XFOIL Version 6.96 Calculated polar for: NACA 65(4)-221 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -0.8809 0.10475 0.10116 -0.0601 1.0000 0.0271 -19.500 -0.9056 0.09736 0.09358 -0.0639 1.0000 0.0271 -19.250 -0.9271 0.09080 0.08682 -0.0670 1.0000 0.0271 -19.000 -0.9438 0.08525 0.08109 -0.0692 1.0000 0.0271 -18.750 -0.9573 0.08038 0.07605 -0.0710 1.0000 0.0272 -18.500 -0.9688 0.07591 0.07142 -0.0725 1.0000 0.0272 -18.250 -0.9770 0.07200 0.06734 -0.0735 1.0000 0.0273 -18.000 -0.9851 0.06832 0.06350 -0.0744 1.0000 0.0275 -17.750 -0.9886 0.06513 0.06016 -0.0749 1.0000 0.0275 -17.500 -0.9964 0.06195 0.05682 -0.0755 1.0000 0.0278 -17.250 -0.9996 0.05912 0.05384 -0.0758 1.0000 0.0279 -17.000 -1.0035 0.05649 0.05106 -0.0759 1.0000 0.0280 -16.750 -1.0019 0.05430 0.04874 -0.0758 1.0000 0.0281 -16.500 -0.9823 0.05262 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0.00498 -0.0321 0.6679 0.6234 -2.250 -0.0967 0.01074 0.00490 -0.0325 0.6654 0.6256 -2.000 -0.0676 0.01065 0.00481 -0.0330 0.6630 0.6277 -1.750 -0.0382 0.01061 0.00476 -0.0335 0.6607 0.6296 -1.500 -0.0088 0.01060 0.00473 -0.0340 0.6584 0.6316 -1.250 0.0206 0.01062 0.00471 -0.0346 0.6561 0.6338 -1.000 0.0500 0.01069 0.00474 -0.0351 0.6536 0.6361 -0.750 0.0788 0.01067 0.00473 -0.0356 0.6517 0.6384 -0.500 0.1077 0.01067 0.00472 -0.0361 0.6495 0.6405 -0.250 0.1367 0.01068 0.00471 -0.0366 0.6473 0.6424 0.000 0.1658 0.01064 0.00467 -0.0371 0.6451 0.6447 0.250 0.1950 0.01061 0.00466 -0.0376 0.6429 0.6469 0.500 0.2244 0.01062 0.00467 -0.0381 0.6407 0.6490 0.750 0.2539 0.01065 0.00470 -0.0387 0.6386 0.6511 1.000 0.2835 0.01076 0.00478 -0.0393 0.6365 0.6533 1.250 0.3122 0.01080 0.00485 -0.0397 0.6347 0.6556 1.500 0.3408 0.01083 0.00491 -0.0402 0.6327 0.6580 1.750 0.3695 0.01087 0.00497 -0.0406 0.6305 0.6603 2.000 0.3983 0.01088 0.00500 -0.0411 0.6281 0.6626 2.250 0.4272 0.01088 0.00503 -0.0415 0.6259 0.6651 2.500 0.4564 0.01091 0.00510 -0.0420 0.6240 0.6674 2.750 0.4858 0.01097 0.00517 -0.0426 0.6220 0.6697 3.000 0.5154 0.01105 0.00526 -0.0432 0.6199 0.6722 3.250 0.5444 0.01119 0.00542 -0.0437 0.6177 0.6748 3.500 0.5720 0.01123 0.00552 -0.0439 0.6154 0.6774 3.750 0.5999 0.01127 0.00559 -0.0442 0.6123 0.6798 4.000 0.6281 0.01123 0.00562 -0.0445 0.6091 0.6827 4.250 0.6570 0.01123 0.00566 -0.0449 0.6061 0.6854 4.500 0.6866 0.01123 0.00567 -0.0454 0.6025 0.6882 4.750 0.7127 0.01119 0.00569 -0.0452 0.5965 0.6911 5.000 0.7396 0.01104 0.00555 -0.0451 0.5892 0.6942 5.250 0.7689 0.01103 0.00549 -0.0455 0.5832 0.6971 5.500 0.7929 0.01095 0.00551 -0.0450 0.5765 0.6999 5.750 0.8186 0.01081 0.00539 -0.0447 0.5681 0.7030 6.000 0.8422 0.01077 0.00544 -0.0441 0.5590 0.7062 6.250 0.8669 0.01076 0.00544 -0.0436 0.5502 0.7097 6.500 0.8897 0.01078 0.00553 -0.0429 0.5395 0.7135 6.750 0.9120 0.01084 0.00560 -0.0421 0.5276 0.7170 7.000 0.9326 0.01091 0.00568 -0.0409 0.5145 0.7205 7.250 0.9504 0.01103 0.00584 -0.0393 0.4972 0.7242 7.500 0.9638 0.01125 0.00604 -0.0369 0.4730 0.7280 7.750 0.9628 0.01164 0.00633 -0.0319 0.4403 0.7325 8.000 0.9503 0.01255 0.00702 -0.0254 0.3990 0.7370 8.250 0.9363 0.01373 0.00805 -0.0194 0.3581 0.7420 8.500 0.9224 0.01519 0.00934 -0.0139 0.3190 0.7472 8.750 0.9104 0.01682 0.01079 -0.0092 0.2806 0.7528 9.000 0.8999 0.01857 0.01235 -0.0051 0.2430 0.7581 9.250 0.8921 0.02027 0.01394 -0.0016 0.2094 0.7636 9.500 0.8851 0.02209 0.01560 0.0016 0.1755 0.7693 9.750 0.8791 0.02398 0.01730 0.0044 0.1422 0.7751 10.000 0.8717 0.02596 0.01912 0.0072 0.1065 0.7809 10.250 0.8649 0.02803 0.02102 0.0098 0.0739 0.7871 10.500 0.8640 0.02988 0.02273 0.0116 0.0541 0.7937 10.750 0.8677 0.03143 0.02426 0.0132 0.0460 0.8000 11.000 0.8757 0.03274 0.02561 0.0143 0.0420 0.8072 11.250 0.8828 0.03420 0.02708 0.0154 0.0395 0.8144 11.500 0.8923 0.03543 0.02841 0.0163 0.0376 0.8217 11.750 0.9010 0.03680 0.02982 0.0172 0.0362 0.8299 12.000 0.9045 0.03856 0.03163 0.0184 0.0347 0.8377 12.250 0.9145 0.03986 0.03301 0.0191 0.0336 0.8469 12.500 0.9232 0.04125 0.03450 0.0199 0.0328 0.8562 12.750 0.9313 0.04273 0.03604 0.0207 0.0318 0.8671 13.000 0.9379 0.04423 0.03764 0.0217 0.0311 0.8796 13.250 0.9409 0.04606 0.03954 0.0228 0.0303 0.8946 13.500 0.9448 0.04779 0.04137 0.0238 0.0298 0.9147 13.750 0.9593 0.04938 0.04311 0.0231 0.0293 0.9446 14.000 0.9786 0.05125 0.04507 0.0207 0.0285 1.0000 14.250 0.9891 0.05295 0.04680 0.0206 0.0281 1.0000 14.500 0.9987 0.05473 0.04861 0.0206 0.0277 1.0000 14.750 1.0076 0.05657 0.05047 0.0205 0.0272 1.0000 15.000 1.0175 0.05833 0.05224 0.0204 0.0268 1.0000 15.250 1.0259 0.06018 0.05409 0.0204 0.0263 1.0000 15.500 1.0348 0.06194 0.05586 0.0205 0.0260 1.0000 15.750 1.0458 0.06339 0.05731 0.0208 0.0256 1.0000 16.000 1.0558 0.06525 0.05926 0.0206 0.0253 1.0000 16.250 1.0671 0.06690 0.06095 0.0204 0.0251 1.0000 16.500 1.0782 0.06857 0.06267 0.0203 0.0249 1.0000 16.750 1.0881 0.07041 0.06458 0.0200 0.0246 1.0000 17.000 1.0987 0.07216 0.06637 0.0198 0.0244 1.0000 17.250 1.1081 0.07409 0.06837 0.0195 0.0239 1.0000 17.500 1.1171 0.07610 0.07043 0.0191 0.0236 1.0000 17.750 1.1267 0.07802 0.07240 0.0187 0.0233 1.0000 18.000 1.1357 0.08003 0.07446 0.0183 0.0231 1.0000 18.250 1.1446 0.08205 0.07653 0.0179 0.0228 1.0000 18.500 1.1544 0.08395 0.07847 0.0175 0.0227 1.0000 18.750 1.1644 0.08582 0.08036 0.0171 0.0224 1.0000 19.000 1.1758 0.08750 0.08207 0.0168 0.0222 1.0000 19.250 1.1943 0.08826 0.08286 0.0172 0.0218 1.0000