XFOIL Version 6.96 Calculated polar for: NASA SC(2)-0518 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.3481 0.07068 0.06587 -0.0561 1.0000 0.0332 -19.500 -1.3485 0.06753 0.06265 -0.0572 1.0000 0.0335 -19.250 -1.3487 0.06443 0.05950 -0.0582 1.0000 0.0339 -19.000 -1.3462 0.06170 0.05672 -0.0590 1.0000 0.0344 -18.750 -1.3428 0.05915 0.05412 -0.0597 1.0000 0.0349 -18.500 -1.3379 0.05680 0.05172 -0.0602 1.0000 0.0354 -18.250 -1.3320 0.05459 0.04946 -0.0607 1.0000 0.0359 -18.000 -1.3244 0.05257 0.04741 -0.0611 1.0000 0.0364 -17.750 -1.3173 0.05054 0.04532 -0.0615 1.0000 0.0369 -17.500 -1.3078 0.04880 0.04354 -0.0618 1.0000 0.0374 -17.250 -1.2998 0.04694 0.04163 -0.0620 1.0000 0.0378 -17.000 -1.2914 0.04512 0.03978 -0.0622 1.0000 0.0384 -16.750 -1.2815 0.04350 0.03814 -0.0623 1.0000 0.0390 -16.500 -1.2717 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0.1127 0.6007 3.250 0.7829 0.01190 0.00469 -0.1080 0.1064 0.6023 3.500 0.8112 0.01210 0.00485 -0.1080 0.1013 0.6037 3.750 0.8394 0.01230 0.00503 -0.1079 0.0971 0.6051 4.000 0.8676 0.01249 0.00519 -0.1079 0.0924 0.6064 4.250 0.8954 0.01272 0.00538 -0.1077 0.0880 0.6078 4.500 0.9232 0.01293 0.00557 -0.1076 0.0842 0.6090 4.750 0.9506 0.01317 0.00577 -0.1074 0.0810 0.6102 5.000 0.9782 0.01337 0.00596 -0.1072 0.0787 0.6112 5.250 1.0054 0.01361 0.00617 -0.1070 0.0761 0.6123 5.500 1.0322 0.01386 0.00641 -0.1067 0.0736 0.6142 5.750 1.0594 0.01406 0.00663 -0.1065 0.0720 0.6160 6.000 1.0862 0.01429 0.00687 -0.1062 0.0703 0.6179 6.250 1.1126 0.01455 0.00712 -0.1058 0.0685 0.6198 6.500 1.1383 0.01484 0.00740 -0.1053 0.0665 0.6218 6.750 1.1645 0.01507 0.00765 -0.1049 0.0651 0.6237 7.000 1.1902 0.01533 0.00791 -0.1044 0.0635 0.6256 7.250 1.2154 0.01562 0.00819 -0.1038 0.0619 0.6273 7.500 1.2399 0.01593 0.00850 -0.1031 0.0603 0.6289 7.750 1.2645 0.01622 0.00880 -0.1024 0.0592 0.6305 8.000 1.2887 0.01651 0.00909 -0.1017 0.0578 0.6318 8.250 1.3123 0.01682 0.00941 -0.1008 0.0563 0.6334 8.500 1.3350 0.01717 0.00976 -0.0999 0.0548 0.6358 8.750 1.3573 0.01751 0.01012 -0.0988 0.0536 0.6381 9.000 1.3791 0.01784 0.01048 -0.0976 0.0525 0.6403 9.250 1.3999 0.01819 0.01085 -0.0963 0.0514 0.6426 9.500 1.4182 0.01857 0.01125 -0.0945 0.0503 0.6449 9.750 1.4345 0.01900 0.01169 -0.0924 0.0492 0.6472 10.000 1.4529 0.01946 0.01216 -0.0908 0.0483 0.6494 10.250 1.4721 0.01990 0.01263 -0.0893 0.0474 0.6514 10.500 1.4908 0.02038 0.01314 -0.0878 0.0465 0.6532 10.750 1.5092 0.02090 0.01368 -0.0863 0.0454 0.6557 11.000 1.5268 0.02147 0.01427 -0.0848 0.0443 0.6589 11.250 1.5438 0.02209 0.01492 -0.0832 0.0434 0.6621 11.500 1.5614 0.02267 0.01554 -0.0817 0.0428 0.6653 11.750 1.5786 0.02328 0.01620 -0.0802 0.0421 0.6683 12.000 1.5950 0.02395 0.01691 -0.0787 0.0414 0.6711 12.250 1.6110 0.02467 0.01765 -0.0772 0.0407 0.6736 12.750 1.6409 0.02628 0.01934 -0.0741 0.0393 0.6797 13.000 1.6546 0.02720 0.02030 -0.0725 0.0386 0.6832 13.250 1.6692 0.02807 0.02122 -0.0711 0.0382 0.6867 13.500 1.6833 0.02899 0.02219 -0.0696 0.0378 0.6902 13.750 1.6968 0.02997 0.02323 -0.0682 0.0373 0.6934 14.000 1.7096 0.03102 0.02432 -0.0668 0.0368 0.6963 14.250 1.7215 0.03215 0.02550 -0.0654 0.0363 0.6995 14.500 1.7331 0.03334 0.02674 -0.0641 0.0357 0.7036 14.750 1.7434 0.03466 0.02812 -0.0627 0.0352 0.7076 15.000 1.7531 0.03606 0.02957 -0.0614 0.0347 0.7115 15.250 1.7611 0.03761 0.03117 -0.0600 0.0342 0.7149 15.500 1.7702 0.03909 0.03272 -0.0588 0.0340 0.7180 15.750 1.7793 0.04061 0.03431 -0.0577 0.0337 0.7207 16.000 1.7873 0.04228 0.03605 -0.0567 0.0334 0.7244 16.250 1.7946 0.04404 0.03789 -0.0557 0.0331 0.7282 16.500 1.8013 0.04589 0.03982 -0.0548 0.0328 0.7318 16.750 1.8068 0.04792 0.04192 -0.0539 0.0325 0.7354 17.000 1.8115 0.05009 0.04417 -0.0532 0.0322 0.7386 17.250 1.8155 0.05239 0.04653 -0.0526 0.0319 0.7414 17.500 1.8185 0.05484 0.04906 -0.0521 0.0316 0.7445 17.750 1.8201 0.05751 0.05181 -0.0517 0.0314 0.7479 18.000 1.8203 0.06041 0.05480 -0.0514 0.0311 0.7513 18.250 1.8191 0.06354 0.05801 -0.0514 0.0308 0.7546 18.500 1.8164 0.06694 0.06150 -0.0515 0.0306 0.7577 18.750 1.8117 0.07067 0.06533 -0.0518 0.0303 0.7604 19.000 1.8049 0.07476 0.06951 -0.0523 0.0301 0.7626 19.250 1.7997 0.07873 0.07359 -0.0530 0.0299 0.7651