XFOIL Version 6.96 Calculated polar for: NACA 16-015 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 ------ -------- --------- --------- -------- -------- -------- -19.000 -0.8458 0.12828 0.12548 -0.0481 1.0000 0.0080 -18.750 -0.9138 0.11017 0.10709 -0.0565 1.0000 0.0077 -18.500 -0.9535 0.09834 0.09505 -0.0621 1.0000 0.0076 -18.250 -0.9841 0.08882 0.08534 -0.0668 1.0000 0.0075 -18.000 -1.0119 0.08049 0.07684 -0.0706 1.0000 0.0075 -17.750 -1.0347 0.07371 0.06989 -0.0731 1.0000 0.0075 -17.500 -1.0540 0.06809 0.06410 -0.0745 1.0000 0.0075 -17.250 -1.0727 0.06313 0.05900 -0.0750 1.0000 0.0076 -17.000 -1.0903 0.05877 0.05449 -0.0747 1.0000 0.0076 -16.750 -1.1057 0.05506 0.05065 -0.0737 1.0000 0.0077 -16.500 -1.1190 0.05190 0.04736 -0.0721 1.0000 0.0078 -16.250 -1.1305 0.04914 0.04449 -0.0700 1.0000 0.0079 -16.000 -1.1398 0.04677 0.04201 -0.0676 1.0000 0.0080 -15.750 -1.1430 0.04446 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0.00384 -0.0018 0.8917 0.8415 -1.500 -0.1638 0.00834 0.00398 0.0004 0.8880 0.8513 -1.250 -0.1399 0.00842 0.00405 0.0012 0.8846 0.8566 -1.000 -0.1212 0.00836 0.00396 0.0031 0.8814 0.8627 -0.750 -0.0854 0.00838 0.00397 0.0011 0.8800 0.8645 -0.500 -0.0505 0.00838 0.00396 -0.0008 0.8786 0.8664 -0.250 -0.0164 0.00836 0.00394 -0.0024 0.8773 0.8686 0.000 -0.0001 0.00840 0.00399 0.0000 0.8728 0.8729 0.250 0.0164 0.00836 0.00394 0.0024 0.8686 0.8773 0.500 0.0505 0.00838 0.00396 0.0008 0.8664 0.8786 0.750 0.0854 0.00838 0.00397 -0.0011 0.8645 0.8800 1.000 0.1212 0.00836 0.00396 -0.0031 0.8627 0.8814 1.250 0.1399 0.00842 0.00405 -0.0012 0.8566 0.8846 1.500 0.1638 0.00834 0.00398 -0.0004 0.8513 0.8880 1.750 0.1820 0.00821 0.00385 0.0018 0.8416 0.8917 2.000 0.2127 0.00809 0.00369 0.0012 0.8225 0.8929 2.250 0.2412 0.00805 0.00359 0.0012 0.7960 0.8944 2.500 0.2692 0.00809 0.00355 0.0011 0.7667 0.8960 2.750 0.2914 0.00821 0.00353 0.0024 0.7255 0.8984 3.000 0.2894 0.00834 0.00343 0.0092 0.6728 0.9049 3.250 0.2859 0.00894 0.00364 0.0162 0.5821 0.9083 3.500 0.2799 0.00962 0.00396 0.0235 0.4942 0.9129 3.750 0.2713 0.01000 0.00406 0.0313 0.4268 0.9202 4.000 0.2836 0.01071 0.00444 0.0341 0.3418 0.9224 4.250 0.3000 0.01130 0.00476 0.0360 0.2736 0.9247 4.500 0.3167 0.01180 0.00505 0.0379 0.2171 0.9274 4.750 0.3311 0.01218 0.00525 0.0403 0.1749 0.9311 5.000 0.3439 0.01246 0.00541 0.0431 0.1449 0.9354 5.250 0.3674 0.01287 0.00571 0.0435 0.1151 0.9369 5.500 0.3909 0.01326 0.00601 0.0439 0.0919 0.9384 5.750 0.4133 0.01364 0.00631 0.0445 0.0730 0.9403 6.000 0.4349 0.01398 0.00660 0.0453 0.0593 0.9427 6.250 0.4528 0.01426 0.00685 0.0470 0.0515 0.9462 6.500 0.4696 0.01447 0.00708 0.0490 0.0474 0.9497 6.750 0.4953 0.01482 0.00744 0.0489 0.0441 0.9508 7.000 0.5201 0.01523 0.00784 0.0489 0.0409 0.9521 7.250 0.5445 0.01562 0.00825 0.0491 0.0388 0.9536 7.500 0.5684 0.01596 0.00864 0.0493 0.0374 0.9554 7.750 0.5901 0.01629 0.00901 0.0500 0.0358 0.9576 8.000 0.6021 0.01653 0.00928 0.0530 0.0344 0.9624 8.250 0.6275 0.01700 0.00976 0.0527 0.0326 0.9633 8.500 0.6511 0.01759 0.01038 0.0528 0.0308 0.9643 8.750 0.6767 0.01796 0.01082 0.0525 0.0298 0.9653 9.000 0.7016 0.01837 0.01127 0.0524 0.0284 0.9664 9.250 0.7262 0.01879 0.01173 0.0522 0.0269 0.9677 9.500 0.7493 0.01926 0.01222 0.0523 0.0255 0.9693 9.750 0.7661 0.01987 0.01286 0.0537 0.0239 0.9720 10.000 0.7840 0.02021 0.01326 0.0551 0.0231 0.9747 10.250 0.8098 0.02067 0.01379 0.0546 0.0217 0.9753 10.500 0.8351 0.02115 0.01433 0.0541 0.0203 0.9759 10.750 0.8596 0.02167 0.01486 0.0538 0.0190 0.9768 11.000 0.8818 0.02232 0.01556 0.0538 0.0179 0.9778 11.250 0.9039 0.02289 0.01621 0.0539 0.0168 0.9789 11.500 0.9249 0.02344 0.01683 0.0542 0.0157 0.9803 11.750 0.9441 0.02402 0.01744 0.0548 0.0147 0.9821 12.000 0.9581 0.02470 0.01816 0.0565 0.0140 0.9849 12.250 0.9782 0.02555 0.01909 0.0566 0.0133 0.9856 12.500 0.9976 0.02639 0.02003 0.0568 0.0127 0.9863 12.750 1.0159 0.02724 0.02098 0.0572 0.0121 0.9872 13.000 1.0337 0.02810 0.02193 0.0576 0.0115 0.9881 13.250 1.0503 0.02902 0.02292 0.0581 0.0110 0.9893 13.500 1.0645 0.03014 0.02411 0.0589 0.0105 0.9906 13.750 1.0764 0.03138 0.02546 0.0599 0.0101 0.9921 14.000 1.0883 0.03256 0.02676 0.0610 0.0098 0.9935 14.250 1.0992 0.03386 0.02819 0.0620 0.0095 0.9946 14.500 1.1103 0.03528 0.02975 0.0627 0.0092 0.9953 14.750 1.1201 0.03682 0.03142 0.0634 0.0089 0.9961 15.000 1.1289 0.03847 0.03320 0.0640 0.0087 0.9971 15.250 1.1363 0.04027 0.03512 0.0646 0.0085 0.9980 15.500 1.1419 0.04223 0.03721 0.0652 0.0083 0.9990 15.750 1.1454 0.04444 0.03955 0.0657 0.0081 0.9998 16.000 1.1407 0.04666 0.04189 0.0676 0.0080 1.0000 16.250 1.1312 0.04904 0.04438 0.0700 0.0079 1.0000 16.500 1.1201 0.05175 0.04721 0.0721 0.0078 1.0000 16.750 1.1066 0.05494 0.05052 0.0737 0.0077 1.0000 17.000 1.0914 0.05863 0.05435 0.0747 0.0076 1.0000 17.250 1.0739 0.06298 0.05884 0.0750 0.0076 1.0000 17.500 1.0557 0.06789 0.06389 0.0745 0.0075 1.0000 17.750 1.0365 0.07349 0.06966 0.0731 0.0075 1.0000 18.000 1.0135 0.08031 0.07665 0.0705 0.0075 1.0000 18.250 0.9860 0.08861 0.08512 0.0667 0.0075 1.0000 18.500 0.9549 0.09826 0.09498 0.0620 0.0076 1.0000 18.750 0.9156 0.11005 0.10697 0.0563 0.0077 1.0000 19.000 0.8479 0.12811 0.12531 0.0480 0.0080 1.0000