XFOIL Version 6.96 Calculated polar for: NACA 64(3)-218 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.250 -0.8115 0.12114 0.11664 -0.0286 1.0000 0.0262 -18.000 -0.8635 0.10626 0.10140 -0.0378 1.0000 0.0260 -17.750 -0.8871 0.09795 0.09287 -0.0427 1.0000 0.0261 -17.500 -0.9041 0.09128 0.08600 -0.0464 1.0000 0.0263 -17.250 -0.9172 0.08555 0.08008 -0.0494 1.0000 0.0264 -17.000 -0.9274 0.08052 0.07487 -0.0518 1.0000 0.0266 -16.750 -0.9348 0.07607 0.07025 -0.0537 1.0000 0.0268 -16.500 -0.9405 0.07201 0.06602 -0.0553 1.0000 0.0270 -16.250 -0.9441 0.06835 0.06218 -0.0566 1.0000 0.0273 -16.000 -0.9457 0.06503 0.05870 -0.0576 1.0000 0.0276 -15.750 -0.9464 0.06192 0.05541 -0.0585 1.0000 0.0280 -15.500 -0.9451 0.05911 0.05243 -0.0591 1.0000 0.0283 -15.250 -0.9415 0.05662 0.04978 -0.0595 1.0000 0.0286 -15.000 -0.9344 0.05457 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0.7256 0.4565 -5.250 -0.4308 0.01310 0.00606 -0.0335 0.7193 0.4796 -5.000 -0.4043 0.01309 0.00598 -0.0332 0.7139 0.4977 -4.750 -0.3772 0.01308 0.00592 -0.0331 0.7083 0.5119 -4.500 -0.3499 0.01307 0.00581 -0.0331 0.7020 0.5243 -4.250 -0.3225 0.01310 0.00581 -0.0329 0.6965 0.5356 -4.000 -0.2952 0.01319 0.00586 -0.0327 0.6911 0.5490 -3.750 -0.2677 0.01325 0.00587 -0.0327 0.6851 0.5612 -3.500 -0.2397 0.01327 0.00586 -0.0326 0.6799 0.5676 -3.250 -0.2115 0.01323 0.00569 -0.0328 0.6756 0.5720 -3.000 -0.1832 0.01316 0.00553 -0.0331 0.6702 0.5763 -2.750 -0.1549 0.01310 0.00546 -0.0332 0.6651 0.5794 -2.500 -0.1265 0.01308 0.00538 -0.0333 0.6607 0.5830 -2.250 -0.0981 0.01306 0.00529 -0.0335 0.6567 0.5871 -2.000 -0.0696 0.01302 0.00521 -0.0338 0.6518 0.5908 -1.750 -0.0410 0.01298 0.00509 -0.0341 0.6472 0.5945 -1.500 -0.0126 0.01294 0.00504 -0.0342 0.6431 0.5972 -1.250 0.0159 0.01293 0.00498 -0.0344 0.6393 0.6000 -1.000 0.0444 0.01291 0.00497 -0.0346 0.6345 0.6030 -0.750 0.0729 0.01290 0.00494 -0.0349 0.6301 0.6064 -0.500 0.1016 0.01290 0.00488 -0.0352 0.6264 0.6103 -0.250 0.1303 0.01291 0.00484 -0.0354 0.6233 0.6139 0.000 0.1587 0.01292 0.00489 -0.0356 0.6198 0.6170 0.250 0.1870 0.01294 0.00494 -0.0358 0.6159 0.6204 0.500 0.2155 0.01297 0.00497 -0.0361 0.6123 0.6242 0.750 0.2443 0.01300 0.00499 -0.0364 0.6091 0.6283 1.000 0.2730 0.01304 0.00500 -0.0366 0.6062 0.6321 1.250 0.3013 0.01308 0.00508 -0.0368 0.6030 0.6354 1.500 0.3294 0.01314 0.00520 -0.0370 0.5992 0.6394 1.750 0.3578 0.01320 0.00530 -0.0372 0.5959 0.6439 2.000 0.3864 0.01327 0.00537 -0.0375 0.5929 0.6491 2.250 0.4146 0.01333 0.00549 -0.0376 0.5902 0.6530 2.500 0.4431 0.01341 0.00559 -0.0378 0.5875 0.6577 2.750 0.4711 0.01351 0.00575 -0.0380 0.5842 0.6628 3.000 0.4991 0.01360 0.00590 -0.0382 0.5802 0.6680 3.250 0.5266 0.01367 0.00606 -0.0382 0.5761 0.6722 3.500 0.5546 0.01375 0.00619 -0.0383 0.5726 0.6772 3.750 0.5834 0.01385 0.00629 -0.0386 0.5697 0.6829 4.000 0.6106 0.01396 0.00652 -0.0386 0.5658 0.6881 4.250 0.6374 0.01407 0.00676 -0.0386 0.5617 0.6932 4.500 0.6649 0.01415 0.00690 -0.0386 0.5568 0.6992 4.750 0.6925 0.01418 0.00693 -0.0385 0.5499 0.7055 5.000 0.7174 0.01416 0.00703 -0.0380 0.5391 0.7111 5.250 0.7430 0.01417 0.00710 -0.0376 0.5283 0.7178 5.500 0.7692 0.01420 0.00714 -0.0373 0.5184 0.7245 5.750 0.7937 0.01427 0.00735 -0.0367 0.5080 0.7304 6.000 0.8187 0.01434 0.00746 -0.0363 0.4966 0.7372 6.250 0.8424 0.01441 0.00758 -0.0356 0.4813 0.7438 6.500 0.8646 0.01452 0.00776 -0.0346 0.4627 0.7502 6.750 0.8861 0.01469 0.00795 -0.0337 0.4382 0.7578 7.000 0.9043 0.01494 0.00817 -0.0321 0.3998 0.7648 7.250 0.9125 0.01558 0.00852 -0.0291 0.3449 0.7730 7.500 0.9155 0.01651 0.00919 -0.0256 0.2940 0.7814 7.750 0.9139 0.01747 0.00997 -0.0214 0.2519 0.7904 8.000 0.9112 0.01844 0.01082 -0.0172 0.2191 0.8000 8.500 0.9111 0.02069 0.01290 -0.0106 0.1650 0.8211 8.750 0.9127 0.02190 0.01405 -0.0080 0.1436 0.8333 9.000 0.9161 0.02306 0.01519 -0.0057 0.1261 0.8458 9.250 0.9201 0.02428 0.01640 -0.0035 0.1110 0.8599 9.500 0.9245 0.02551 0.01763 -0.0016 0.0984 0.8763 9.750 0.9292 0.02676 0.01891 0.0003 0.0876 0.8969 10.000 0.9362 0.02804 0.02023 0.0015 0.0786 0.9269 10.250 0.9480 0.02940 0.02160 0.0014 0.0701 1.0000 10.500 0.9580 0.03082 0.02302 0.0019 0.0637 1.0000 10.750 0.9667 0.03235 0.02454 0.0024 0.0587 1.0000 11.000 0.9754 0.03390 0.02609 0.0029 0.0545 1.0000 11.250 0.9839 0.03548 0.02769 0.0033 0.0511 1.0000 11.500 0.9926 0.03708 0.02930 0.0037 0.0479 1.0000 11.750 0.9997 0.03883 0.03105 0.0042 0.0456 1.0000 12.000 1.0086 0.04046 0.03275 0.0045 0.0434 1.0000 12.250 1.0167 0.04221 0.03452 0.0047 0.0412 1.0000 12.500 1.0225 0.04420 0.03651 0.0050 0.0399 1.0000 12.750 1.0315 0.04593 0.03833 0.0052 0.0382 1.0000 13.000 1.0393 0.04781 0.04026 0.0053 0.0367 1.0000 13.250 1.0464 0.04981 0.04229 0.0053 0.0355 1.0000 13.500 1.0518 0.05199 0.04449 0.0053 0.0344 1.0000 13.750 1.0599 0.05395 0.04653 0.0053 0.0333 1.0000 14.000 1.0674 0.05602 0.04867 0.0052 0.0321 1.0000 14.250 1.0746 0.05815 0.05085 0.0050 0.0311 1.0000 14.500 1.0804 0.06047 0.05321 0.0048 0.0303 1.0000 14.750 1.0857 0.06285 0.05562 0.0045 0.0296 1.0000 15.000 1.0929 0.06509 0.05796 0.0042 0.0289 1.0000 15.250 1.0995 0.06742 0.06038 0.0039 0.0281 1.0000 15.500 1.1057 0.06983 0.06287 0.0035 0.0275 1.0000 15.750 1.1113 0.07234 0.06545 0.0030 0.0269 1.0000 16.000 1.1167 0.07492 0.06808 0.0024 0.0264 1.0000 16.250 1.1216 0.07758 0.07080 0.0018 0.0260 1.0000 16.500 1.1266 0.08023 0.07347 0.0012 0.0256 1.0000 16.750 1.1313 0.08303 0.07639 0.0004 0.0251 1.0000 17.000 1.1356 0.08593 0.07943 -0.0004 0.0247 1.0000 17.250 1.1386 0.08905 0.08268 -0.0013 0.0243 1.0000 17.500 1.1411 0.09229 0.08605 -0.0024 0.0239 1.0000 17.750 1.1426 0.09574 0.08961 -0.0037 0.0235 1.0000 18.000 1.1435 0.09933 0.09332 -0.0052 0.0231 1.0000 18.250 1.1438 0.10303 0.09713 -0.0068 0.0228 1.0000 18.500 1.1441 0.10680 0.10099 -0.0085 0.0225 1.0000 18.750 1.1444 0.11058 0.10485 -0.0103 0.0222 1.0000 19.000 1.1450 0.11432 0.10866 -0.0122 0.0220 1.0000 19.250 1.1459 0.11801 0.11240 -0.0140 0.0217 1.0000