853 0.04931 0.04385 -0.0305 1.0000 0.0165 -11.750 -0.9912 0.04642 0.04080 -0.0295 1.0000 0.0168 -11.500 -0.9926 0.04420 0.03845 -0.0282 1.0000 0.0170 -11.250 -0.9918 0.04229 0.03640 -0.0265 1.0000 0.0173 -11.000 -0.9897 0.04045 0.03440 -0.0245 1.0000 0.0176 -10.750 -0.9846 0.03852 0.03226 -0.0227 1.0000 0.0179 -10.500 -0.9764 0.03648 0.02998 -0.0211 1.0000 0.0183 -10.250 -0.9655 0.03452 0.02778 -0.0196 1.0000 0.0186 -10.000 -0.9522 0.03269 0.02572 -0.0182 1.0000 0.0190 -9.750 -0.9370 0.03098 0.02377 -0.0170 1.0000 0.0195 -9.500 -0.9201 0.02940 0.02198 -0.0159 1.0000 0.0200 -9.250 -0.9020 0.02809 0.02048 -0.0148 1.0000 0.0207 -9.000 -0.8829 0.02697 0.01916 -0.0138 1.0000 0.0214 -8.750 -0.8647 0.02542 0.01754 -0.0128 1.0000 0.0221 -8.500 -0.8462 0.02422 0.01629 -0.0117 1.0000 0.0227 -8.250 -0.8274 0.02320 0.01520 -0.0106 1.0000 0.0233 -8.000 -0.8085 0.02225 0.01420 -0.0095 1.0000 0.0241 -7.750 -0.7898 0.02135 0.01324 -0.0083 1.0000 0.0250 -7.500 -0.7713 0.02051 0.01232 -0.0069 1.0000 0.0260 -7.250 -0.7530 0.01972 0.01147 -0.0055 1.0000 0.0271 -7.000 -0.7353 0.01896 0.01063 -0.0040 1.0000 0.0284 -6.750 -0.7188 0.01819 0.00987 -0.0024 1.0000 0.0306 -6.500 -0.7009 0.01762 0.00927 -0.0008 1.0000 0.0331 -6.250 -0.6831 0.01708 0.00866 0.0008 1.0000 0.0358 -6.000 -0.6670 0.01643 0.00801 0.0027 1.0000 0.0393 -5.750 -0.6437 0.01590 0.00744 0.0031 0.9975 0.0448 -5.500 -0.6101 0.01526 0.00682 0.0013 0.9901 0.0556 -5.250 -0.5768 0.01460 0.00625 -0.0005 0.9825 0.0753 -5.000 -0.5451 0.01384 0.00570 -0.0020 0.9738 0.1158 -4.750 -0.5168 0.01290 0.00514 -0.0030 0.9629 0.1929 -4.500 -0.4908 0.01185 0.00463 -0.0036 0.9512 0.3039 -4.250 -0.4646 0.01108 0.00431 -0.0038 0.9395 0.4106 -4.000 -0.4360 0.01069 0.00413 -0.0041 0.9284 0.4788 -3.750 -0.4070 0.01044 0.00401 -0.0044 0.9174 0.5255 -3.500 -0.3794 0.01027 0.00390 -0.0042 0.9049 0.5603 -3.250 -0.3521 0.01015 0.00381 -0.0039 0.8928 0.5911 -3.000 -0.3248 0.01007 0.00374 -0.0036 0.8810 0.6167 -2.750 -0.2977 0.01000 0.00367 -0.0032 0.8696 0.6375 -2.500 -0.2708 0.00995 0.00358 -0.0028 0.8580 0.6544 -2.250 -0.2440 0.00991 0.00351 -0.0024 0.8465 0.6683 -2.000 -0.2170 0.00987 0.00343 -0.0021 0.8357 0.6795 -1.750 -0.1897 0.00984 0.00332 -0.0018 0.8254 0.6899 -1.500 -0.1627 0.00981 0.00326 -0.0015 0.8146 0.6992 -1.250 -0.1356 0.00978 0.00320 -0.0013 0.8044 0.7086 -1.000 -0.1084 0.00977 0.00313 -0.0010 0.7951 0.7187 -0.750 -0.0814 0.00975 0.00311 -0.0008 0.7846 0.7276 -0.500 -0.0542 0.00974 0.00308 -0.0005 0.7752 0.7372 -0.250 -0.0271 0.00974 0.00306 -0.0002 0.7659 0.7468 0.000 0.0000 0.00973 0.00307 0.0000 0.7560 0.7560 0.250 0.0271 0.00974 0.00306 0.0002 0.7468 0.7659 0.500 0.0542 0.00974 0.00308 0.0005 0.7372 0.7752 0.750 0.0814 0.00975 0.00311 0.0008 0.7276 0.7847 1.000 0.1084 0.00977 0.00313 0.0010 0.7187 0.7950 1.250 0.1356 0.00978 0.00320 0.0013 0.7086 0.8044 1.500 0.1627 0.00981 0.00326 0.0015 0.6992 0.8146 1.750 0.1897 0.00984 0.00332 0.0018 0.6899 0.8254 2.000 0.2170 0.00987 0.00343 0.0021 0.6796 0.8357 2.250 0.2440 0.00991 0.00351 0.0024 0.6683 0.8465 2.500 0.2708 0.00995 0.00358 0.0028 0.6544 0.8580 2.750 0.2977 0.01000 0.00367 0.0032 0.6375 0.8696 3.000 0.3249 0.01007 0.00374 0.0036 0.6168 0.8810 3.250 0.3521 0.01015 0.00381 0.0039 0.5910 0.8928 3.500 0.3794 0.01027 0.00390 0.0042 0.5602 0.9049 3.750 0.4070 0.01044 0.00401 0.0044 0.5255 0.9174 4.000 0.4361 0.01069 0.00414 0.0041 0.4789 0.9284 4.250 0.4646 0.01108 0.00431 0.0038 0.4106 0.9394 4.500 0.4908 0.01185 0.00463 0.0036 0.3042 0.9511 4.750 0.5168 0.01290 0.00514 0.0030 0.1929 0.9628 5.000 0.5451 0.01384 0.00570 0.0020 0.1158 0.9738 5.250 0.5768 0.01460 0.00625 0.0005 0.0753 0.9824 5.500 0.6101 0.01526 0.00682 -0.0013 0.0556 0.9901 5.750 0.6437 0.01590 0.00744 -0.0031 0.0448 0.9974 6.000 0.6671 0.01643 0.00801 -0.0027 0.0393 1.0000 6.250 0.6832 0.01708 0.00866 -0.0008 0.0358 1.0000 6.500 0.7009 0.01762 0.00927 0.0008 0.0331 1.0000 6.750 0.7188 0.01819 0.00987 0.0024 0.0306 1.0000 7.000 0.7353 0.01896 0.01063 0.0040 0.0284 1.0000 7.250 0.7530 0.01972 0.01146 0.0055 0.0271 1.0000 7.500 0.7713 0.02051 0.01232 0.0069 0.0260 1.0000 7.750 0.7898 0.02135 0.01324 0.0083 0.0250 1.0000 8.000 0.8085 0.02225 0.01420 0.0095 0.0241 1.0000 8.250 0.8274 0.02320 0.01520 0.0106 0.0233 1.0000 8.500 0.8462 0.02422 0.01629 0.0117 0.0227 1.0000 8.750 0.8647 0.02542 0.01754 0.0128 0.0221 1.0000 9.000 0.8829 0.02696 0.01916 0.0138 0.0214 1.0000 9.250 0.9020 0.02809 0.02047 0.0148 0.0207 1.0000 9.500 0.9201 0.02939 0.02198 0.0159 0.0200 1.0000 9.750 0.9370 0.03097 0.02376 0.0170 0.0195 1.0000 10.000 0.9523 0.03268 0.02571 0.0182 0.0190 1.0000 10.250 0.9656 0.03452 0.02778 0.0196 0.0186 1.0000 10.500 0.9765 0.03648 0.02998 0.0210 0.0183 1.0000 10.750 0.9847 0.03852 0.03226 0.0227 0.0179 1.0000 11.000 0.9899 0.04046 0.03440 0.0245 0.0176 1.0000 11.250 0.9921 0.04229 0.03641 0.0265 0.0173 1.0000 11.500 0.9929 0.04420 0.03846 0.0281 0.0170 1.0000 11.750 0.9916 0.04643 0.04081 0.0295 0.0167 1.0000 12.000 0.9857 0.04933 0.04387 0.0304 0.0165 1.0000 12.250 0.9732 0.05301 0.04779 0.0308 0.0163 1.0000 12.500 0.9574 0.05730 0.05236 0.0302 0.0162 1.0000 12.750 0.9392 0.06236 0.05769 0.0284 0.0162 1.0000 13.000 0.9187 0.06831 0.06387 0.0255 0.0161 1.0000 13.250 0.8968 0.07520 0.07096 0.0215 0.0162 1.0000 13.500 0.8734 0.08317 0.07911 0.0162 0.0162 1.0000 13.750 0.8481 0.09251 0.08859 0.0100 0.0164 1.0000