XFOIL Version 6.96 Calculated polar for: NASA SC(2)-0010 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.250 -1.0785 0.04676 0.04311 -0.0260 1.0000 0.0200 -12.000 -1.0927 0.04361 0.03974 -0.0237 1.0000 0.0201 -11.750 -1.0981 0.04142 0.03739 -0.0210 1.0000 0.0202 -11.500 -1.0933 0.03961 0.03544 -0.0193 1.0000 0.0205 -11.250 -1.0879 0.03752 0.03317 -0.0175 1.0000 0.0208 -11.000 -1.0825 0.03502 0.03041 -0.0157 1.0000 0.0210 -10.750 -1.0751 0.03238 0.02747 -0.0139 1.0000 0.0212 -10.500 -1.0634 0.03011 0.02492 -0.0124 1.0000 0.0214 -10.250 -1.0485 0.02815 0.02271 -0.0111 1.0000 0.0217 -10.000 -1.0314 0.02642 0.02076 -0.0100 1.0000 0.0220 -9.750 -1.0124 0.02490 0.01903 -0.0090 1.0000 0.0223 -9.500 -0.9921 0.02357 0.01752 -0.0082 1.0000 0.0227 -9.250 -0.9705 0.02244 0.01622 -0.0074 1.0000 0.0230 -9.000 -0.9482 0.02143 0.01507 -0.0067 1.0000 0.0233 -8.750 -0.9285 0.01968 0.01321 -0.0058 1.0000 0.0241 -8.500 -0.9054 0.01892 0.01244 -0.0053 1.0000 0.0248 -8.250 -0.8815 0.01829 0.01177 -0.0049 1.0000 0.0256 -8.000 -0.8576 0.01760 0.01102 -0.0043 1.0000 0.0265 -7.750 -0.8336 0.01690 0.01025 -0.0038 1.0000 0.0273 -7.500 -0.8090 0.01632 0.00958 -0.0033 1.0000 0.0281 -7.250 -0.7870 0.01529 0.00854 -0.0025 1.0000 0.0295 -7.000 -0.7623 0.01480 0.00806 -0.0021 1.0000 0.0310 -6.750 -0.7372 0.01436 0.00759 -0.0017 1.0000 0.0330 -6.500 -0.7135 0.01371 0.00691 -0.0011 1.0000 0.0354 -6.250 -0.6882 0.01337 0.00660 -0.0007 1.0000 0.0385 -6.000 -0.6637 0.01293 0.00614 -0.0002 1.0000 0.0423 -5.750 -0.6390 0.01260 0.00585 0.0003 1.0000 0.0463 -5.500 -0.6147 0.01231 0.00554 0.0009 1.0000 0.0499 -5.250 -0.5924 0.01187 0.00515 0.0018 1.0000 0.0544 -5.000 -0.5701 0.01167 0.00494 0.0028 1.0000 0.0580 -4.750 -0.5416 0.01125 0.00455 0.0023 0.9977 0.0631 -4.500 -0.5039 0.01096 0.00427 0.0000 0.9939 0.0690 -4.250 -0.4679 0.01056 0.00392 -0.0020 0.9876 0.0772 -4.000 -0.4319 0.01023 0.00362 -0.0039 0.9805 0.0871 -3.750 -0.3974 0.00985 0.00334 -0.0055 0.9714 0.1034 -3.500 -0.3663 0.00942 0.00307 -0.0064 0.9591 0.1374 -3.250 -0.3391 0.00886 0.00282 -0.0065 0.9450 0.2081 -3.000 -0.3150 0.00821 0.00257 -0.0060 0.9308 0.3097 -2.750 -0.2932 0.00734 0.00230 -0.0052 0.9176 0.4644 -2.500 -0.2720 0.00667 0.00224 -0.0038 0.9059 0.6249 -2.250 -0.2457 0.00661 0.00226 -0.0033 0.8945 0.6746 -2.000 -0.2188 0.00660 0.00225 -0.0029 0.8855 0.7013 -1.750 -0.1913 0.00660 0.00224 -0.0026 0.8772 0.7208 -1.500 -0.1637 0.00660 0.00224 -0.0023 0.8702 0.7353 -1.250 -0.1359 0.00658 0.00224 -0.0021 0.8622 0.7488 -1.000 -0.1086 0.00660 0.00223 -0.0017 0.8545 0.7614 -0.750 -0.0815 0.00659 0.00224 -0.0013 0.8441 0.7769 -0.500 -0.0547 0.00660 0.00226 -0.0007 0.8343 0.7932 -0.250 -0.0269 0.00662 0.00226 -0.0005 0.8263 0.8044 0.000 0.0000 0.00660 0.00228 0.0000 0.8158 0.8158 0.250 0.0269 0.00662 0.00227 0.0005 0.8045 0.8264 0.500 0.0547 0.00660 0.00226 0.0008 0.7930 0.8344 0.750 0.0815 0.00659 0.00224 0.0013 0.7771 0.8441 1.000 0.1086 0.00660 0.00223 0.0017 0.7614 0.8545 1.250 0.1359 0.00658 0.00224 0.0021 0.7487 0.8623 1.500 0.1637 0.00660 0.00224 0.0023 0.7353 0.8702 1.750 0.1912 0.00660 0.00224 0.0026 0.7208 0.8772 2.000 0.2187 0.00660 0.00225 0.0029 0.7014 0.8855 2.250 0.2457 0.00661 0.00226 0.0033 0.6746 0.8945 2.500 0.2719 0.00667 0.00224 0.0039 0.6249 0.9059 2.750 0.2932 0.00734 0.00230 0.0052 0.4640 0.9176 3.000 0.3150 0.00821 0.00257 0.0060 0.3096 0.9308 3.250 0.3391 0.00886 0.00282 0.0065 0.2082 0.9451 3.500 0.3663 0.00942 0.00307 0.0064 0.1374 0.9591 3.750 0.3974 0.00985 0.00334 0.0055 0.1033 0.9715 4.000 0.4320 0.01023 0.00362 0.0039 0.0871 0.9806 4.250 0.4680 0.01056 0.00392 0.0020 0.0772 0.9876 4.500 0.5040 0.01096 0.00427 0.0000 0.0690 0.9939 4.750 0.5417 0.01125 0.00455 -0.0023 0.0631 0.9978 5.000 0.5700 0.01167 0.00494 -0.0028 0.0580 1.0000 5.250 0.5924 0.01187 0.00515 -0.0018 0.0544 1.0000 5.500 0.6147 0.01231 0.00553 -0.0009 0.0499 1.0000 5.750 0.6390 0.01260 0.00585 -0.0003 0.0463 1.0000 6.000 0.6637 0.01293 0.00614 0.0002 0.0423 1.0000 6.250 0.6882 0.01337 0.00660 0.0007 0.0386 1.0000 6.500 0.7135 0.01371 0.00691 0.0011 0.0354 1.0000 6.750 0.7372 0.01436 0.00758 0.0017 0.0329 1.0000 7.000 0.7623 0.01480 0.00806 0.0021 0.0310 1.0000 7.250 0.7870 0.01529 0.00854 0.0025 0.0295 1.0000 7.500 0.8090 0.01632 0.00958 0.0033 0.0281 1.0000 7.750 0.8336 0.01690 0.01025 0.0038 0.0273 1.0000 8.000 0.8576 0.01760 0.01102 0.0043 0.0265 1.0000 8.250 0.8815 0.01830 0.01178 0.0049 0.0256 1.0000 8.500 0.9054 0.01892 0.01244 0.0053 0.0248 1.0000 8.750 0.9285 0.01967 0.01321 0.0058 0.0241 1.0000 9.000 0.9482 0.02144 0.01507 0.0067 0.0233 1.0000 9.250 0.9706 0.02244 0.01622 0.0074 0.0230 1.0000 9.500 0.9921 0.02357 0.01752 0.0082 0.0227 1.0000 9.750 1.0125 0.02490 0.01903 0.0090 0.0223 1.0000 10.000 1.0314 0.02642 0.02076 0.0100 0.0220 1.0000 10.250 1.0486 0.02815 0.02271 0.0111 0.0217 1.0000 10.500 1.0635 0.03012 0.02493 0.0124 0.0214 1.0000 10.750 1.0752 0.03238 0.02747 0.0139 0.0212 1.0000 11.000 1.0828 0.03501 0.03040 0.0157 0.0210 1.0000 11.250 1.0884 0.03748 0.03313 0.0175 0.0207 1.0000 11.500 1.0944 0.03950 0.03532 0.0192 0.0205 1.0000 11.750 1.0987 0.04140 0.03736 0.0209 0.0202 1.0000 12.000 1.0929 0.04365 0.03978 0.0237 0.0201 1.0000 12.250 1.0809 0.04657 0.04290 0.0259 0.0200 1.0000 12.500 0.6810 0.09468 0.09239 0.0075 0.0240 1.0000 12.750 0.6841 0.09713 0.09482 0.0065 0.0237 1.0000