XFOIL Version 6.96 Calculated polar for: NACA 63(4)-421 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.1077 0.07928 0.07494 -0.0576 1.0000 0.0200 -19.500 -1.1075 0.07622 0.07184 -0.0588 1.0000 0.0207 -19.250 -1.1073 0.07315 0.06872 -0.0599 1.0000 0.0213 -19.000 -1.1049 0.07043 0.06595 -0.0609 1.0000 0.0217 -18.750 -1.1029 0.06767 0.06313 -0.0618 1.0000 0.0223 -18.500 -1.1001 0.06505 0.06047 -0.0627 1.0000 0.0228 -18.250 -1.0980 0.06234 0.05773 -0.0635 1.0000 0.0234 -18.000 -1.0933 0.06002 0.05537 -0.0642 1.0000 0.0241 -17.750 -1.0893 0.05760 0.05290 -0.0649 1.0000 0.0246 -17.500 -1.0824 0.05555 0.05082 -0.0654 1.0000 0.0254 -17.250 -1.0764 0.05339 0.04860 -0.0660 1.0000 0.0258 -17.000 -1.0709 0.05124 0.04642 -0.0665 1.0000 0.0262 -16.500 -1.0409 0.04672 0.04183 -0.0709 0.9567 0.0276 -16.250 -0.9936 0.04418 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-0.0711 0.5351 0.4745 -1.250 0.1926 0.00761 0.00194 -0.0715 0.5314 0.4790 -0.750 0.2523 0.00766 0.00195 -0.0724 0.5249 0.4866 -0.500 0.2823 0.00765 0.00196 -0.0729 0.5214 0.4911 -0.250 0.3121 0.00766 0.00197 -0.0733 0.5174 0.4957 0.000 0.3417 0.00769 0.00200 -0.0737 0.5134 0.4998 0.250 0.3712 0.00774 0.00202 -0.0741 0.5097 0.5032 0.750 0.4310 0.00777 0.00208 -0.0750 0.5038 0.5104 1.000 0.4607 0.00780 0.00211 -0.0754 0.5003 0.5141 1.250 0.4902 0.00784 0.00215 -0.0758 0.4963 0.5177 1.500 0.5192 0.00791 0.00220 -0.0761 0.4914 0.5212 1.750 0.5488 0.00795 0.00225 -0.0765 0.4874 0.5243 2.000 0.5783 0.00799 0.00230 -0.0769 0.4822 0.5282 2.250 0.6073 0.00805 0.00236 -0.0772 0.4772 0.5325 2.500 0.6360 0.00813 0.00243 -0.0775 0.4727 0.5366 2.750 0.6655 0.00817 0.00249 -0.0779 0.4691 0.5404 3.000 0.6947 0.00823 0.00256 -0.0782 0.4648 0.5436 3.250 0.7234 0.00830 0.00264 -0.0785 0.4602 0.5472 3.500 0.7517 0.00839 0.00273 -0.0787 0.4555 0.5513 3.750 0.7808 0.00845 0.00282 -0.0791 0.4519 0.5554 4.000 0.8095 0.00852 0.00291 -0.0793 0.4475 0.5594 4.250 0.8378 0.00862 0.00301 -0.0795 0.4428 0.5632 4.500 0.8653 0.00874 0.00312 -0.0796 0.4367 0.5675 4.750 0.8933 0.00884 0.00324 -0.0798 0.4293 0.5723 5.000 0.9199 0.00900 0.00338 -0.0797 0.4211 0.5767 5.250 0.9477 0.00910 0.00350 -0.0799 0.4163 0.5807 5.500 0.9753 0.00922 0.00363 -0.0800 0.4109 0.5841 5.750 1.0018 0.00937 0.00378 -0.0799 0.4048 0.5885 6.000 1.0286 0.00950 0.00394 -0.0799 0.3990 0.5930 6.250 1.0551 0.00964 0.00409 -0.0798 0.3912 0.5975 6.500 1.0801 0.00985 0.00428 -0.0795 0.3824 0.6019 6.750 1.1040 0.01008 0.00449 -0.0790 0.3685 0.6062 7.000 1.1259 0.01039 0.00474 -0.0782 0.3500 0.6113 7.250 1.1429 0.01087 0.00511 -0.0767 0.3222 0.6162 7.500 1.1569 0.01143 0.00554 -0.0747 0.2976 0.6205 7.750 1.1677 0.01197 0.00598 -0.0720 0.2749 0.6242 8.000 1.1722 0.01258 0.00650 -0.0683 0.2526 0.6290 8.250 1.1777 0.01326 0.00711 -0.0650 0.2333 0.6344 8.500 1.1840 0.01398 0.00777 -0.0621 0.2156 0.6397 8.750 1.1901 0.01478 0.00851 -0.0593 0.1996 0.6443 9.000 1.1962 0.01565 0.00933 -0.0568 0.1848 0.6494 9.250 1.2021 0.01661 0.01026 -0.0544 0.1711 0.6549 9.500 1.2091 0.01759 0.01121 -0.0523 0.1591 0.6604 10.000 1.2240 0.01969 0.01329 -0.0486 0.1388 0.6715 10.250 1.2298 0.02092 0.01449 -0.0468 0.1288 0.6774 10.500 1.2337 0.02232 0.01586 -0.0450 0.1174 0.6829 10.750 1.2406 0.02361 0.01715 -0.0435 0.1089 0.6884 11.000 1.2470 0.02496 0.01851 -0.0421 0.1013 0.6948 11.250 1.2526 0.02642 0.01997 -0.0408 0.0940 0.7012 11.750 1.2633 0.02954 0.02309 -0.0384 0.0802 0.7128 12.000 1.2684 0.03118 0.02475 -0.0373 0.0744 0.7195 12.250 1.2729 0.03295 0.02652 -0.0363 0.0684 0.7255 12.500 1.2784 0.03469 0.02829 -0.0355 0.0633 0.7323 12.750 1.2843 0.03645 0.03008 -0.0348 0.0588 0.7394 13.000 1.2892 0.03837 0.03201 -0.0341 0.0547 0.7456 13.250 1.2951 0.04024 0.03392 -0.0336 0.0507 0.7520 13.500 1.3011 0.04214 0.03585 -0.0331 0.0475 0.7597 14.000 1.3130 0.04609 0.03989 -0.0324 0.0420 0.7752 14.250 1.3175 0.04830 0.04214 -0.0322 0.0392 0.7835 14.500 1.3245 0.05027 0.04416 -0.0320 0.0374 0.7919 14.750 1.3292 0.05252 0.04647 -0.0319 0.0353 0.8013 15.000 1.3350 0.05468 0.04869 -0.0318 0.0336 0.8114 15.250 1.3406 0.05694 0.05101 -0.0319 0.0321 0.8233 15.500 1.3463 0.05914 0.05329 -0.0319 0.0309 0.8364 15.750 1.3510 0.06149 0.05572 -0.0320 0.0300 0.8511 16.000 1.3563 0.06370 0.05805 -0.0319 0.0291 0.8734 16.250 1.3624 0.06576 0.06033 -0.0320 0.0284 0.9577 16.750 1.3718 0.07084 0.06549 -0.0328 0.0268 1.0000 17.000 1.3754 0.07365 0.06834 -0.0334 0.0260 1.0000 17.250 1.3817 0.07613 0.07087 -0.0339 0.0256 1.0000 17.500 1.3865 0.07886 0.07365 -0.0346 0.0251 1.0000 17.750 1.3911 0.08163 0.07647 -0.0353 0.0245 1.0000 18.000 1.3954 0.08445 0.07932 -0.0361 0.0240 1.0000 18.250 1.3980 0.08755 0.08247 -0.0370 0.0234 1.0000 18.500 1.4017 0.09050 0.08546 -0.0379 0.0229 1.0000