XFOIL Version 6.96 Calculated polar for: NACA 63(4)-221 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -0.9659 0.10933 0.10348 -0.0327 1.0000 0.0380 -19.500 -0.9667 0.10552 0.09953 -0.0347 1.0000 0.0387 -19.250 -0.9656 0.10206 0.09598 -0.0364 1.0000 0.0394 -19.000 -0.9624 0.09907 0.09297 -0.0378 1.0000 0.0401 -18.750 -0.9597 0.09598 0.08985 -0.0392 1.0000 0.0408 -18.500 -0.9573 0.09282 0.08662 -0.0407 1.0000 0.0416 -18.250 -0.9538 0.08989 0.08362 -0.0419 1.0000 0.0425 -18.000 -0.9509 0.08687 0.08049 -0.0432 1.0000 0.0435 -17.750 -0.9465 0.08409 0.07759 -0.0443 1.0000 0.0444 -17.500 -0.9417 0.08154 0.07505 -0.0452 1.0000 0.0451 -17.250 -0.9377 0.07882 0.07230 -0.0462 1.0000 0.0461 -17.000 -0.9325 0.07629 0.06973 -0.0471 1.0000 0.0470 -16.750 -0.9273 0.07376 0.06714 -0.0480 1.0000 0.0481 -16.500 -0.9214 0.07137 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0.00614 -0.0318 0.6173 0.5392 -2.000 -0.0722 0.01416 0.00601 -0.0320 0.6136 0.5439 -1.750 -0.0437 0.01413 0.00595 -0.0323 0.6090 0.5480 -1.500 -0.0152 0.01411 0.00597 -0.0325 0.6043 0.5513 -1.250 0.0134 0.01411 0.00596 -0.0327 0.6003 0.5551 -1.000 0.0422 0.01410 0.00590 -0.0329 0.5968 0.5592 -0.750 0.0710 0.01410 0.00583 -0.0333 0.5935 0.5634 -0.500 0.0995 0.01410 0.00585 -0.0336 0.5892 0.5673 -0.250 0.1279 0.01411 0.00591 -0.0337 0.5847 0.5708 0.000 0.1565 0.01412 0.00592 -0.0339 0.5807 0.5746 0.250 0.1853 0.01414 0.00588 -0.0342 0.5772 0.5786 0.500 0.2142 0.01417 0.00588 -0.0345 0.5739 0.5828 0.750 0.2425 0.01420 0.00595 -0.0348 0.5699 0.5866 1.000 0.2707 0.01424 0.00605 -0.0349 0.5658 0.5903 1.250 0.2992 0.01428 0.00610 -0.0351 0.5620 0.5945 1.500 0.3280 0.01432 0.00611 -0.0354 0.5585 0.5990 1.750 0.3568 0.01438 0.00614 -0.0357 0.5552 0.6035 2.000 0.3846 0.01444 0.00629 -0.0359 0.5511 0.6071 2.250 0.4125 0.01451 0.00642 -0.0360 0.5469 0.6108 2.500 0.4407 0.01457 0.00650 -0.0362 0.5431 0.6151 2.750 0.4695 0.01464 0.00654 -0.0364 0.5398 0.6202 3.000 0.4977 0.01473 0.00664 -0.0367 0.5359 0.6249 3.250 0.5248 0.01482 0.00685 -0.0367 0.5314 0.6288 3.500 0.5524 0.01490 0.00699 -0.0367 0.5271 0.6331 3.750 0.5805 0.01498 0.00707 -0.0369 0.5233 0.6379 4.000 0.6095 0.01507 0.00712 -0.0372 0.5199 0.6429 4.250 0.6357 0.01519 0.00738 -0.0371 0.5152 0.6470 4.500 0.6623 0.01531 0.00758 -0.0370 0.5105 0.6516 4.750 0.6897 0.01541 0.00772 -0.0371 0.5063 0.6569 5.000 0.7182 0.01551 0.00779 -0.0373 0.5025 0.6624 5.250 0.7440 0.01565 0.00806 -0.0371 0.4979 0.6666 5.500 0.7696 0.01579 0.00831 -0.0369 0.4927 0.6712 5.750 0.7962 0.01588 0.00843 -0.0368 0.4873 0.6767 6.000 0.8223 0.01599 0.00855 -0.0367 0.4806 0.6826 6.250 0.8460 0.01609 0.00877 -0.0361 0.4724 0.6873 6.500 0.8718 0.01619 0.00887 -0.0358 0.4663 0.6923 6.750 0.8952 0.01637 0.00918 -0.0353 0.4593 0.6979 7.000 0.9196 0.01652 0.00936 -0.0350 0.4522 0.7039 7.250 0.9425 0.01668 0.00960 -0.0342 0.4451 0.7088 7.500 0.9640 0.01686 0.00988 -0.0334 0.4365 0.7146 7.750 0.9859 0.01705 0.01009 -0.0326 0.4279 0.7209 8.000 1.0050 0.01728 0.01040 -0.0314 0.4178 0.7264 8.250 1.0227 0.01752 0.01072 -0.0300 0.4074 0.7321 8.500 1.0383 0.01781 0.01101 -0.0283 0.3952 0.7390 8.750 1.0480 0.01815 0.01138 -0.0257 0.3801 0.7454 9.000 1.0526 0.01862 0.01187 -0.0225 0.3634 0.7516 9.250 1.0561 0.01933 0.01255 -0.0195 0.3447 0.7590 9.500 1.0577 0.02021 0.01340 -0.0165 0.3246 0.7661 9.750 1.0580 0.02128 0.01443 -0.0137 0.3056 0.7738 10.250 1.0572 0.02388 0.01697 -0.0088 0.2694 0.7899 10.500 1.0566 0.02539 0.01845 -0.0068 0.2524 0.7990 10.750 1.0555 0.02697 0.02003 -0.0048 0.2364 0.8078 11.000 1.0545 0.02869 0.02173 -0.0031 0.2205 0.8179 11.250 1.0532 0.03049 0.02352 -0.0014 0.2059 0.8280 11.500 1.0525 0.03239 0.02541 -0.0001 0.1922 0.8395 11.750 1.0510 0.03435 0.02738 0.0012 0.1798 0.8521 12.000 1.0513 0.03626 0.02931 0.0023 0.1682 0.8670 12.250 1.0524 0.03816 0.03126 0.0033 0.1576 0.8869 12.500 1.0548 0.04018 0.03335 0.0037 0.1477 0.9195 13.000 1.0631 0.04444 0.03763 0.0034 0.1288 1.0000 13.250 1.0668 0.04674 0.03991 0.0033 0.1206 1.0000 13.500 1.0696 0.04916 0.04231 0.0031 0.1126 1.0000 13.750 1.0742 0.05147 0.04462 0.0029 0.1051 1.0000 14.000 1.0770 0.05400 0.04714 0.0027 0.0981 1.0000 14.250 1.0802 0.05655 0.04968 0.0023 0.0917 1.0000 14.500 1.0843 0.05903 0.05217 0.0020 0.0862 1.0000 14.750 1.0863 0.06180 0.05495 0.0015 0.0811 1.0000 15.000 1.0910 0.06433 0.05751 0.0010 0.0768 1.0000 15.250 1.0934 0.06717 0.06036 0.0004 0.0729 1.0000 15.500 1.0970 0.06989 0.06311 -0.0002 0.0694 1.0000 15.750 1.1002 0.07271 0.06598 -0.0009 0.0663 1.0000 16.000 1.1014 0.07582 0.06908 -0.0018 0.0636 1.0000 16.250 1.1061 0.07854 0.07188 -0.0025 0.0610 1.0000 16.500 1.1091 0.08151 0.07489 -0.0034 0.0586 1.0000 16.750 1.1095 0.08486 0.07825 -0.0045 0.0568 1.0000 17.000 1.1144 0.08764 0.08110 -0.0054 0.0547 1.0000 17.250 1.1176 0.09070 0.08423 -0.0065 0.0529 1.0000 17.500 1.1187 0.09408 0.08762 -0.0077 0.0510 1.0000 17.750 1.1212 0.09728 0.09088 -0.0089 0.0495 1.0000 18.000 1.1248 0.10038 0.09406 -0.0101 0.0476 1.0000 18.250 1.1271 0.10371 0.09744 -0.0115 0.0461 1.0000 18.500 1.1280 0.10723 0.10099 -0.0131 0.0450 1.0000