XFOIL Version 6.96 Calculated polar for: NACA 63(4)-421 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -0.9716 0.09449 0.08982 -0.0554 1.0000 0.0267 -19.500 -0.9732 0.09092 0.08619 -0.0570 1.0000 0.0273 -19.250 -0.9729 0.08765 0.08285 -0.0584 1.0000 0.0278 -19.000 -0.9730 0.08437 0.07951 -0.0598 1.0000 0.0283 -18.750 -0.9704 0.08150 0.07656 -0.0609 1.0000 0.0290 -18.500 -0.9686 0.07855 0.07353 -0.0620 1.0000 0.0295 -18.250 -0.9681 0.07549 0.07042 -0.0632 1.0000 0.0300 -18.000 -0.9675 0.07245 0.06734 -0.0643 1.0000 0.0305 -17.750 -0.9651 0.06970 0.06456 -0.0653 1.0000 0.0311 -17.500 -0.9623 0.06703 0.06183 -0.0662 1.0000 0.0316 -17.250 -0.9577 0.06462 0.05936 -0.0669 1.0000 0.0323 -17.000 -0.9529 0.06224 0.05693 -0.0676 1.0000 0.0329 -16.750 -0.9459 0.06016 0.05478 -0.0682 1.0000 0.0336 -16.500 -0.9435 0.05761 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-0.0700 0.5565 0.5117 -0.750 0.2427 0.00952 0.00290 -0.0704 0.5527 0.5160 -0.500 0.2720 0.00955 0.00290 -0.0707 0.5491 0.5199 -0.250 0.3012 0.00960 0.00291 -0.0711 0.5456 0.5236 0.000 0.3309 0.00961 0.00293 -0.0715 0.5423 0.5272 0.250 0.3603 0.00962 0.00297 -0.0719 0.5384 0.5309 0.500 0.3895 0.00965 0.00300 -0.0722 0.5343 0.5346 0.750 0.4185 0.00970 0.00303 -0.0725 0.5304 0.5383 1.000 0.4475 0.00977 0.00307 -0.0728 0.5271 0.5420 1.250 0.4770 0.00980 0.00312 -0.0732 0.5239 0.5457 1.500 0.5061 0.00982 0.00319 -0.0735 0.5203 0.5497 1.750 0.5351 0.00987 0.00326 -0.0738 0.5165 0.5538 2.000 0.5638 0.00994 0.00332 -0.0741 0.5125 0.5578 2.250 0.5923 0.01003 0.00338 -0.0743 0.5086 0.5616 2.500 0.6214 0.01007 0.00346 -0.0747 0.5044 0.5651 2.750 0.6499 0.01012 0.00355 -0.0749 0.4995 0.5690 3.000 0.6782 0.01020 0.00364 -0.0751 0.4951 0.5731 3.250 0.7061 0.01031 0.00373 -0.0752 0.4910 0.5776 3.500 0.7349 0.01037 0.00383 -0.0755 0.4873 0.5820 3.750 0.7633 0.01044 0.00394 -0.0757 0.4830 0.5861 4.000 0.7911 0.01053 0.00406 -0.0759 0.4787 0.5904 4.250 0.8186 0.01064 0.00418 -0.0759 0.4745 0.5948 4.500 0.8464 0.01074 0.00431 -0.0761 0.4707 0.5992 4.750 0.8744 0.01084 0.00444 -0.0762 0.4663 0.6032 5.000 0.9016 0.01094 0.00459 -0.0763 0.4617 0.6073 5.250 0.9278 0.01108 0.00473 -0.0761 0.4562 0.6119 5.500 0.9544 0.01119 0.00489 -0.0761 0.4492 0.6170 5.750 0.9797 0.01135 0.00505 -0.0758 0.4411 0.6219 6.000 1.0052 0.01151 0.00522 -0.0756 0.4354 0.6264 6.250 1.0312 0.01164 0.00542 -0.0754 0.4297 0.6310 6.500 1.0555 0.01182 0.00562 -0.0750 0.4233 0.6358 6.750 1.0798 0.01201 0.00583 -0.0746 0.4172 0.6408 7.000 1.1038 0.01220 0.00604 -0.0741 0.4097 0.6456 7.250 1.1249 0.01245 0.00631 -0.0732 0.4017 0.6508 7.500 1.1476 0.01264 0.00655 -0.0725 0.3926 0.6563 7.750 1.1664 0.01294 0.00684 -0.0712 0.3821 0.6615 8.000 1.1806 0.01326 0.00715 -0.0691 0.3680 0.6663 8.250 1.1897 0.01370 0.00756 -0.0662 0.3487 0.6717 8.500 1.1928 0.01442 0.00820 -0.0626 0.3242 0.6777 8.750 1.1943 0.01532 0.00901 -0.0591 0.3028 0.6835 9.000 1.1957 0.01634 0.00996 -0.0559 0.2835 0.6887 9.250 1.2005 0.01733 0.01092 -0.0534 0.2671 0.6945 9.500 1.2050 0.01842 0.01198 -0.0510 0.2513 0.7009 9.750 1.2078 0.01969 0.01319 -0.0487 0.2346 0.7069 10.000 1.2108 0.02101 0.01450 -0.0466 0.2192 0.7131 10.250 1.2123 0.02252 0.01598 -0.0445 0.2033 0.7197 10.500 1.2147 0.02406 0.01749 -0.0426 0.1890 0.7258 10.750 1.2167 0.02568 0.01909 -0.0409 0.1759 0.7319 11.000 1.2198 0.02730 0.02071 -0.0394 0.1646 0.7391 11.250 1.2228 0.02901 0.02241 -0.0380 0.1547 0.7461 11.500 1.2254 0.03077 0.02419 -0.0367 0.1450 0.7529 11.750 1.2299 0.03247 0.02592 -0.0357 0.1365 0.7603 12.000 1.2330 0.03435 0.02780 -0.0346 0.1280 0.7671 12.250 1.2368 0.03622 0.02971 -0.0337 0.1199 0.7748 12.500 1.2394 0.03828 0.03178 -0.0329 0.1111 0.7832 12.750 1.2424 0.04035 0.03387 -0.0322 0.1038 0.7917 13.000 1.2436 0.04264 0.03617 -0.0316 0.0951 0.8008 13.250 1.2460 0.04489 0.03844 -0.0310 0.0873 0.8099 13.500 1.2498 0.04705 0.04064 -0.0306 0.0812 0.8204 13.750 1.2519 0.04941 0.04305 -0.0302 0.0753 0.8320 14.000 1.2549 0.05169 0.04538 -0.0299 0.0699 0.8456 14.250 1.2581 0.05394 0.04770 -0.0295 0.0655 0.8625 14.500 1.2589 0.05628 0.05014 -0.0289 0.0611 0.8890 15.000 1.2680 0.06112 0.05511 -0.0294 0.0536 1.0000 15.250 1.2725 0.06369 0.05771 -0.0298 0.0505 1.0000 15.500 1.2765 0.06634 0.06038 -0.0301 0.0476 1.0000 15.750 1.2809 0.06901 0.06308 -0.0306 0.0452 1.0000 16.000 1.2844 0.07179 0.06589 -0.0311 0.0430 1.0000 16.250 1.2888 0.07454 0.06868 -0.0317 0.0411 1.0000 16.500 1.2924 0.07740 0.07157 -0.0323 0.0392 1.0000 16.750 1.2956 0.08038 0.07460 -0.0331 0.0379 1.0000 17.000 1.3004 0.08316 0.07743 -0.0338 0.0365 1.0000 17.250 1.3031 0.08626 0.08057 -0.0347 0.0353 1.0000 17.500 1.3055 0.08943 0.08378 -0.0356 0.0342 1.0000 17.750 1.3086 0.09255 0.08697 -0.0366 0.0334 1.0000 18.000 1.3124 0.09560 0.09008 -0.0376 0.0323 1.0000 18.250 1.3149 0.09884 0.09338 -0.0387 0.0315 1.0000 18.500 1.3166 0.10223 0.09682 -0.0399 0.0307 1.0000