XFOIL Version 6.96 Calculated polar for: NACA 64(3)-418 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 -1.0946 0.08244 0.07873 -0.0603 1.0000 0.0150 -19.500 -1.1024 0.07794 0.07414 -0.0624 1.0000 0.0151 -19.250 -1.1059 0.07415 0.07028 -0.0641 1.0000 0.0152 -19.000 -1.1076 0.07065 0.06670 -0.0656 1.0000 0.0154 -18.750 -1.1118 0.06692 0.06289 -0.0671 1.0000 0.0155 -18.500 -1.1118 0.06380 0.05969 -0.0684 1.0000 0.0156 -18.250 -1.1121 0.06071 0.05653 -0.0695 1.0000 0.0158 -18.000 -1.1113 0.05780 0.05355 -0.0706 1.0000 0.0159 -17.750 -1.1098 0.05505 0.05072 -0.0715 1.0000 0.0160 -17.500 -1.1068 0.05252 0.04813 -0.0722 1.0000 0.0162 -17.250 -1.1025 0.05019 0.04572 -0.0729 1.0000 0.0163 -17.000 -1.0982 0.04789 0.04336 -0.0734 1.0000 0.0165 -16.750 -1.0936 0.04568 0.04108 -0.0739 1.0000 0.0166 -16.500 -1.0874 0.04369 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0.5683 2.750 0.6616 0.00759 0.00211 -0.0798 0.5094 0.5720 3.000 0.6908 0.00762 0.00218 -0.0802 0.5069 0.5758 3.250 0.7197 0.00766 0.00225 -0.0805 0.5035 0.5803 3.500 0.7479 0.00774 0.00233 -0.0806 0.4970 0.5849 3.750 0.7762 0.00781 0.00241 -0.0808 0.4896 0.5892 4.250 0.8318 0.00800 0.00260 -0.0810 0.4713 0.5974 4.500 0.8593 0.00811 0.00270 -0.0811 0.4622 0.6023 4.750 0.8871 0.00820 0.00281 -0.0812 0.4539 0.6071 5.000 0.9136 0.00837 0.00294 -0.0811 0.4379 0.6113 5.250 0.9366 0.00871 0.00315 -0.0805 0.3982 0.6162 5.500 0.9527 0.00948 0.00361 -0.0787 0.3363 0.6215 5.750 0.9711 0.01009 0.00403 -0.0774 0.2947 0.6266 6.000 0.9880 0.01075 0.00448 -0.0758 0.2513 0.6312 6.250 1.0045 0.01137 0.00494 -0.0742 0.2151 0.6368 6.500 1.0216 0.01191 0.00536 -0.0726 0.1864 0.6426 6.750 1.0382 0.01243 0.00578 -0.0710 0.1620 0.6479 7.000 1.0521 0.01298 0.00623 -0.0689 0.1385 0.6536 7.250 1.0620 0.01349 0.00666 -0.0660 0.1184 0.6599 7.500 1.0709 0.01409 0.00718 -0.0630 0.1011 0.6664 7.750 1.0800 0.01472 0.00777 -0.0603 0.0849 0.6732 8.000 1.0900 0.01536 0.00837 -0.0578 0.0724 0.6804 8.500 1.1130 0.01666 0.00964 -0.0537 0.0560 0.6939 8.750 1.1248 0.01736 0.01034 -0.0519 0.0499 0.7011 9.000 1.1365 0.01810 0.01109 -0.0502 0.0447 0.7077 9.500 1.1608 0.01966 0.01269 -0.0471 0.0368 0.7227 9.750 1.1723 0.02053 0.01359 -0.0456 0.0337 0.7300 10.000 1.1847 0.02139 0.01448 -0.0443 0.0314 0.7382 10.250 1.1965 0.02232 0.01544 -0.0430 0.0294 0.7457 10.500 1.2085 0.02326 0.01643 -0.0418 0.0277 0.7544 10.750 1.2194 0.02431 0.01752 -0.0405 0.0261 0.7629 11.000 1.2314 0.02530 0.01857 -0.0395 0.0250 0.7732 11.250 1.2426 0.02638 0.01970 -0.0384 0.0237 0.7827 11.500 1.2530 0.02754 0.02091 -0.0373 0.0227 0.7927 11.750 1.2635 0.02872 0.02216 -0.0363 0.0218 0.8034 12.000 1.2742 0.02991 0.02342 -0.0354 0.0209 0.8157 12.250 1.2839 0.03116 0.02475 -0.0344 0.0199 0.8309 12.500 1.2927 0.03249 0.02616 -0.0334 0.0191 0.8495 12.750 1.3011 0.03384 0.02761 -0.0324 0.0183 0.8712 13.000 1.3097 0.03514 0.02901 -0.0313 0.0177 0.8949 13.250 1.3167 0.03648 0.03049 -0.0301 0.0170 0.9368 13.750 1.3376 0.03974 0.03384 -0.0300 0.0156 1.0000 14.000 1.3475 0.04135 0.03549 -0.0296 0.0150 1.0000 14.250 1.3563 0.04308 0.03726 -0.0293 0.0145 1.0000 14.500 1.3647 0.04488 0.03909 -0.0290 0.0140 1.0000 14.750 1.3729 0.04673 0.04098 -0.0288 0.0137 1.0000 15.000 1.3802 0.04872 0.04300 -0.0287 0.0133 1.0000 15.250 1.3876 0.05073 0.04506 -0.0285 0.0128 1.0000 15.500 1.3952 0.05274 0.04712 -0.0285 0.0125 1.0000 15.750 1.4026 0.05482 0.04924 -0.0285 0.0123 1.0000 16.000 1.4094 0.05699 0.05147 -0.0286 0.0120 1.0000 16.250 1.4156 0.05927 0.05379 -0.0287 0.0117 1.0000 16.500 1.4216 0.06161 0.05618 -0.0289 0.0115 1.0000 16.750 1.4269 0.06406 0.05868 -0.0292 0.0113 1.0000 17.000 1.4316 0.06661 0.06128 -0.0296 0.0111 1.0000 17.250 1.4352 0.06936 0.06409 -0.0300 0.0109 1.0000 17.500 1.4381 0.07225 0.06704 -0.0305 0.0107 1.0000 17.750 1.4422 0.07502 0.06987 -0.0311 0.0106 1.0000 18.000 1.4455 0.07792 0.07284 -0.0317 0.0105 1.0000 18.250 1.4489 0.08087 0.07585 -0.0325 0.0104 1.0000 18.500 1.4512 0.08402 0.07908 -0.0333 0.0103 1.0000 18.750 1.4536 0.08719 0.08232 -0.0342 0.0102 1.0000 19.000 1.4544 0.09062 0.08583 -0.0353 0.0101 1.0000 19.250 1.4557 0.09399 0.08927 -0.0364 0.0099 1.0000