XFOIL Version 6.96 Calculated polar for: NASA SC(2)-0406 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.000 -0.5484 0.10584 0.09897 0.0010 1.0000 0.0488 -9.750 -0.6672 0.11154 0.10438 0.0115 1.0000 0.0491 -9.500 -0.6647 0.10702 0.09990 0.0098 1.0000 0.0475 -9.250 -0.6638 0.10226 0.09518 0.0074 1.0000 0.0460 -9.000 -0.6642 0.09719 0.09017 0.0043 1.0000 0.0447 -8.750 -0.6661 0.09165 0.08469 0.0002 1.0000 0.0433 -8.500 -0.6699 0.08483 0.07792 -0.0068 1.0000 0.0418 -8.000 -0.6722 0.07107 0.06374 -0.0196 1.0000 0.0387 -7.750 -0.6658 0.06607 0.05857 -0.0218 1.0000 0.0385 -7.500 -0.6570 0.06103 0.05321 -0.0241 1.0000 0.0386 -7.000 -0.6313 0.05250 0.04429 -0.0269 1.0000 0.0415 -6.750 -0.6138 0.04866 0.04010 -0.0281 1.0000 0.0432 -6.500 -0.5936 0.04445 0.03541 -0.0293 1.0000 0.0439 -6.250 -0.5707 0.04037 0.03077 -0.0302 1.0000 0.0443 -6.000 -0.5459 0.03674 0.02657 -0.0306 1.0000 0.0452 -5.750 -0.5197 0.03352 0.02280 -0.0308 1.0000 0.0467 -5.500 -0.4928 0.03071 0.01937 -0.0305 1.0000 0.0489 -5.250 -0.4668 0.02850 0.01686 -0.0302 1.0000 0.0546 -5.000 -0.4409 0.02677 0.01487 -0.0296 1.0000 0.0628 -4.750 -0.4160 0.02504 0.01307 -0.0289 1.0000 0.0733 -4.500 -0.3914 0.02346 0.01139 -0.0279 1.0000 0.0867 -4.250 -0.3664 0.02208 0.00991 -0.0272 1.0000 0.1060 -4.000 -0.3415 0.02068 0.00846 -0.0269 1.0000 0.1298 -3.750 -0.3156 0.01908 0.00721 -0.0273 1.0000 0.1847 -3.500 -0.2961 0.01654 0.00656 -0.0266 1.0000 0.4981 -3.250 -0.2829 0.01623 0.00674 -0.0217 1.0000 0.6827 -3.000 -0.2690 0.01617 0.00672 -0.0170 1.0000 0.7624 -2.750 -0.2592 0.01609 0.00667 -0.0111 1.0000 0.8311 -2.500 -0.2488 0.01584 0.00636 -0.0049 1.0000 0.9013 -2.250 -0.2059 0.01546 0.00573 -0.0064 1.0000 0.9587 -2.000 -0.1584 0.01515 0.00513 -0.0107 1.0000 0.9817 -1.750 -0.1170 0.01485 0.00464 -0.0141 1.0000 1.0000 -1.500 -0.1018 0.01462 0.00429 -0.0128 1.0000 1.0000 -1.250 -0.0835 0.01446 0.00403 -0.0119 1.0000 1.0000 -1.000 -0.0620 0.01434 0.00382 -0.0115 1.0000 1.0000 -0.750 -0.0382 0.01428 0.00368 -0.0115 1.0000 1.0000 -0.500 -0.0132 0.01425 0.00360 -0.0117 1.0000 1.0000 -0.250 0.0125 0.01426 0.00355 -0.0119 1.0000 1.0000 0.000 0.0386 0.01429 0.00357 -0.0122 1.0000 1.0000 0.250 0.0648 0.01435 0.00364 -0.0124 1.0000 1.0000 0.500 0.0910 0.01443 0.00377 -0.0127 1.0000 1.0000 0.750 0.1172 0.01454 0.00396 -0.0129 1.0000 1.0000 1.000 0.1433 0.01468 0.00419 -0.0131 1.0000 1.0000 1.250 0.1693 0.01484 0.00448 -0.0132 1.0000 1.0000 1.500 0.1951 0.01503 0.00482 -0.0134 1.0000 1.0000 1.750 0.2209 0.01525 0.00528 -0.0136 1.0000 1.0000 2.000 0.2467 0.01550 0.00576 -0.0138 1.0000 1.0000 2.250 0.2724 0.01580 0.00632 -0.0141 1.0000 1.0000 2.500 0.3679 0.01557 0.00677 -0.0254 0.8805 1.0000 2.750 0.4061 0.01655 0.00648 -0.0226 0.4549 1.0000 3.000 0.4221 0.01925 0.00747 -0.0212 0.1821 1.0000 3.250 0.4467 0.02080 0.00870 -0.0210 0.1288 1.0000 3.500 0.4738 0.02225 0.01017 -0.0208 0.1033 1.0000 3.750 0.5013 0.02375 0.01171 -0.0206 0.0830 1.0000 4.000 0.5292 0.02552 0.01366 -0.0201 0.0703 1.0000 4.250 0.5563 0.02723 0.01546 -0.0199 0.0585 1.0000 4.500 0.5853 0.02952 0.01819 -0.0193 0.0536 1.0000 4.750 0.6118 0.03161 0.02052 -0.0191 0.0483 1.0000 5.000 0.6378 0.03427 0.02360 -0.0188 0.0442 1.0000 5.250 0.6634 0.03744 0.02740 -0.0183 0.0424 1.0000 5.500 0.6870 0.04106 0.03162 -0.0179 0.0417 1.0000 5.750 0.7083 0.04504 0.03624 -0.0176 0.0413 1.0000 6.000 0.7272 0.04935 0.04109 -0.0175 0.0413 1.0000 6.250 0.7434 0.05402 0.04625 -0.0177 0.0416 1.0000 6.500 0.7568 0.05892 0.05157 -0.0182 0.0420 1.0000 6.750 0.7676 0.06400 0.05698 -0.0191 0.0426 1.0000 7.000 0.7759 0.06916 0.06241 -0.0202 0.0433 1.0000 7.250 0.7819 0.07431 0.06775 -0.0217 0.0440 1.0000 7.500 0.7863 0.07940 0.07297 -0.0232 0.0448 1.0000 7.750 0.7900 0.08435 0.07800 -0.0245 0.0455 1.0000 8.000 0.7935 0.08927 0.08295 -0.0255 0.0460 1.0000 8.500 0.7763 0.10419 0.09800 -0.0416 0.0539 1.0000 9.000 0.7815 0.11404 0.10781 -0.0447 0.0582 1.0000 9.250 0.6413 0.10946 0.10342 -0.0336 0.0554 1.0000 9.500 0.6463 0.11389 0.10785 -0.0333 0.0583 1.0000