XFOIL Version 6.96 Calculated polar for: NASA/LANGLEY RC-12(N)1 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 ------ -------- --------- --------- -------- -------- -------- -10.500 -0.4899 0.09013 0.08700 -0.0132 1.0000 0.0200 -10.250 -0.5026 0.08320 0.08010 -0.0164 1.0000 0.0200 -10.000 -0.5216 0.07443 0.07134 -0.0213 1.0000 0.0197 -9.750 -0.7046 0.06396 0.06034 -0.0253 1.0000 0.0174 -9.500 -0.7229 0.05908 0.05527 -0.0243 1.0000 0.0174 -9.250 -0.7323 0.05460 0.05056 -0.0234 1.0000 0.0174 -9.000 -0.7330 0.05116 0.04694 -0.0226 0.9792 0.0176 -8.750 -0.7189 0.04957 0.04519 -0.0228 0.9169 0.0180 -8.500 -0.7101 0.04774 0.04315 -0.0216 0.8916 0.0185 -8.250 -0.7024 0.04516 0.04029 -0.0200 0.8749 0.0191 -8.000 -0.6951 0.04173 0.03646 -0.0181 0.8625 0.0197 -7.750 -0.6867 0.03791 0.03218 -0.0161 0.8525 0.0199 -7.500 -0.6747 0.03437 0.02816 -0.0142 0.8434 0.0201 -7.250 -0.6595 0.03131 0.02463 -0.0124 0.8358 0.0205 -7.000 -0.6410 0.02870 0.02156 -0.0110 0.8286 0.0210 -6.750 -0.6203 0.02662 0.01903 -0.0098 0.8225 0.0216 -6.500 -0.5977 0.02497 0.01705 -0.0090 0.8158 0.0225 -6.250 -0.5745 0.02385 0.01581 -0.0085 0.8100 0.0233 -6.000 -0.5501 0.02272 0.01452 -0.0080 0.8044 0.0239 -5.750 -0.5252 0.02161 0.01325 -0.0075 0.7987 0.0245 -5.500 -0.5005 0.02060 0.01207 -0.0069 0.7938 0.0253 -5.250 -0.4752 0.01964 0.01098 -0.0065 0.7884 0.0263 -5.000 -0.4501 0.01878 0.01001 -0.0059 0.7832 0.0273 -4.750 -0.4254 0.01811 0.00922 -0.0053 0.7788 0.0285 -4.500 -0.4015 0.01732 0.00845 -0.0048 0.7736 0.0305 -4.250 -0.3767 0.01679 0.00788 -0.0044 0.7685 0.0325 -4.000 -0.3524 0.01624 0.00724 -0.0037 0.7644 0.0345 -3.750 -0.3273 0.01576 0.00668 -0.0033 0.7598 0.0364 -3.500 -0.3032 0.01519 0.00613 -0.0027 0.7547 0.0403 -3.250 -0.2778 0.01484 0.00570 -0.0023 0.7504 0.0449 -3.000 -0.2527 0.01442 0.00523 -0.0018 0.7463 0.0500 -2.750 -0.2266 0.01411 0.00490 -0.0016 0.7413 0.0587 -2.500 -0.2012 0.01373 0.00453 -0.0012 0.7368 0.0735 -2.250 -0.1773 0.01318 0.00418 -0.0006 0.7331 0.1263 -2.000 -0.1704 0.01100 0.00388 0.0024 0.7283 0.5659 -1.750 -0.1472 0.01075 0.00386 0.0036 0.7236 0.6462 -1.500 -0.1223 0.01058 0.00376 0.0044 0.7196 0.6900 -1.250 -0.0969 0.01040 0.00369 0.0052 0.7154 0.7277 -1.000 -0.0706 0.01021 0.00369 0.0058 0.7106 0.7685 -0.750 -0.0424 0.01012 0.00374 0.0062 0.7062 0.8100 -0.500 -0.0121 0.01013 0.00375 0.0061 0.7026 0.8371 -0.250 0.0194 0.01017 0.00379 0.0054 0.6974 0.8569 0.000 0.0513 0.01021 0.00380 0.0047 0.6925 0.8757 0.250 0.0834 0.01026 0.00379 0.0039 0.6884 0.8928 0.500 0.1164 0.01032 0.00384 0.0029 0.6832 0.9077 0.750 0.1498 0.01038 0.00387 0.0017 0.6776 0.9204 1.000 0.1827 0.01043 0.00386 0.0008 0.6730 0.9322 1.250 0.2173 0.01049 0.00393 -0.0007 0.6667 0.9422 1.500 0.2527 0.01054 0.00395 -0.0023 0.6606 0.9502 1.750 0.2855 0.01060 0.00398 -0.0034 0.6547 0.9593 2.000 0.3232 0.01065 0.00404 -0.0055 0.6476 0.9648 2.250 0.3565 0.01070 0.00405 -0.0067 0.6418 0.9725 2.500 0.3936 0.01074 0.00413 -0.0089 0.6338 0.9777 3.000 0.4645 0.01081 0.00424 -0.0124 0.6183 0.9889 3.250 0.4998 0.01085 0.00428 -0.0141 0.6103 0.9942 3.500 0.5366 0.01086 0.00434 -0.0162 0.6005 0.9982 3.750 0.5667 0.01087 0.00437 -0.0168 0.5876 1.0000 4.000 0.5913 0.01088 0.00434 -0.0162 0.5694 1.0000 4.250 0.6159 0.01092 0.00437 -0.0157 0.5475 1.0000 4.500 0.6403 0.01101 0.00442 -0.0151 0.5243 1.0000 4.750 0.6645 0.01114 0.00451 -0.0145 0.4970 1.0000 5.000 0.6882 0.01134 0.00463 -0.0139 0.4647 1.0000 5.250 0.7110 0.01166 0.00481 -0.0131 0.4222 1.0000 5.500 0.7322 0.01216 0.00508 -0.0123 0.3707 1.0000 5.750 0.7520 0.01283 0.00548 -0.0113 0.3134 1.0000 6.000 0.7709 0.01358 0.00597 -0.0103 0.2575 1.0000 6.250 0.7889 0.01440 0.00653 -0.0092 0.2018 1.0000 6.500 0.8062 0.01525 0.00713 -0.0080 0.1542 1.0000 6.750 0.8239 0.01601 0.00773 -0.0068 0.1214 1.0000 7.000 0.8418 0.01673 0.00834 -0.0056 0.0998 1.0000 7.250 0.8599 0.01738 0.00896 -0.0043 0.0841 1.0000 7.500 0.8775 0.01805 0.00960 -0.0030 0.0724 1.0000 8.000 0.9120 0.01937 0.01093 -0.0002 0.0564 1.0000 8.250 0.9275 0.02014 0.01169 0.0013 0.0510 1.0000 8.500 0.9443 0.02080 0.01244 0.0027 0.0463 1.0000 8.750 0.9582 0.02167 0.01330 0.0043 0.0423 1.0000 9.000 0.9731 0.02245 0.01417 0.0059 0.0396 1.0000 9.250 0.9872 0.02327 0.01507 0.0075 0.0370 1.0000 9.500 0.9999 0.02417 0.01601 0.0091 0.0347 1.0000 9.750 1.0073 0.02533 0.01720 0.0113 0.0326 1.0000 10.000 1.0185 0.02624 0.01822 0.0131 0.0310 1.0000 10.250 1.0290 0.02729 0.01937 0.0147 0.0294 1.0000 10.500 1.0392 0.02847 0.02063 0.0160 0.0281 1.0000 10.750 1.0490 0.02975 0.02198 0.0172 0.0270 1.0000 11.000 1.0569 0.03128 0.02355 0.0184 0.0259 1.0000 11.250 1.0651 0.03290 0.02526 0.0196 0.0250 1.0000 11.500 1.0759 0.03430 0.02681 0.0206 0.0241 1.0000 11.750 1.0859 0.03579 0.02843 0.0214 0.0230 1.0000 12.000 1.0949 0.03735 0.03011 0.0222 0.0221 1.0000 12.250 1.1029 0.03904 0.03190 0.0229 0.0213 1.0000 12.500 1.1099 0.04084 0.03379 0.0235 0.0207 1.0000 12.750 1.1156 0.04282 0.03585 0.0242 0.0202 1.0000 13.000 1.1194 0.04510 0.03821 0.0249 0.0197 1.0000 13.250 1.1234 0.04741 0.04072 0.0254 0.0192 1.0000 13.500 1.1258 0.04990 0.04343 0.0258 0.0187 1.0000 13.750 1.1262 0.05263 0.04637 0.0259 0.0182 1.0000 14.000 1.1251 0.05556 0.04949 0.0258 0.0177 1.0000 14.250 1.1228 0.05868 0.05279 0.0255 0.0172 1.0000 14.500 1.1192 0.06203 0.05631 0.0249 0.0168 1.0000 14.750 1.1141 0.06565 0.06008 0.0241 0.0165 1.0000 15.000 1.1074 0.06964 0.06423 0.0230 0.0163 1.0000 15.250 1.0994 0.07402 0.06877 0.0215 0.0161 1.0000 15.500 1.0901 0.07882 0.07373 0.0196 0.0160 1.0000 15.750 1.0793 0.08413 0.07920 0.0172 0.0158 1.0000 16.000 1.0664 0.09006 0.08529 0.0144 0.0157 1.0000 16.250 1.0511 0.09674 0.09215 0.0109 0.0156 1.0000 16.500 1.0318 0.10464 0.10025 0.0066 0.0156 1.0000 16.750 1.0032 0.11515 0.11100 0.0005 0.0157 1.0000