XFOIL Version 6.96 Calculated polar for: NACA 63-212 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 ------ -------- --------- --------- -------- -------- -------- -12.000 -0.6759 0.08043 0.07660 -0.0301 1.0000 0.0178 -11.750 -0.7050 0.07039 0.06643 -0.0379 1.0000 0.0176 -11.500 -0.7286 0.06322 0.05912 -0.0431 1.0000 0.0174 -11.250 -0.7516 0.05726 0.05296 -0.0466 1.0000 0.0174 -11.000 -0.7724 0.05240 0.04789 -0.0485 1.0000 0.0173 -10.750 -0.7879 0.04868 0.04397 -0.0487 1.0000 0.0173 -10.500 -0.8040 0.04537 0.04043 -0.0474 1.0000 0.0173 -10.250 -0.8118 0.04222 0.03700 -0.0459 1.0000 0.0173 -10.000 -0.8128 0.03913 0.03358 -0.0446 1.0000 0.0174 -9.750 -0.8085 0.03627 0.03038 -0.0433 1.0000 0.0176 -9.500 -0.7992 0.03379 0.02757 -0.0422 1.0000 0.0177 -9.250 -0.7868 0.03154 0.02499 -0.0411 1.0000 0.0179 -9.000 -0.7718 0.02971 0.02283 -0.0400 1.0000 0.0183 -8.750 -0.7552 0.02803 0.02097 -0.0391 1.0000 0.0186 -8.500 -0.7376 0.02677 0.01966 -0.0382 1.0000 0.0191 -8.250 -0.7198 0.02559 0.01839 -0.0372 1.0000 0.0195 -8.000 -0.7030 0.02442 0.01711 -0.0358 1.0000 0.0198 -7.750 -0.6795 0.02318 0.01576 -0.0358 0.9950 0.0201 -7.500 -0.6474 0.02190 0.01436 -0.0374 0.9849 0.0205 -7.000 -0.5837 0.01968 0.01193 -0.0403 0.9647 0.0217 -6.750 -0.5528 0.01873 0.01089 -0.0415 0.9540 0.0224 -6.500 -0.5228 0.01791 0.00996 -0.0424 0.9433 0.0231 -6.250 -0.4942 0.01703 0.00904 -0.0432 0.9325 0.0241 -6.000 -0.4669 0.01640 0.00834 -0.0436 0.9210 0.0257 -5.750 -0.4404 0.01587 0.00774 -0.0436 0.9098 0.0281 -5.500 -0.4148 0.01528 0.00707 -0.0434 0.8992 0.0313 -5.250 -0.3896 0.01475 0.00647 -0.0432 0.8889 0.0362 -5.000 -0.3648 0.01424 0.00593 -0.0428 0.8783 0.0443 -4.750 -0.3397 0.01379 0.00548 -0.0424 0.8688 0.0579 -4.500 -0.3150 0.01328 0.00506 -0.0421 0.8594 0.0867 -4.250 -0.2906 0.01266 0.00464 -0.0419 0.8498 0.1395 -4.000 -0.2670 0.01188 0.00421 -0.0417 0.8415 0.2284 -3.750 -0.2443 0.01095 0.00388 -0.0415 0.8320 0.3686 -3.500 -0.2194 0.01054 0.00377 -0.0411 0.8239 0.4577 -3.250 -0.1934 0.01036 0.00374 -0.0407 0.8151 0.5177 -3.000 -0.1672 0.01027 0.00373 -0.0403 0.8073 0.5623 -2.750 -0.1405 0.01022 0.00372 -0.0398 0.7989 0.5912 -2.500 -0.1133 0.01021 0.00367 -0.0395 0.7911 0.6127 -2.250 -0.0859 0.01020 0.00362 -0.0393 0.7829 0.6286 -2.000 -0.0584 0.01018 0.00356 -0.0391 0.7754 0.6393 -1.750 -0.0306 0.01016 0.00349 -0.0389 0.7673 0.6495 -1.500 -0.0026 0.01015 0.00342 -0.0389 0.7598 0.6596 -1.250 0.0250 0.01013 0.00338 -0.0387 0.7519 0.6678 -1.000 0.0531 0.01013 0.00332 -0.0387 0.7444 0.6769 -0.750 0.0808 0.01012 0.00331 -0.0385 0.7366 0.6848 -0.500 0.1089 0.01013 0.00327 -0.0385 0.7293 0.6934 -0.250 0.1366 0.01013 0.00327 -0.0384 0.7213 0.7014 0.000 0.1646 0.01015 0.00326 -0.0383 0.7142 0.7098 0.250 0.1924 0.01016 0.00329 -0.0382 0.7062 0.7180 0.500 0.2202 0.01019 0.00330 -0.0381 0.6991 0.7263 0.750 0.2480 0.01021 0.00335 -0.0381 0.6911 0.7348 1.000 0.2757 0.01024 0.00338 -0.0379 0.6840 0.7429 1.250 0.3035 0.01028 0.00345 -0.0379 0.6758 0.7518 1.500 0.3309 0.01032 0.00351 -0.0377 0.6685 0.7598 1.750 0.3586 0.01037 0.00359 -0.0376 0.6600 0.7691 2.000 0.3857 0.01041 0.00369 -0.0373 0.6522 0.7770 2.250 0.4133 0.01047 0.00377 -0.0372 0.6433 0.7864 2.500 0.4401 0.01052 0.00389 -0.0369 0.6342 0.7947 2.750 0.4671 0.01058 0.00398 -0.0366 0.6251 0.8038 3.000 0.4938 0.01064 0.00410 -0.0362 0.6137 0.8132 3.250 0.5199 0.01069 0.00420 -0.0357 0.5994 0.8223 3.500 0.5460 0.01076 0.00429 -0.0352 0.5823 0.8325 3.750 0.5709 0.01083 0.00437 -0.0344 0.5633 0.8420 4.000 0.5955 0.01092 0.00447 -0.0336 0.5372 0.8522 4.250 0.6192 0.01108 0.00454 -0.0327 0.5018 0.8632 4.500 0.6419 0.01128 0.00468 -0.0316 0.4613 0.8744 4.750 0.6638 0.01157 0.00486 -0.0304 0.4148 0.8864 5.000 0.6833 0.01209 0.00511 -0.0290 0.3443 0.8998 5.250 0.6999 0.01295 0.00557 -0.0274 0.2544 0.9158 5.500 0.7174 0.01388 0.00612 -0.0262 0.1754 0.9351 5.750 0.7399 0.01481 0.00673 -0.0260 0.1122 0.9587 6.000 0.7669 0.01566 0.00737 -0.0267 0.0743 1.0000 6.250 0.7899 0.01636 0.00800 -0.0265 0.0570 1.0000 6.500 0.8129 0.01704 0.00865 -0.0262 0.0478 1.0000 7.000 0.8576 0.01843 0.01008 -0.0253 0.0374 1.0000 7.250 0.8789 0.01917 0.01085 -0.0247 0.0343 1.0000 7.500 0.8980 0.02010 0.01180 -0.0238 0.0318 1.0000 7.750 0.9187 0.02084 0.01262 -0.0231 0.0297 1.0000 8.000 0.9385 0.02163 0.01348 -0.0224 0.0277 1.0000 8.250 0.9568 0.02255 0.01442 -0.0214 0.0263 1.0000 8.500 0.9722 0.02374 0.01563 -0.0202 0.0253 1.0000 8.750 0.9894 0.02481 0.01678 -0.0191 0.0244 1.0000 9.000 1.0068 0.02589 0.01796 -0.0180 0.0237 1.0000 9.250 1.0238 0.02703 0.01921 -0.0169 0.0229 1.0000 9.500 1.0401 0.02822 0.02049 -0.0157 0.0223 1.0000 9.750 1.0561 0.02945 0.02182 -0.0146 0.0216 1.0000 10.000 1.0715 0.03067 0.02312 -0.0134 0.0210 1.0000 10.250 1.0856 0.03188 0.02439 -0.0123 0.0204 1.0000 10.500 1.0991 0.03327 0.02584 -0.0112 0.0199 1.0000 10.750 1.1124 0.03512 0.02780 -0.0102 0.0193 1.0000 11.000 1.1242 0.03677 0.02966 -0.0090 0.0190 1.0000 11.250 1.1340 0.03866 0.03177 -0.0077 0.0186 1.0000 11.500 1.1411 0.04077 0.03413 -0.0064 0.0183 1.0000 11.750 1.1454 0.04311 0.03671 -0.0052 0.0181 1.0000 12.000 1.1469 0.04566 0.03951 -0.0041 0.0178 1.0000 12.250 1.1450 0.04854 0.04265 -0.0031 0.0176 1.0000 12.500 1.1403 0.05170 0.04606 -0.0024 0.0175 1.0000 12.750 1.1328 0.05522 0.04982 -0.0022 0.0173 1.0000 13.000 1.1233 0.05907 0.05391 -0.0024 0.0171 1.0000 13.250 1.1102 0.06362 0.05871 -0.0033 0.0170 1.0000 13.500 1.0960 0.06849 0.06380 -0.0049 0.0169 1.0000 13.750 1.0791 0.07413 0.06966 -0.0072 0.0168 1.0000 14.000 1.0592 0.08066 0.07641 -0.0106 0.0167 1.0000 14.250 1.0292 0.08973 0.08574 -0.0158 0.0169 1.0000 14.500 0.9968 0.10052 0.09677 -0.0229 0.0171 1.0000 14.750 0.9379 0.12061 0.11716 -0.0364 0.0177 1.0000