XFOIL Version 6.96 Calculated polar for: NASA SC(2)-0712 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.250 -1.0340 0.09184 0.08810 -0.0469 1.0000 0.0182 -18.000 -1.0600 0.08296 0.07905 -0.0521 1.0000 0.0182 -17.750 -1.0794 0.07551 0.07144 -0.0565 1.0000 0.0182 -17.500 -1.0938 0.06919 0.06497 -0.0602 1.0000 0.0183 -17.250 -1.1044 0.06378 0.05942 -0.0633 1.0000 0.0184 -17.000 -1.1120 0.05910 0.05462 -0.0658 1.0000 0.0185 -16.750 -1.1174 0.05503 0.05043 -0.0678 1.0000 0.0187 -16.500 -1.1206 0.05145 0.04674 -0.0693 1.0000 0.0188 -16.250 -1.1224 0.04830 0.04346 -0.0704 1.0000 0.0190 -16.000 -1.1231 0.04549 0.04055 -0.0712 1.0000 0.0191 -15.750 -1.1225 0.04296 0.03791 -0.0716 1.0000 0.0193 -15.500 -1.1208 0.04068 0.03553 -0.0717 1.0000 0.0195 -15.250 -1.1183 0.03861 0.03336 -0.0716 1.0000 0.0198 -15.000 -1.1152 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0.8203 0.6516 -0.750 0.4550 0.00754 0.00270 -0.1249 0.7797 0.6549 -0.500 0.4804 0.00784 0.00274 -0.1240 0.7152 0.6576 -0.250 0.5009 0.00863 0.00292 -0.1223 0.5818 0.6601 0.000 0.5223 0.00953 0.00321 -0.1212 0.4500 0.6624 0.250 0.5457 0.01030 0.00347 -0.1205 0.3345 0.6645 0.500 0.5708 0.01091 0.00369 -0.1201 0.2501 0.6666 0.750 0.5972 0.01137 0.00387 -0.1199 0.1931 0.6685 1.000 0.6238 0.01173 0.00407 -0.1196 0.1556 0.6704 1.250 0.6507 0.01204 0.00427 -0.1194 0.1292 0.6723 1.500 0.6779 0.01231 0.00447 -0.1192 0.1119 0.6742 1.750 0.7053 0.01256 0.00467 -0.1191 0.0983 0.6763 2.000 0.7327 0.01282 0.00487 -0.1189 0.0873 0.6785 2.250 0.7601 0.01308 0.00508 -0.1187 0.0785 0.6805 2.500 0.7874 0.01335 0.00530 -0.1186 0.0709 0.6825 2.750 0.8150 0.01358 0.00552 -0.1184 0.0656 0.6845 3.250 0.8690 0.01412 0.00601 -0.1180 0.0558 0.6881 3.500 0.8956 0.01441 0.00630 -0.1176 0.0521 0.6898 3.750 0.9223 0.01468 0.00658 -0.1173 0.0491 0.6916 4.000 0.9486 0.01501 0.00689 -0.1169 0.0461 0.6936 4.250 0.9750 0.01531 0.00720 -0.1165 0.0438 0.6956 4.500 1.0014 0.01562 0.00752 -0.1162 0.0417 0.6978 4.750 1.0273 0.01598 0.00787 -0.1157 0.0397 0.7000 5.000 1.0533 0.01633 0.00823 -0.1153 0.0381 0.7022 5.250 1.0792 0.01666 0.00858 -0.1149 0.0364 0.7043 5.500 1.1044 0.01702 0.00897 -0.1143 0.0350 0.7063 5.750 1.1290 0.01747 0.00943 -0.1136 0.0337 0.7083 6.000 1.1539 0.01786 0.00987 -0.1130 0.0327 0.7104 6.250 1.1787 0.01825 0.01031 -0.1123 0.0316 0.7128 6.500 1.2033 0.01865 0.01074 -0.1117 0.0304 0.7154 6.750 1.2275 0.01911 0.01120 -0.1110 0.0294 0.7181 7.000 1.2509 0.01965 0.01176 -0.1101 0.0284 0.7206 7.250 1.2747 0.02010 0.01228 -0.1093 0.0277 0.7226 7.500 1.2979 0.02057 0.01282 -0.1084 0.0269 0.7245 7.750 1.3208 0.02106 0.01338 -0.1075 0.0262 0.7265 8.000 1.3434 0.02157 0.01394 -0.1065 0.0255 0.7287 8.250 1.3653 0.02214 0.01454 -0.1054 0.0248 0.7310 8.500 1.3857 0.02285 0.01528 -0.1041 0.0242 0.7334 8.750 1.4072 0.02342 0.01594 -0.1030 0.0237 0.7358 9.000 1.4281 0.02403 0.01661 -0.1018 0.0232 0.7381 9.250 1.4483 0.02463 0.01729 -0.1004 0.0226 0.7401 9.500 1.4679 0.02524 0.01799 -0.0990 0.0220 0.7421 9.750 1.4868 0.02587 0.01869 -0.0975 0.0215 0.7443 10.000 1.5045 0.02656 0.01944 -0.0958 0.0211 0.7465 10.250 1.5201 0.02735 0.02029 -0.0938 0.0207 0.7491 10.500 1.5330 0.02829 0.02129 -0.0914 0.0204 0.7518 10.750 1.5456 0.02909 0.02220 -0.0888 0.0201 0.7545 11.000 1.5566 0.02995 0.02318 -0.0861 0.0198 0.7568 11.250 1.5678 0.03090 0.02425 -0.0835 0.0196 0.7590 11.500 1.5787 0.03191 0.02539 -0.0810 0.0193 0.7612 11.750 1.5887 0.03300 0.02659 -0.0785 0.0190 0.7636 12.000 1.5982 0.03413 0.02784 -0.0760 0.0187 0.7662 12.250 1.6067 0.03536 0.02917 -0.0736 0.0185 0.7689 12.500 1.6143 0.03667 0.03059 -0.0712 0.0183 0.7716 12.750 1.6211 0.03806 0.03209 -0.0688 0.0181 0.7739 13.000 1.6264 0.03958 0.03373 -0.0664 0.0179 0.7760 13.250 1.6306 0.04124 0.03551 -0.0641 0.0177 0.7783 13.500 1.6333 0.04310 0.03749 -0.0619 0.0175 0.7806 13.750 1.6340 0.04520 0.03970 -0.0599 0.0174 0.7830 14.000 1.6324 0.04762 0.04224 -0.0579 0.0172 0.7853 14.250 1.6285 0.05040 0.04514 -0.0563 0.0171 0.7875 14.500 1.6213 0.05366 0.04854 -0.0549 0.0170 0.7894 14.750 1.6158 0.05696 0.05202 -0.0540 0.0169 0.7912 15.000 1.6076 0.06079 0.05603 -0.0536 0.0168 0.7930 15.250 1.5979 0.06508 0.06051 -0.0538 0.0167 0.7950 15.500 1.5848 0.07023 0.06586 -0.0549 0.0166 0.7970 15.750 1.5694 0.07628 0.07210 -0.0570 0.0166 0.7989 16.000 1.5501 0.08357 0.07960 -0.0605 0.0165 0.8006 16.250 1.5263 0.09235 0.08860 -0.0654 0.0165 0.8020 16.500 1.4951 0.10329 0.09977 -0.0721 0.0165 0.8029 16.750 1.4553 0.11643 0.11315 -0.0803 0.0166 0.8034 17.000 1.4074 0.13174 0.12870 -0.0901 0.0166 0.8034