XFOIL Version 6.96 Calculated polar for: NACA 65(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 -1.0200 0.07668 0.07262 -0.0773 1.0000 0.0180 -19.500 -1.0198 0.07359 0.06946 -0.0784 1.0000 0.0181 -19.250 -1.0169 0.07087 0.06668 -0.0794 1.0000 0.0182 -19.000 -1.0146 0.06813 0.06388 -0.0804 1.0000 0.0183 -18.750 -1.0118 0.06551 0.06119 -0.0812 1.0000 0.0185 -18.250 -0.9960 0.06018 0.05573 -0.0842 0.9666 0.0188 -18.000 -0.9690 0.05723 0.05268 -0.0900 0.9578 0.0189 -17.750 -0.9417 0.05433 0.04967 -0.0958 0.9501 0.0191 -17.500 -0.9078 0.05169 0.04693 -0.1024 0.9397 0.0193 -17.250 -0.8785 0.04923 0.04432 -0.1079 0.9222 0.0194 -17.000 -0.8595 0.04761 0.04254 -0.1100 0.8984 0.0196 -16.750 -0.8531 0.04582 0.04060 -0.1101 0.8785 0.0195 -16.500 -0.8454 0.04424 0.03892 -0.1100 0.8642 0.0197 -16.250 -0.8405 0.04253 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0.00200 -0.0709 0.5998 0.5704 -1.500 0.1563 0.00730 0.00199 -0.0714 0.5978 0.5721 -1.250 0.1856 0.00733 0.00199 -0.0719 0.5957 0.5737 -1.000 0.2152 0.00731 0.00199 -0.0724 0.5942 0.5759 -0.750 0.2448 0.00731 0.00199 -0.0730 0.5924 0.5779 -0.500 0.2743 0.00731 0.00200 -0.0735 0.5904 0.5797 -0.250 0.3038 0.00732 0.00201 -0.0740 0.5885 0.5817 0.000 0.3331 0.00734 0.00202 -0.0745 0.5866 0.5838 0.250 0.3624 0.00737 0.00204 -0.0750 0.5847 0.5860 0.500 0.3915 0.00740 0.00206 -0.0755 0.5828 0.5879 0.750 0.4204 0.00744 0.00209 -0.0759 0.5807 0.5895 1.000 0.4493 0.00750 0.00212 -0.0763 0.5785 0.5909 1.250 0.4788 0.00751 0.00215 -0.0769 0.5770 0.5926 1.500 0.5081 0.00751 0.00219 -0.0774 0.5755 0.5947 1.750 0.5373 0.00753 0.00224 -0.0779 0.5738 0.5969 2.000 0.5664 0.00756 0.00229 -0.0784 0.5719 0.5992 2.250 0.5953 0.00759 0.00234 -0.0788 0.5698 0.6014 2.500 0.6240 0.00763 0.00239 -0.0792 0.5677 0.6035 2.750 0.6526 0.00768 0.00245 -0.0796 0.5657 0.6055 3.000 0.6810 0.00774 0.00251 -0.0799 0.5637 0.6073 3.250 0.7091 0.00782 0.00258 -0.0802 0.5614 0.6090 3.500 0.7380 0.00784 0.00265 -0.0807 0.5591 0.6107 3.750 0.7665 0.00786 0.00271 -0.0810 0.5558 0.6131 4.000 0.7942 0.00791 0.00278 -0.0813 0.5516 0.6154 4.250 0.8209 0.00798 0.00286 -0.0813 0.5467 0.6179 4.500 0.8479 0.00803 0.00294 -0.0814 0.5397 0.6206 4.750 0.8721 0.00815 0.00302 -0.0809 0.5284 0.6231 5.000 0.8984 0.00823 0.00312 -0.0809 0.5193 0.6254 5.250 0.9225 0.00837 0.00323 -0.0804 0.5106 0.6274 5.500 0.9440 0.00855 0.00337 -0.0795 0.4928 0.6295 5.750 0.9613 0.00883 0.00358 -0.0778 0.4669 0.6322 6.000 0.9644 0.00936 0.00392 -0.0734 0.4258 0.6350 6.250 0.9585 0.01013 0.00448 -0.0676 0.3814 0.6378 6.500 0.9559 0.01096 0.00514 -0.0626 0.3443 0.6407 6.750 0.9524 0.01192 0.00593 -0.0578 0.3064 0.6435 7.000 0.9486 0.01299 0.00684 -0.0533 0.2702 0.6464 7.250 0.9476 0.01407 0.00778 -0.0495 0.2394 0.6493 7.500 0.9463 0.01524 0.00883 -0.0459 0.2094 0.6530 7.750 0.9459 0.01648 0.00995 -0.0426 0.1822 0.6565 8.000 0.9477 0.01771 0.01108 -0.0398 0.1573 0.6599 8.250 0.9494 0.01902 0.01228 -0.0371 0.1345 0.6631 8.500 0.9548 0.02020 0.01340 -0.0350 0.1166 0.6659 8.750 0.9568 0.02160 0.01472 -0.0326 0.0961 0.6695 9.000 0.9621 0.02288 0.01595 -0.0307 0.0804 0.6733 9.250 0.9675 0.02421 0.01722 -0.0289 0.0659 0.6772 9.500 0.9716 0.02566 0.01860 -0.0271 0.0498 0.6811 9.750 0.9772 0.02708 0.01997 -0.0255 0.0375 0.6847 10.000 0.9878 0.02821 0.02110 -0.0245 0.0323 0.6891 10.250 0.9984 0.02938 0.02229 -0.0234 0.0287 0.6935 10.500 1.0106 0.03045 0.02338 -0.0226 0.0266 0.6982 10.750 1.0232 0.03154 0.02449 -0.0219 0.0251 0.7023 11.000 1.0356 0.03266 0.02564 -0.0211 0.0237 0.7061 11.250 1.0473 0.03383 0.02684 -0.0204 0.0223 0.7108 11.500 1.0600 0.03497 0.02802 -0.0198 0.0214 0.7157 11.750 1.0725 0.03614 0.02922 -0.0192 0.0204 0.7205 12.250 1.0959 0.03865 0.03181 -0.0180 0.0190 0.7306 12.500 1.1085 0.03987 0.03307 -0.0175 0.0184 0.7364 12.750 1.1213 0.04109 0.03433 -0.0171 0.0177 0.7421 13.000 1.1324 0.04246 0.03575 -0.0167 0.0172 0.7473 13.250 1.1440 0.04381 0.03715 -0.0163 0.0168 0.7533 13.500 1.1551 0.04522 0.03859 -0.0159 0.0162 0.7591 13.750 1.1651 0.04678 0.04020 -0.0155 0.0159 0.7645 14.000 1.1765 0.04820 0.04169 -0.0152 0.0156 0.7709 14.250 1.1880 0.04963 0.04318 -0.0149 0.0152 0.7782 14.500 1.1983 0.05121 0.04482 -0.0147 0.0148 0.7851 14.750 1.2087 0.05277 0.04645 -0.0145 0.0147 0.7930 15.000 1.2193 0.05436 0.04809 -0.0143 0.0144 0.8006 15.250 1.2282 0.05612 0.04992 -0.0141 0.0141 0.8085 15.500 1.2373 0.05789 0.05175 -0.0140 0.0140 0.8166 15.750 1.2465 0.05965 0.05357 -0.0139 0.0137 0.8245 16.000 1.2534 0.06169 0.05568 -0.0138 0.0135 0.8333 16.250 1.2605 0.06373 0.05779 -0.0138 0.0132 0.8419 16.500 1.2685 0.06567 0.05981 -0.0138 0.0131 0.8525 16.750 1.2751 0.06777 0.06201 -0.0138 0.0129 0.8649 17.000 1.2822 0.06976 0.06410 -0.0137 0.0129 0.8805 17.250 1.2878 0.07181 0.06628 -0.0135 0.0127 0.9038 17.500 1.2935 0.07398 0.06860 -0.0135 0.0126 0.9462 17.750 1.3037 0.07633 0.07104 -0.0148 0.0124 1.0000 18.000 1.3084 0.07896 0.07372 -0.0153 0.0123 1.0000 18.250 1.3149 0.08136 0.07618 -0.0158 0.0122 1.0000 18.500 1.3188 0.08414 0.07902 -0.0164 0.0120 1.0000 18.750 1.3242 0.08675 0.08168 -0.0171 0.0119 1.0000 19.000 1.3279 0.08958 0.08457 -0.0178 0.0118 1.0000 19.250 1.3323 0.09238 0.08741 -0.0186 0.0116 1.0000