XFOIL Version 6.96 Calculated polar for: NACA 63-415 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.500 -0.7187 0.09149 0.08869 -0.0506 1.0000 0.0203 -15.250 -0.7729 0.07691 0.07384 -0.0605 1.0000 0.0198 -15.000 -0.8084 0.06743 0.06413 -0.0667 1.0000 0.0197 -14.750 -0.8319 0.06085 0.05736 -0.0706 1.0000 0.0197 -14.500 -0.8540 0.05497 0.05126 -0.0737 1.0000 0.0197 -14.250 -0.8685 0.05044 0.04655 -0.0757 1.0000 0.0198 -14.000 -0.8800 0.04651 0.04243 -0.0770 1.0000 0.0199 -13.750 -0.8880 0.04322 0.03896 -0.0778 1.0000 0.0202 -13.500 -0.8935 0.04030 0.03587 -0.0781 1.0000 0.0204 -13.250 -0.8968 0.03782 0.03321 -0.0780 1.0000 0.0206 -13.000 -0.8983 0.03561 0.03083 -0.0776 1.0000 0.0209 -12.750 -0.8990 0.03389 0.02892 -0.0768 1.0000 0.0211 -12.500 -0.8982 0.03149 0.02639 -0.0755 1.0000 0.0215 -12.250 -0.8916 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0.00855 0.00292 -0.0792 0.6090 0.6961 2.250 0.6018 0.00859 0.00301 -0.0793 0.6027 0.7031 2.500 0.6304 0.00864 0.00308 -0.0795 0.5965 0.7097 2.750 0.6586 0.00873 0.00318 -0.0795 0.5907 0.7162 3.000 0.6873 0.00878 0.00327 -0.0797 0.5838 0.7238 3.250 0.7150 0.00886 0.00335 -0.0797 0.5768 0.7302 3.500 0.7430 0.00889 0.00345 -0.0797 0.5678 0.7375 3.750 0.7706 0.00898 0.00353 -0.0797 0.5594 0.7443 4.000 0.7983 0.00902 0.00364 -0.0796 0.5508 0.7516 4.250 0.8258 0.00912 0.00374 -0.0796 0.5416 0.7591 4.500 0.8526 0.00918 0.00385 -0.0794 0.5300 0.7661 4.750 0.8798 0.00927 0.00395 -0.0793 0.5163 0.7742 5.000 0.9057 0.00936 0.00408 -0.0789 0.5011 0.7814 5.250 0.9324 0.00950 0.00422 -0.0788 0.4867 0.7897 5.500 0.9582 0.00963 0.00439 -0.0784 0.4730 0.7971 5.750 0.9843 0.00981 0.00458 -0.0781 0.4575 0.8058 6.000 1.0089 0.01000 0.00478 -0.0776 0.4385 0.8136 6.250 1.0330 0.01029 0.00501 -0.0770 0.4132 0.8227 6.500 1.0546 0.01066 0.00531 -0.0760 0.3793 0.8311 6.750 1.0739 0.01125 0.00571 -0.0748 0.3334 0.8410 7.000 1.0892 0.01205 0.00627 -0.0730 0.2796 0.8508 7.250 1.1023 0.01297 0.00692 -0.0708 0.2239 0.8615 7.500 1.1139 0.01393 0.00763 -0.0685 0.1737 0.8737 7.750 1.1250 0.01479 0.00831 -0.0661 0.1343 0.8874 8.000 1.1333 0.01562 0.00898 -0.0630 0.1020 0.9038 8.250 1.1375 0.01628 0.00958 -0.0591 0.0796 0.9283 8.500 1.1435 0.01693 0.01019 -0.0558 0.0645 1.0000 8.750 1.1562 0.01780 0.01099 -0.0541 0.0548 1.0000 9.000 1.1708 0.01854 0.01174 -0.0527 0.0497 1.0000 9.250 1.1818 0.01948 0.01266 -0.0509 0.0456 1.0000 9.500 1.1957 0.02027 0.01349 -0.0495 0.0429 1.0000 9.750 1.2056 0.02132 0.01455 -0.0478 0.0403 1.0000 10.000 1.2147 0.02248 0.01574 -0.0461 0.0382 1.0000 10.250 1.2273 0.02345 0.01676 -0.0449 0.0363 1.0000 10.500 1.2374 0.02462 0.01797 -0.0436 0.0345 1.0000 10.750 1.2391 0.02645 0.01981 -0.0418 0.0326 1.0000 11.000 1.2523 0.02751 0.02095 -0.0409 0.0314 1.0000 11.250 1.2625 0.02882 0.02231 -0.0399 0.0298 1.0000 11.500 1.2704 0.03035 0.02388 -0.0389 0.0287 1.0000 11.750 1.2701 0.03262 0.02617 -0.0375 0.0274 1.0000 12.000 1.2778 0.03429 0.02792 -0.0367 0.0266 1.0000 12.250 1.2867 0.03591 0.02962 -0.0360 0.0257 1.0000 12.500 1.2940 0.03770 0.03147 -0.0353 0.0248 1.0000 12.750 1.3005 0.03960 0.03342 -0.0347 0.0241 1.0000 13.000 1.3047 0.04176 0.03561 -0.0342 0.0234 1.0000 13.250 1.3020 0.04464 0.03854 -0.0334 0.0226 1.0000 13.500 1.3105 0.04652 0.04051 -0.0331 0.0222 1.0000 13.750 1.3174 0.04860 0.04268 -0.0329 0.0217 1.0000 14.000 1.3239 0.05076 0.04493 -0.0327 0.0210 1.0000 14.250 1.3297 0.05305 0.04730 -0.0327 0.0205 1.0000 14.500 1.3357 0.05537 0.04968 -0.0327 0.0201 1.0000 14.750 1.3406 0.05786 0.05221 -0.0329 0.0196 1.0000 15.000 1.3446 0.06048 0.05488 -0.0330 0.0193 1.0000 15.250 1.3475 0.06325 0.05769 -0.0330 0.0189 1.0000 15.500 1.3510 0.06603 0.06056 -0.0330 0.0185 1.0000 15.750 1.3554 0.06881 0.06346 -0.0334 0.0183 1.0000 16.000 1.3588 0.07178 0.06656 -0.0340 0.0181 1.0000 16.250 1.3619 0.07485 0.06975 -0.0346 0.0178 1.0000 16.500 1.3642 0.07809 0.07310 -0.0354 0.0175 1.0000 16.750 1.3660 0.08144 0.07657 -0.0362 0.0173 1.0000 17.000 1.3668 0.08499 0.08023 -0.0373 0.0170 1.0000 17.250 1.3669 0.08871 0.08407 -0.0385 0.0168 1.0000 17.500 1.3663 0.09262 0.08810 -0.0399 0.0166 1.0000 17.750 1.3653 0.09665 0.09224 -0.0414 0.0164 1.0000 18.000 1.3637 0.10083 0.09652 -0.0431 0.0163 1.0000 18.250 1.3615 0.10515 0.10095 -0.0450 0.0161 1.0000 18.500 1.3595 0.10951 0.10541 -0.0470 0.0159 1.0000 18.750 1.3572 0.11393 0.10991 -0.0491 0.0158 1.0000 19.000 1.3540 0.11852 0.11460 -0.0514 0.0156 1.0000 19.250 1.3489 0.12347 0.11966 -0.0538 0.0154 1.0000