XFOIL Version 6.96 Calculated polar for: NASA SC(2)-0610 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.250 -0.5663 0.10276 0.09722 -0.0236 1.0000 0.1483 -10.000 -0.5554 0.09992 0.09438 -0.0226 1.0000 0.1531 -9.750 -0.6216 0.09347 0.08817 -0.0331 1.0000 0.1602 -9.500 -0.5725 0.09138 0.08598 -0.0262 1.0000 0.1642 -9.250 -0.5670 0.08841 0.08304 -0.0255 1.0000 0.1696 -9.000 -0.6793 0.08095 0.07569 -0.0393 1.0000 0.1760 -8.750 -0.5924 0.08038 0.07519 -0.0269 1.0000 0.1814 -8.500 -0.7087 0.05047 0.04372 -0.0505 1.0000 0.0881 -8.250 -0.6936 0.04619 0.03919 -0.0504 1.0000 0.0835 -8.000 -0.6777 0.04158 0.03418 -0.0511 1.0000 0.0811 -7.750 -0.6573 0.03738 0.02947 -0.0519 1.0000 0.0798 -7.500 -0.6341 0.03437 0.02600 -0.0525 1.0000 0.0814 -7.250 -0.6086 0.03194 0.02306 -0.0530 1.0000 0.0845 -7.000 -0.5816 0.02981 0.02040 -0.0533 1.0000 0.0867 -6.750 -0.5583 0.02734 0.01794 -0.0532 1.0000 0.0905 -6.500 -0.5330 0.02607 0.01654 -0.0530 1.0000 0.0969 -6.250 -0.5073 0.02441 0.01467 -0.0526 1.0000 0.1024 -6.000 -0.4824 0.02326 0.01356 -0.0523 1.0000 0.1106 -5.750 -0.4572 0.02197 0.01226 -0.0519 1.0000 0.1186 -5.500 -0.4309 0.02115 0.01134 -0.0517 1.0000 0.1298 -5.250 -0.4056 0.02003 0.01044 -0.0513 1.0000 0.1424 -5.000 -0.3787 0.01913 0.00965 -0.0514 1.0000 0.1605 -4.750 -0.3499 0.01809 0.00892 -0.0520 1.0000 0.1897 -4.500 -0.3085 0.01535 0.00855 -0.0563 1.0000 0.5117 -4.250 -0.2978 0.01657 0.00999 -0.0504 1.0000 0.6446 -4.000 -0.2865 0.01766 0.01104 -0.0451 1.0000 0.6786 -3.750 -0.2717 0.01855 0.01184 -0.0410 1.0000 0.7055 -3.500 -0.2614 0.01931 0.01255 -0.0358 1.0000 0.7234 -3.250 -0.2502 0.01992 0.01312 -0.0310 1.0000 0.7408 -3.000 -0.2387 0.02038 0.01356 -0.0265 1.0000 0.7577 -2.750 -0.2287 0.02073 0.01389 -0.0216 1.0000 0.7748 -2.500 -0.2196 0.02096 0.01410 -0.0165 1.0000 0.7927 -2.250 -0.2102 0.02105 0.01417 -0.0118 1.0000 0.8122 -2.000 -0.1979 0.02106 0.01415 -0.0079 1.0000 0.8334 -1.750 -0.1910 0.02079 0.01387 -0.0028 1.0000 0.8516 -1.500 -0.1810 0.02044 0.01350 0.0013 1.0000 0.8697 -1.250 -0.1658 0.02007 0.01311 0.0038 1.0000 0.8849 -1.000 -0.1449 0.01976 0.01277 0.0048 1.0000 0.8958 -0.750 -0.1207 0.01955 0.01252 0.0048 1.0000 0.9043 -0.500 -0.0982 0.01926 0.01222 0.0052 1.0000 0.9115 -0.250 -0.0717 0.01914 0.01209 0.0045 1.0000 0.9181 0.000 -0.0475 0.01896 0.01191 0.0044 1.0000 0.9242 0.250 -0.0217 0.01888 0.01185 0.0039 1.0000 0.9299 0.500 0.0078 0.01895 0.01194 0.0024 1.0000 0.9340 0.750 0.0331 0.01890 0.01193 0.0019 1.0000 0.9385 1.000 0.0610 0.01899 0.01207 0.0007 1.0000 0.9427 1.250 0.0902 0.01918 0.01233 -0.0008 1.0000 0.9468 1.500 0.1164 0.01931 0.01254 -0.0017 1.0000 0.9511 1.750 0.1433 0.01954 0.01287 -0.0029 1.0000 0.9558 2.000 0.2138 0.01981 0.01329 -0.0116 0.9761 0.9576 2.250 0.2948 0.01933 0.01301 -0.0207 0.9442 0.9587 2.500 0.3603 0.01825 0.01214 -0.0260 0.9141 0.9601 2.750 0.4143 0.01685 0.01097 -0.0285 0.8815 0.9619 3.000 0.4567 0.01539 0.00971 -0.0283 0.8293 0.9643 3.250 0.5028 0.01586 0.00794 -0.0269 0.3427 0.9644 3.500 0.5186 0.01778 0.00875 -0.0253 0.2007 0.9687 3.750 0.5434 0.01881 0.00952 -0.0251 0.1659 0.9731 4.000 0.5723 0.01985 0.01036 -0.0257 0.1457 0.9772 4.250 0.6034 0.02097 0.01138 -0.0266 0.1304 0.9818 4.500 0.6373 0.02221 0.01263 -0.0280 0.1179 0.9866 4.750 0.6722 0.02379 0.01421 -0.0296 0.1084 0.9922 5.000 0.7026 0.02506 0.01549 -0.0304 0.0996 1.0000 5.250 0.7336 0.02702 0.01769 -0.0312 0.0938 1.0000 5.500 0.7633 0.02851 0.01934 -0.0319 0.0875 1.0000 5.750 0.7933 0.03154 0.02242 -0.0331 0.0835 1.0000 6.000 0.8205 0.03386 0.02527 -0.0331 0.0819 1.0000 6.250 0.8457 0.03648 0.02846 -0.0328 0.0798 1.0000 6.500 0.8686 0.03955 0.03205 -0.0326 0.0779 1.0000 6.750 0.8884 0.04370 0.03671 -0.0321 0.0792 1.0000 7.000 0.9064 0.04834 0.04172 -0.0319 0.0813 1.0000 7.250 0.8627 0.07130 0.06714 -0.0319 0.1793 1.0000 7.500 0.8915 0.07537 0.07111 -0.0319 0.1746 1.0000 7.750 0.8600 0.08053 0.07660 -0.0344 0.1641 1.0000 8.000 0.7796 0.07719 0.07335 -0.0191 0.1729 1.0000 8.250 0.6943 0.08478 0.08112 -0.0238 0.1713 1.0000 8.500 0.6552 0.09282 0.08913 -0.0308 0.1646 1.0000