XFOIL Version 6.96 Calculated polar for: NACA 63-412 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -13.500 -0.8163 0.05641 0.05349 -0.0612 1.0000 0.0093 -13.250 -0.8408 0.04909 0.04595 -0.0664 1.0000 0.0093 -13.000 -0.8587 0.04361 0.04028 -0.0698 1.0000 0.0093 -12.750 -0.8743 0.03910 0.03556 -0.0717 1.0000 0.0094 -12.500 -0.8787 0.03634 0.03264 -0.0723 1.0000 0.0095 -12.250 -0.8858 0.03366 0.02979 -0.0720 1.0000 0.0097 -12.000 -0.8929 0.03159 0.02756 -0.0704 1.0000 0.0098 -11.750 -0.8958 0.02978 0.02557 -0.0684 1.0000 0.0100 -11.500 -0.8925 0.02801 0.02360 -0.0667 1.0000 0.0102 -11.250 -0.8851 0.02651 0.02191 -0.0651 1.0000 0.0104 -11.000 -0.8750 0.02522 0.02044 -0.0635 1.0000 0.0106 -10.750 -0.8602 0.02381 0.01890 -0.0629 0.9986 0.0109 -10.500 -0.8323 0.02274 0.01772 -0.0644 0.9920 0.0112 -10.250 -0.8024 0.02190 0.01680 -0.0661 0.9863 0.0116 -10.000 -0.7721 0.02119 0.01601 -0.0676 0.9802 0.0122 -9.750 -0.7407 0.02030 0.01500 -0.0694 0.9742 0.0128 -9.500 -0.7108 0.01935 0.01389 -0.0707 0.9661 0.0133 -9.250 -0.6795 0.01848 0.01284 -0.0722 0.9582 0.0138 -9.000 -0.6490 0.01743 0.01170 -0.0738 0.9492 0.0144 -8.750 -0.6192 0.01681 0.01102 -0.0748 0.9386 0.0150 -8.500 -0.5904 0.01625 0.01038 -0.0756 0.9280 0.0156 -8.250 -0.5631 0.01576 0.00979 -0.0759 0.9168 0.0163 -8.000 -0.5374 0.01528 0.00919 -0.0758 0.9050 0.0171 -7.750 -0.5121 0.01485 0.00864 -0.0756 0.8931 0.0177 -7.500 -0.4883 0.01417 0.00788 -0.0752 0.8813 0.0184 -7.250 -0.4632 0.01373 0.00736 -0.0750 0.8706 0.0192 -7.000 -0.4376 0.01337 0.00693 -0.0748 0.8602 0.0201 -6.750 -0.4116 0.01303 0.00652 -0.0747 0.8514 0.0211 -6.500 -0.3856 0.01269 0.00609 -0.0745 0.8424 0.0221 -6.250 -0.3593 0.01232 0.00563 -0.0744 0.8343 0.0229 -6.000 -0.3334 0.01187 0.00513 -0.0743 0.8261 0.0242 -5.750 -0.3066 0.01157 0.00479 -0.0743 0.8180 0.0257 -5.500 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0.2781 0.00718 0.00151 -0.0772 0.6663 0.6220 -0.250 0.3066 0.00720 0.00152 -0.0773 0.6589 0.6313 0.000 0.3350 0.00722 0.00154 -0.0774 0.6519 0.6398 0.250 0.3634 0.00725 0.00157 -0.0775 0.6444 0.6489 0.500 0.3917 0.00729 0.00160 -0.0775 0.6374 0.6579 0.750 0.4201 0.00732 0.00165 -0.0776 0.6296 0.6664 1.000 0.4484 0.00738 0.00169 -0.0777 0.6224 0.6755 1.250 0.4766 0.00742 0.00175 -0.0778 0.6143 0.6837 1.500 0.5048 0.00748 0.00181 -0.0778 0.6065 0.6923 1.750 0.5329 0.00753 0.00188 -0.0778 0.5979 0.7000 2.000 0.5611 0.00760 0.00195 -0.0779 0.5896 0.7083 2.250 0.5888 0.00767 0.00204 -0.0779 0.5802 0.7158 2.500 0.6167 0.00775 0.00212 -0.0779 0.5689 0.7240 2.750 0.6441 0.00784 0.00222 -0.0778 0.5555 0.7312 3.000 0.6714 0.00796 0.00233 -0.0777 0.5404 0.7393 3.250 0.6981 0.00809 0.00245 -0.0775 0.5221 0.7468 3.500 0.7246 0.00827 0.00257 -0.0772 0.5013 0.7550 3.750 0.7499 0.00851 0.00273 -0.0768 0.4658 0.7627 4.000 0.7744 0.00887 0.00292 -0.0763 0.4192 0.7711 4.250 0.7989 0.00922 0.00316 -0.0758 0.3816 0.7791 4.500 0.8219 0.00974 0.00347 -0.0752 0.3270 0.7877 4.750 0.8428 0.01047 0.00391 -0.0743 0.2584 0.7964 5.000 0.8639 0.01120 0.00437 -0.0734 0.1974 0.8053 5.250 0.8843 0.01198 0.00487 -0.0724 0.1377 0.8149 5.500 0.9050 0.01266 0.00536 -0.0715 0.0933 0.8244 5.750 0.9268 0.01324 0.00581 -0.0707 0.0653 0.8347 6.000 0.9495 0.01367 0.00622 -0.0700 0.0504 0.8455 6.250 0.9720 0.01407 0.00662 -0.0692 0.0411 0.8567 6.500 0.9942 0.01448 0.00705 -0.0683 0.0345 0.8688 6.750 1.0164 0.01483 0.00744 -0.0674 0.0307 0.8821 7.000 1.0368 0.01525 0.00789 -0.0662 0.0268 0.8975 7.250 1.0568 0.01555 0.00828 -0.0649 0.0246 0.9178 7.500 1.0781 0.01590 0.00871 -0.0638 0.0222 0.9809 7.750 1.1004 0.01643 0.00926 -0.0632 0.0204 1.0000 8.000 1.1226 0.01692 0.00979 -0.0626 0.0190 1.0000 8.250 1.1438 0.01746 0.01036 -0.0618 0.0178 1.0000 8.500 1.1635 0.01808 0.01100 -0.0608 0.0167 1.0000 8.750 1.1818 0.01877 0.01173 -0.0596 0.0159 1.0000 9.000 1.2002 0.01939 0.01242 -0.0584 0.0154 1.0000 9.250 1.2164 0.02005 0.01313 -0.0568 0.0149 1.0000 9.500 1.2308 0.02073 0.01387 -0.0550 0.0144 1.0000 9.750 1.2442 0.02147 0.01466 -0.0531 0.0140 1.0000 10.000 1.2570 0.02226 0.01551 -0.0512 0.0136 1.0000 10.250 1.2689 0.02312 0.01642 -0.0494 0.0132 1.0000 10.500 1.2790 0.02415 0.01750 -0.0475 0.0128 1.0000 10.750 1.2858 0.02545 0.01886 -0.0454 0.0124 1.0000 11.000 1.2965 0.02653 0.02003 -0.0439 0.0123 1.0000 11.250 1.3063 0.02774 0.02133 -0.0424 0.0121 1.0000 11.500 1.3153 0.02905 0.02273 -0.0409 0.0119 1.0000 11.750 1.3236 0.03048 0.02427 -0.0396 0.0117 1.0000 12.000 1.3317 0.03199 0.02587 -0.0383 0.0115 1.0000 12.250 1.3390 0.03361 0.02759 -0.0372 0.0114 1.0000 12.500 1.3462 0.03530 0.02938 -0.0362 0.0112 1.0000 12.750 1.3526 0.03711 0.03129 -0.0352 0.0110 1.0000 13.000 1.3591 0.03897 0.03324 -0.0345 0.0108 1.0000 13.250 1.3651 0.04091 0.03528 -0.0338 0.0106 1.0000 13.500 1.3709 0.04292 0.03737 -0.0333 0.0104 1.0000 13.750 1.3753 0.04514 0.03969 -0.0329 0.0102 1.0000 14.000 1.3791 0.04747 0.04213 -0.0327 0.0101 1.0000 14.250 1.3811 0.05009 0.04484 -0.0326 0.0099 1.0000 14.500 1.3816 0.05298 0.04783 -0.0326 0.0098 1.0000 14.750 1.3804 0.05617 0.05114 -0.0328 0.0097 1.0000 15.000 1.3768 0.05980 0.05489 -0.0331 0.0095 1.0000 15.250 1.3725 0.06367 0.05891 -0.0338 0.0094 1.0000 15.500 1.3704 0.06740 0.06278 -0.0347 0.0094 1.0000 15.750 1.3669 0.07146 0.06699 -0.0358 0.0093 1.0000 16.000 1.3626 0.07582 0.07151 -0.0373 0.0092 1.0000 16.250 1.3568 0.08057 0.07643 -0.0391 0.0092 1.0000 16.500 1.3492 0.08575 0.08177 -0.0412 0.0091 1.0000 16.750 1.3406 0.09132 0.08751 -0.0437 0.0090 1.0000 17.000 1.3309 0.09731 0.09367 -0.0466 0.0090 1.0000 17.250 1.3192 0.10390 0.10044 -0.0500 0.0089 1.0000 17.500 1.3064 0.11094 0.10764 -0.0538 0.0088 1.0000 17.750 1.2922 0.11855 0.11543 -0.0582 0.0088 1.0000 18.000 1.2762 0.12686 0.12391 -0.0632 0.0088 1.0000 18.250 1.2584 0.13587 0.13309 -0.0688 0.0088 1.0000 18.500 1.2377 0.14599 0.14340 -0.0752 0.0087 1.0000 18.750 1.2128 0.15775 0.15534 -0.0828 0.0088 1.0000