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 = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -0.9379 0.10794 0.10395 -0.0455 1.0000 0.0184 -19.500 -0.9454 0.10294 0.09887 -0.0481 1.0000 0.0185 -19.250 -0.9530 0.09800 0.09384 -0.0507 1.0000 0.0187 -19.000 -0.9596 0.09335 0.08910 -0.0531 1.0000 0.0188 -18.750 -0.9650 0.08894 0.08459 -0.0553 1.0000 0.0189 -18.500 -0.9700 0.08466 0.08022 -0.0574 1.0000 0.0191 -18.250 -0.9739 0.08059 0.07607 -0.0593 1.0000 0.0193 -18.000 -0.9772 0.07675 0.07213 -0.0611 1.0000 0.0195 -17.750 -0.9798 0.07306 0.06836 -0.0627 1.0000 0.0196 -17.500 -0.9811 0.06961 0.06483 -0.0642 1.0000 0.0198 -17.250 -0.9817 0.06632 0.06145 -0.0655 1.0000 0.0201 -17.000 -0.9809 0.06329 0.05832 -0.0667 1.0000 0.0203 -16.750 -0.9801 0.06030 0.05525 -0.0678 1.0000 0.0205 -16.500 -0.9805 0.05726 0.05216 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0.5953 0.5273 -1.250 0.1887 0.00871 0.00235 -0.0726 0.5909 0.5326 -1.000 0.2180 0.00873 0.00235 -0.0729 0.5865 0.5379 -0.750 0.2471 0.00877 0.00234 -0.0732 0.5821 0.5426 -0.500 0.2762 0.00877 0.00236 -0.0734 0.5778 0.5471 -0.250 0.3055 0.00878 0.00238 -0.0737 0.5731 0.5520 0.000 0.3347 0.00882 0.00239 -0.0740 0.5688 0.5570 0.250 0.3636 0.00887 0.00241 -0.0743 0.5647 0.5613 0.500 0.3927 0.00888 0.00245 -0.0745 0.5606 0.5657 0.750 0.4219 0.00891 0.00250 -0.0748 0.5560 0.5708 1.000 0.4509 0.00896 0.00254 -0.0751 0.5515 0.5757 1.250 0.4796 0.00902 0.00258 -0.0753 0.5474 0.5798 1.500 0.5086 0.00905 0.00265 -0.0755 0.5432 0.5844 1.750 0.5375 0.00909 0.00271 -0.0758 0.5386 0.5896 2.000 0.5663 0.00916 0.00277 -0.0760 0.5339 0.5946 2.250 0.5946 0.00924 0.00284 -0.0761 0.5292 0.5990 2.500 0.6235 0.00928 0.00294 -0.0764 0.5246 0.6037 2.750 0.6521 0.00934 0.00302 -0.0766 0.5194 0.6087 3.000 0.6804 0.00943 0.00310 -0.0767 0.5144 0.6139 3.250 0.7086 0.00951 0.00321 -0.0769 0.5097 0.6188 3.500 0.7370 0.00957 0.00332 -0.0770 0.5043 0.6239 3.750 0.7650 0.00966 0.00343 -0.0771 0.4987 0.6289 4.000 0.7928 0.00977 0.00354 -0.0772 0.4934 0.6336 4.250 0.8208 0.00984 0.00367 -0.0773 0.4868 0.6388 4.500 0.8477 0.00997 0.00380 -0.0772 0.4788 0.6444 4.750 0.8753 0.01008 0.00393 -0.0773 0.4706 0.6498 5.000 0.9020 0.01021 0.00408 -0.0772 0.4626 0.6545 5.250 0.9291 0.01032 0.00424 -0.0771 0.4542 0.6597 5.500 0.9547 0.01051 0.00440 -0.0768 0.4425 0.6654 5.750 0.9794 0.01072 0.00459 -0.0764 0.4252 0.6707 6.000 1.0033 0.01096 0.00481 -0.0759 0.4062 0.6761 6.250 1.0273 0.01122 0.00504 -0.0753 0.3902 0.6818 6.500 1.0504 0.01152 0.00530 -0.0747 0.3716 0.6871 6.750 1.0712 0.01190 0.00562 -0.0737 0.3482 0.6925 7.000 1.0890 0.01242 0.00603 -0.0723 0.3189 0.6985 7.250 1.1039 0.01306 0.00653 -0.0704 0.2868 0.7045 7.500 1.1160 0.01378 0.00711 -0.0681 0.2542 0.7099 7.750 1.1264 0.01445 0.00767 -0.0656 0.2271 0.7160 8.000 1.1329 0.01515 0.00826 -0.0623 0.2028 0.7225 8.250 1.1397 0.01590 0.00894 -0.0593 0.1816 0.7289 8.500 1.1461 0.01672 0.00971 -0.0564 0.1613 0.7359 8.750 1.1532 0.01759 0.01052 -0.0539 0.1445 0.7427 9.000 1.1600 0.01852 0.01142 -0.0515 0.1293 0.7497 9.250 1.1669 0.01952 0.01239 -0.0493 0.1154 0.7576 9.500 1.1738 0.02059 0.01344 -0.0472 0.1027 0.7652 9.750 1.1813 0.02168 0.01453 -0.0454 0.0924 0.7739 10.000 1.1888 0.02283 0.01569 -0.0437 0.0832 0.7823 10.250 1.1963 0.02403 0.01690 -0.0421 0.0755 0.7920 10.500 1.2036 0.02528 0.01819 -0.0405 0.0689 0.8018 10.750 1.2122 0.02650 0.01945 -0.0392 0.0634 0.8131 11.000 1.2191 0.02785 0.02084 -0.0378 0.0587 0.8254 11.250 1.2273 0.02911 0.02219 -0.0366 0.0549 0.8400 11.500 1.2331 0.03055 0.02369 -0.0352 0.0516 0.8585 11.750 1.2396 0.03181 0.02508 -0.0337 0.0490 0.8858 12.000 1.2497 0.03325 0.02664 -0.0333 0.0462 0.9449 12.500 1.2654 0.03650 0.02996 -0.0322 0.0414 1.0000 12.750 1.2724 0.03830 0.03178 -0.0317 0.0394 1.0000 13.000 1.2802 0.04009 0.03361 -0.0312 0.0377 1.0000 13.250 1.2879 0.04192 0.03549 -0.0309 0.0360 1.0000 13.500 1.2947 0.04389 0.03749 -0.0306 0.0345 1.0000 13.750 1.3006 0.04598 0.03961 -0.0304 0.0331 1.0000 14.000 1.3080 0.04799 0.04168 -0.0303 0.0319 1.0000 14.250 1.3145 0.05011 0.04384 -0.0302 0.0306 1.0000 14.500 1.3197 0.05243 0.04621 -0.0302 0.0296 1.0000 14.750 1.3242 0.05487 0.04869 -0.0303 0.0287 1.0000 15.000 1.3304 0.05717 0.05105 -0.0305 0.0279 1.0000 15.250 1.3356 0.05962 0.05358 -0.0307 0.0270 1.0000 15.500 1.3407 0.06215 0.05615 -0.0310 0.0261 1.0000 15.750 1.3441 0.06490 0.05896 -0.0314 0.0254 1.0000 16.000 1.3464 0.06784 0.06193 -0.0319 0.0247 1.0000 16.250 1.3505 0.07063 0.06481 -0.0324 0.0242 1.0000 16.500 1.3545 0.07346 0.06772 -0.0330 0.0236 1.0000 16.750 1.3575 0.07648 0.07081 -0.0337 0.0230 1.0000 17.000 1.3596 0.07963 0.07403 -0.0345 0.0225 1.0000 17.250 1.3617 0.08285 0.07731 -0.0354 0.0220 1.0000 17.500 1.3620 0.08640 0.08093 -0.0365 0.0215 1.0000 17.750 1.3612 0.09014 0.08473 -0.0377 0.0212 1.0000