XFOIL Version 6.96 Calculated polar for: NASA SC(2)-0012 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 ------ -------- --------- --------- -------- -------- -------- -11.500 -0.7111 0.10060 0.09259 -0.0151 1.0000 0.0702 -11.250 -0.7442 0.08936 0.08131 -0.0228 1.0000 0.0694 -11.000 -0.7825 0.08028 0.07210 -0.0282 1.0000 0.0686 -10.750 -0.8150 0.07383 0.06547 -0.0301 1.0000 0.0682 -10.500 -0.8411 0.06907 0.06051 -0.0294 1.0000 0.0683 -10.250 -0.8601 0.06509 0.05629 -0.0276 1.0000 0.0688 -10.000 -0.8724 0.06121 0.05211 -0.0258 1.0000 0.0698 -9.750 -0.8807 0.05740 0.04789 -0.0239 1.0000 0.0712 -9.500 -0.8858 0.05356 0.04352 -0.0217 1.0000 0.0727 -9.250 -0.8784 0.05061 0.04030 -0.0202 1.0000 0.0744 -9.000 -0.8641 0.04852 0.03811 -0.0193 1.0000 0.0766 -8.750 -0.8509 0.04631 0.03568 -0.0181 1.0000 0.0795 -8.500 -0.8386 0.04372 0.03262 -0.0166 1.0000 0.0828 -8.250 -0.8220 0.04142 0.03003 -0.0155 1.0000 0.0857 -8.000 -0.8023 0.03982 0.02839 -0.0148 1.0000 0.0894 -7.750 -0.7827 0.03800 0.02629 -0.0138 1.0000 0.0938 -7.500 -0.7613 0.03620 0.02424 -0.0131 1.0000 0.0980 -7.250 -0.7391 0.03485 0.02289 -0.0124 1.0000 0.1028 -7.000 -0.7157 0.03341 0.02119 -0.0117 1.0000 0.1083 -6.750 -0.6918 0.03210 0.01993 -0.0112 1.0000 0.1138 -6.500 -0.6675 0.03096 0.01868 -0.0106 1.0000 0.1206 -6.250 -0.6429 0.02984 0.01758 -0.0100 1.0000 0.1274 -6.000 -0.6194 0.02889 0.01659 -0.0092 1.0000 0.1360 -5.750 -0.5972 0.02793 0.01569 -0.0082 1.0000 0.1446 -5.500 -0.5768 0.02706 0.01483 -0.0070 1.0000 0.1559 -5.250 -0.5586 0.02620 0.01404 -0.0054 1.0000 0.1691 -5.000 -0.5430 0.02533 0.01331 -0.0036 1.0000 0.1855 -4.750 -0.5290 0.02445 0.01260 -0.0016 1.0000 0.2086 -4.500 -0.5169 0.02350 0.01193 0.0007 1.0000 0.2424 -4.250 -0.5073 0.02241 0.01129 0.0032 1.0000 0.2980 -4.000 -0.5006 0.02121 0.01083 0.0064 1.0000 0.3998 -3.750 -0.4907 0.02078 0.01152 0.0112 1.0000 0.5637 -3.500 -0.4790 0.02103 0.01187 0.0152 1.0000 0.6649 -3.250 -0.4667 0.02127 0.01207 0.0189 1.0000 0.7183 -3.000 -0.4517 0.02160 0.01238 0.0224 1.0000 0.7587 -2.750 -0.4351 0.02194 0.01266 0.0256 1.0000 0.7921 -2.500 -0.4157 0.02230 0.01294 0.0283 1.0000 0.8220 -2.250 -0.3895 0.02282 0.01339 0.0301 1.0000 0.8524 -2.000 -0.3559 0.02341 0.01389 0.0305 1.0000 0.8844 -1.750 -0.3017 0.02407 0.01440 0.0268 1.0000 0.9107 -1.500 -0.2565 0.02432 0.01451 0.0234 1.0000 0.9273 -1.250 -0.2187 0.02439 0.01447 0.0208 1.0000 0.9398 -1.000 -0.1737 0.02442 0.01441 0.0166 0.9971 0.9489 -0.750 -0.1292 0.02442 0.01432 0.0123 0.9921 0.9565 -0.500 -0.0855 0.02440 0.01424 0.0081 0.9868 0.9629 -0.250 -0.0430 0.02442 0.01423 0.0041 0.9822 0.9702 0.000 0.0000 0.02440 0.01420 0.0000 0.9761 0.9761 0.250 0.0430 0.02441 0.01423 -0.0041 0.9702 0.9822 0.500 0.0855 0.02440 0.01424 -0.0081 0.9629 0.9868 0.750 0.1292 0.02442 0.01432 -0.0123 0.9565 0.9922 1.000 0.1737 0.02442 0.01440 -0.0166 0.9489 0.9971 1.250 0.2187 0.02439 0.01447 -0.0208 0.9398 1.0000 1.500 0.2564 0.02432 0.01450 -0.0234 0.9273 1.0000 1.750 0.3017 0.02407 0.01439 -0.0268 0.9107 1.0000 2.000 0.3558 0.02341 0.01388 -0.0305 0.8845 1.0000 2.250 0.3894 0.02282 0.01339 -0.0301 0.8524 1.0000 2.500 0.4157 0.02230 0.01293 -0.0283 0.8220 1.0000 2.750 0.4350 0.02193 0.01265 -0.0255 0.7922 1.0000 3.000 0.4516 0.02160 0.01238 -0.0224 0.7587 1.0000 3.250 0.4666 0.02126 0.01207 -0.0189 0.7184 1.0000 3.500 0.4789 0.02102 0.01187 -0.0152 0.6650 1.0000 3.750 0.4906 0.02078 0.01152 -0.0112 0.5640 1.0000 4.000 0.5005 0.02121 0.01083 -0.0064 0.4000 1.0000 4.250 0.5072 0.02241 0.01129 -0.0032 0.2981 1.0000 4.500 0.5168 0.02350 0.01192 -0.0007 0.2425 1.0000 4.750 0.5289 0.02445 0.01259 0.0016 0.2086 1.0000 5.000 0.5429 0.02532 0.01331 0.0036 0.1855 1.0000 5.250 0.5586 0.02620 0.01403 0.0055 0.1691 1.0000 5.500 0.5767 0.02706 0.01483 0.0070 0.1559 1.0000 5.750 0.5972 0.02793 0.01569 0.0082 0.1446 1.0000 6.000 0.6194 0.02889 0.01658 0.0092 0.1360 1.0000 6.250 0.6429 0.02984 0.01757 0.0100 0.1274 1.0000 6.500 0.6675 0.03096 0.01868 0.0106 0.1206 1.0000 6.750 0.6918 0.03210 0.01993 0.0112 0.1138 1.0000 7.000 0.7157 0.03341 0.02119 0.0117 0.1083 1.0000 7.250 0.7392 0.03485 0.02289 0.0124 0.1028 1.0000 7.500 0.7613 0.03620 0.02424 0.0130 0.0980 1.0000 7.750 0.7827 0.03800 0.02629 0.0138 0.0938 1.0000 8.000 0.8024 0.03982 0.02839 0.0148 0.0894 1.0000 8.250 0.8221 0.04142 0.03002 0.0155 0.0857 1.0000 8.500 0.8387 0.04372 0.03263 0.0166 0.0828 1.0000 8.750 0.8510 0.04631 0.03568 0.0180 0.0795 1.0000 9.000 0.8642 0.04852 0.03811 0.0192 0.0766 1.0000 9.250 0.8786 0.05061 0.04030 0.0202 0.0744 1.0000 9.500 0.8859 0.05357 0.04353 0.0216 0.0727 1.0000 9.750 0.8809 0.05741 0.04790 0.0238 0.0712 1.0000 10.000 0.8726 0.06123 0.05213 0.0258 0.0698 1.0000 10.250 0.8604 0.06511 0.05631 0.0276 0.0688 1.0000 10.500 0.8415 0.06910 0.06054 0.0293 0.0683 1.0000 10.750 0.8154 0.07386 0.06550 0.0300 0.0682 1.0000 11.000 0.7830 0.08033 0.07215 0.0280 0.0686 1.0000 11.250 0.7447 0.08945 0.08140 0.0226 0.0694 1.0000 11.500 0.7117 0.10073 0.09272 0.0148 0.0702 1.0000