XFOIL Version 6.96 Calculated polar for: NACA 0012-34 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.250 -0.8029 0.06148 0.05877 -0.0435 1.0000 0.0034 -12.000 -0.8242 0.05564 0.05274 -0.0456 1.0000 0.0034 -11.750 -0.8456 0.05056 0.04744 -0.0458 1.0000 0.0034 -11.500 -0.8652 0.04623 0.04287 -0.0446 1.0000 0.0034 -11.250 -0.8836 0.04241 0.03879 -0.0420 1.0000 0.0034 -11.000 -0.9016 0.03892 0.03502 -0.0383 1.0000 0.0035 -10.750 -0.9116 0.03656 0.03245 -0.0344 1.0000 0.0036 -10.500 -0.9177 0.03488 0.03061 -0.0301 1.0000 0.0036 -10.250 -0.9204 0.03391 0.02954 -0.0257 1.0000 0.0037 -10.000 -0.9197 0.03276 0.02826 -0.0219 1.0000 0.0038 -9.750 -0.9173 0.03176 0.02713 -0.0181 1.0000 0.0039 -9.500 -0.9145 0.03069 0.02592 -0.0143 1.0000 0.0040 -9.250 -0.9120 0.02935 0.02441 -0.0103 1.0000 0.0042 -9.000 -0.8976 0.02743 0.02224 -0.0088 0.9987 0.0044 -8.750 -0.8766 0.02509 0.01959 -0.0084 0.9967 0.0045 -8.500 -0.8533 0.02313 0.01735 -0.0083 0.9951 0.0047 -8.250 -0.8298 0.02152 0.01553 -0.0082 0.9929 0.0050 -8.000 -0.8053 0.02019 0.01401 -0.0081 0.9906 0.0052 -7.750 -0.7790 0.01911 0.01278 -0.0084 0.9885 0.0054 -7.500 -0.7546 0.01769 0.01123 -0.0086 0.9867 0.0057 -7.250 -0.7296 0.01687 0.01032 -0.0087 0.9838 0.0061 -7.000 -0.7023 0.01630 0.00971 -0.0092 0.9810 0.0067 -6.750 -0.6736 0.01570 0.00905 -0.0099 0.9789 0.0074 -6.500 -0.6450 0.01502 0.00828 -0.0106 0.9770 0.0080 -6.250 -0.6201 0.01437 0.00755 -0.0104 0.9732 0.0085 -6.000 -0.5965 0.01352 0.00660 -0.0100 0.9691 0.0097 -5.750 -0.5681 0.01304 0.00608 -0.0105 0.9664 0.0111 -5.500 -0.5406 0.01266 0.00563 -0.0109 0.9631 0.0129 -5.250 -0.5159 0.01226 0.00515 -0.0104 0.9579 0.0148 -5.000 -0.4889 0.01182 0.00468 -0.0105 0.9541 0.0211 -4.750 -0.4618 0.01144 0.00432 -0.0106 0.9504 0.0331 -4.250 -0.4171 0.01023 0.00354 -0.0092 0.9393 0.1385 -4.000 -0.3981 0.00942 0.00316 -0.0080 0.9331 0.2434 -3.750 -0.3796 0.00859 0.00282 -0.0066 0.9267 0.3614 -3.500 -0.3602 0.00794 0.00256 -0.0053 0.9206 0.4588 -3.250 -0.3399 0.00746 0.00236 -0.0039 0.9137 0.5349 -3.000 -0.3172 0.00711 0.00220 -0.0030 0.9079 0.5924 -2.750 -0.2942 0.00687 0.00210 -0.0020 0.9008 0.6384 -2.500 -0.2683 0.00671 0.00198 -0.0017 0.8950 0.6670 -2.250 -0.2425 0.00661 0.00190 -0.0013 0.8874 0.6865 -2.000 -0.2157 0.00651 0.00181 -0.0011 0.8809 0.7056 -1.750 -0.1896 0.00643 0.00174 -0.0008 0.8726 0.7249 -1.500 -0.1629 0.00636 0.00168 -0.0006 0.8646 0.7419 -1.250 -0.1360 0.00631 0.00163 -0.0004 0.8560 0.7563 -1.000 -0.1090 0.00627 0.00159 -0.0003 0.8473 0.7692 -0.750 -0.0818 0.00624 0.00156 -0.0002 0.8391 0.7808 -0.500 -0.0546 0.00622 0.00154 -0.0001 0.8300 0.7916 -0.250 -0.0273 0.00621 0.00152 -0.0001 0.8211 0.8019 0.000 0.0000 0.00621 0.00151 0.0000 0.8120 0.8120 0.250 0.0273 0.00621 0.00152 0.0001 0.8019 0.8211 0.500 0.0546 0.00622 0.00154 0.0001 0.7916 0.8300 0.750 0.0818 0.00624 0.00156 0.0002 0.7809 0.8391 1.000 0.1091 0.00627 0.00159 0.0003 0.7693 0.8473 1.250 0.1360 0.00631 0.00163 0.0004 0.7563 0.8560 1.500 0.1629 0.00636 0.00168 0.0006 0.7419 0.8646 1.750 0.1896 0.00643 0.00174 0.0008 0.7249 0.8726 2.000 0.2157 0.00651 0.00181 0.0011 0.7055 0.8808 2.250 0.2425 0.00661 0.00190 0.0013 0.6865 0.8874 2.500 0.2683 0.00671 0.00198 0.0017 0.6672 0.8950 2.750 0.2942 0.00687 0.00210 0.0020 0.6382 0.9007 3.000 0.3172 0.00712 0.00220 0.0030 0.5922 0.9079 3.250 0.3399 0.00746 0.00236 0.0039 0.5347 0.9137 3.500 0.3603 0.00794 0.00256 0.0052 0.4590 0.9205 3.750 0.3797 0.00859 0.00282 0.0066 0.3616 0.9267 4.000 0.3981 0.00942 0.00316 0.0080 0.2425 0.9330 4.250 0.4171 0.01023 0.00354 0.0092 0.1379 0.9393 4.750 0.4619 0.01143 0.00432 0.0106 0.0330 0.9504 5.000 0.4889 0.01182 0.00468 0.0105 0.0211 0.9540 5.250 0.5160 0.01225 0.00514 0.0104 0.0149 0.9578 5.500 0.5408 0.01266 0.00563 0.0108 0.0129 0.9630 5.750 0.5682 0.01304 0.00607 0.0105 0.0111 0.9663 6.000 0.5966 0.01352 0.00660 0.0100 0.0097 0.9691 6.250 0.6201 0.01439 0.00757 0.0104 0.0085 0.9733 6.500 0.6451 0.01502 0.00828 0.0106 0.0080 0.9770 6.750 0.6738 0.01570 0.00905 0.0099 0.0074 0.9789 7.000 0.7026 0.01628 0.00969 0.0091 0.0066 0.9810 7.250 0.7297 0.01687 0.01032 0.0086 0.0061 0.9839 7.500 0.7549 0.01769 0.01123 0.0085 0.0057 0.9867 7.750 0.7792 0.01912 0.01279 0.0084 0.0054 0.9886 8.000 0.8055 0.02020 0.01402 0.0081 0.0052 0.9906 8.250 0.8301 0.02152 0.01553 0.0081 0.0050 0.9930 8.500 0.8536 0.02313 0.01735 0.0083 0.0047 0.9951 8.750 0.8770 0.02510 0.01959 0.0083 0.0045 0.9967 9.000 0.8979 0.02745 0.02226 0.0087 0.0044 0.9987 9.250 0.9117 0.02939 0.02446 0.0104 0.0042 1.0000 9.500 0.9147 0.03063 0.02586 0.0143 0.0040 1.0000 9.750 0.9175 0.03172 0.02709 0.0181 0.0039 1.0000 10.000 0.9190 0.03289 0.02841 0.0220 0.0038 1.0000 10.250 0.9201 0.03399 0.02963 0.0258 0.0037 1.0000 10.500 0.9179 0.03492 0.03065 0.0301 0.0036 1.0000 10.750 0.9123 0.03655 0.03244 0.0343 0.0036 1.0000 11.000 0.9017 0.03899 0.03510 0.0382 0.0035 1.0000 11.250 0.8849 0.04238 0.03876 0.0419 0.0034 1.0000 11.500 0.8658 0.04627 0.04291 0.0445 0.0034 1.0000 11.750 0.8459 0.05065 0.04753 0.0457 0.0034 1.0000 12.000 0.8246 0.05573 0.05283 0.0454 0.0034 1.0000 12.500 0.7833 0.06857 0.06605 0.0393 0.0035 1.0000 12.750 0.7451 0.08192 0.07965 0.0305 0.0036 1.0000