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 = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.0779 0.08309 0.07897 -0.0563 1.0000 0.0260 -19.500 -1.0835 0.07923 0.07507 -0.0578 1.0000 0.0267 -19.250 -1.0828 0.07621 0.07201 -0.0590 1.0000 0.0273 -19.000 -1.0825 0.07315 0.06890 -0.0601 1.0000 0.0277 -18.750 -1.0768 0.07080 0.06650 -0.0609 1.0000 0.0286 -18.500 -1.0728 0.06825 0.06389 -0.0618 1.0000 0.0291 -18.250 -1.0658 0.06608 0.06166 -0.0625 1.0000 0.0296 -18.000 -1.0692 0.06275 0.05829 -0.0636 1.0000 0.0303 -17.750 -1.0668 0.06012 0.05564 -0.0644 1.0000 0.0309 -17.500 -1.0618 0.05780 0.05329 -0.0651 1.0000 0.0317 -17.250 -1.0549 0.05574 0.05118 -0.0656 1.0000 0.0323 -17.000 -1.0485 0.05360 0.04900 -0.0662 1.0000 0.0328 -16.750 -1.0383 0.05191 0.04725 -0.0666 1.0000 0.0335 -16.500 -1.0333 0.04973 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0.00222 -0.0699 0.5875 0.4935 -2.250 0.0751 0.00754 0.00222 -0.0703 0.5830 0.4980 -2.000 0.1055 0.00753 0.00221 -0.0708 0.5801 0.5018 -1.750 0.1358 0.00754 0.00219 -0.0713 0.5766 0.5050 -1.500 0.1657 0.00753 0.00217 -0.0717 0.5727 0.5090 -1.250 0.1953 0.00753 0.00217 -0.0721 0.5687 0.5135 -1.000 0.2249 0.00758 0.00219 -0.0725 0.5643 0.5176 -0.750 0.2552 0.00758 0.00220 -0.0730 0.5614 0.5215 -0.500 0.2854 0.00760 0.00220 -0.0735 0.5578 0.5248 -0.250 0.3152 0.00758 0.00221 -0.0739 0.5538 0.5297 0.000 0.3447 0.00761 0.00223 -0.0743 0.5497 0.5340 0.250 0.3741 0.00767 0.00227 -0.0747 0.5455 0.5379 0.500 0.4043 0.00769 0.00229 -0.0752 0.5427 0.5416 0.750 0.4344 0.00772 0.00232 -0.0756 0.5392 0.5446 1.000 0.4640 0.00772 0.00234 -0.0760 0.5353 0.5495 1.250 0.4932 0.00776 0.00239 -0.0764 0.5311 0.5535 1.500 0.5225 0.00783 0.00244 -0.0767 0.5264 0.5574 1.750 0.5524 0.00785 0.00248 -0.0772 0.5227 0.5611 2.000 0.5820 0.00790 0.00252 -0.0776 0.5181 0.5642 2.250 0.6110 0.00793 0.00257 -0.0779 0.5137 0.5694 2.500 0.6397 0.00803 0.00265 -0.0782 0.5088 0.5739 2.750 0.6695 0.00805 0.00271 -0.0786 0.5057 0.5781 3.000 0.6990 0.00810 0.00277 -0.0790 0.5017 0.5818 3.250 0.7280 0.00816 0.00284 -0.0793 0.4974 0.5854 3.500 0.7563 0.00824 0.00293 -0.0795 0.4928 0.5903 3.750 0.7853 0.00831 0.00302 -0.0798 0.4890 0.5948 4.000 0.8146 0.00835 0.00310 -0.0802 0.4853 0.5991 4.250 0.8434 0.00843 0.00318 -0.0805 0.4809 0.6029 4.500 0.8711 0.00853 0.00328 -0.0806 0.4753 0.6078 4.750 0.8995 0.00860 0.00338 -0.0808 0.4697 0.6129 5.000 0.9280 0.00866 0.00347 -0.0811 0.4638 0.6176 5.250 0.9555 0.00879 0.00359 -0.0811 0.4586 0.6218 5.500 0.9830 0.00891 0.00371 -0.0812 0.4538 0.6259 5.750 1.0114 0.00896 0.00383 -0.0815 0.4492 0.6312 6.000 1.0387 0.00908 0.00396 -0.0815 0.4436 0.6361 6.250 1.0646 0.00926 0.00412 -0.0813 0.4372 0.6407 6.500 1.0925 0.00935 0.00424 -0.0815 0.4317 0.6447 6.750 1.1181 0.00949 0.00441 -0.0813 0.4240 0.6507 7.000 1.1439 0.00965 0.00458 -0.0811 0.4168 0.6561 7.250 1.1692 0.00982 0.00476 -0.0808 0.4079 0.6612 7.500 1.1935 0.01003 0.00495 -0.0804 0.3988 0.6653 7.750 1.2169 0.01023 0.00517 -0.0798 0.3877 0.6712 8.000 1.2406 0.01043 0.00538 -0.0793 0.3777 0.6768 8.250 1.2614 0.01072 0.00564 -0.0783 0.3643 0.6824 8.500 1.2794 0.01108 0.00594 -0.0769 0.3458 0.6875 8.750 1.2917 0.01149 0.00631 -0.0744 0.3270 0.6935 9.000 1.2970 0.01206 0.00680 -0.0708 0.3066 0.6994 9.250 1.3019 0.01274 0.00741 -0.0674 0.2881 0.7050 9.500 1.3066 0.01349 0.00810 -0.0642 0.2703 0.7113 9.750 1.3093 0.01438 0.00894 -0.0609 0.2520 0.7180 10.000 1.3117 0.01541 0.00989 -0.0579 0.2342 0.7243 10.250 1.3136 0.01653 0.01097 -0.0551 0.2166 0.7307 10.500 1.3144 0.01782 0.01220 -0.0524 0.1986 0.7378 10.750 1.3162 0.01916 0.01349 -0.0500 0.1836 0.7448 11.000 1.3182 0.02056 0.01487 -0.0478 0.1703 0.7519 11.250 1.3208 0.02201 0.01630 -0.0458 0.1586 0.7596 11.500 1.3246 0.02347 0.01774 -0.0441 0.1478 0.7666 11.750 1.3275 0.02502 0.01930 -0.0424 0.1377 0.7748 12.000 1.3295 0.02671 0.02098 -0.0408 0.1280 0.7833 12.250 1.3319 0.02842 0.02270 -0.0393 0.1189 0.7919 12.500 1.3354 0.03011 0.02440 -0.0381 0.1106 0.8016 12.750 1.3374 0.03199 0.02630 -0.0368 0.1027 0.8113 13.000 1.3384 0.03402 0.02833 -0.0357 0.0949 0.8220 13.250 1.3411 0.03595 0.03029 -0.0347 0.0876 0.8339 13.500 1.3430 0.03800 0.03239 -0.0338 0.0810 0.8483 13.750 1.3441 0.04013 0.03457 -0.0328 0.0751 0.8669 14.000 1.3433 0.04221 0.03675 -0.0315 0.0692 0.9019 14.250 1.3468 0.04440 0.03906 -0.0314 0.0634 1.0000 14.500 1.3504 0.04671 0.04136 -0.0312 0.0586 1.0000 14.750 1.3523 0.04923 0.04388 -0.0310 0.0538 1.0000 15.000 1.3551 0.05171 0.04636 -0.0310 0.0501 1.0000 15.250 1.3592 0.05412 0.04878 -0.0310 0.0467 1.0000 15.500 1.3618 0.05674 0.05142 -0.0311 0.0442 1.0000 15.750 1.3669 0.05913 0.05383 -0.0312 0.0421 1.0000 16.000 1.3702 0.06176 0.05649 -0.0315 0.0402 1.0000 16.250 1.3731 0.06448 0.05922 -0.0318 0.0386 1.0000 16.500 1.3781 0.06702 0.06182 -0.0322 0.0373 1.0000 16.750 1.3828 0.06962 0.06446 -0.0326 0.0362 1.0000 17.000 1.3854 0.07250 0.06737 -0.0332 0.0350 1.0000 17.250 1.3868 0.07559 0.07049 -0.0338 0.0340 1.0000 17.500 1.3921 0.07821 0.07318 -0.0344 0.0333 1.0000 17.750 1.3962 0.08106 0.07608 -0.0351 0.0325 1.0000 18.000 1.4002 0.08391 0.07897 -0.0359 0.0318 1.0000 18.250 1.4011 0.08722 0.08233 -0.0368 0.0310 1.0000 18.500 1.4023 0.09052 0.08567 -0.0378 0.0303 1.0000