XFOIL Version 6.96 Calculated polar for: NASA SC(2)-0714 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 ------ -------- --------- --------- -------- -------- -------- -11.750 -0.6453 0.09096 0.08500 -0.0551 1.0000 0.1158 -11.500 -0.7461 0.07622 0.07006 -0.0586 1.0000 0.1021 -11.250 -0.7616 0.07243 0.06627 -0.0568 1.0000 0.1010 -11.000 -0.7922 0.06908 0.06288 -0.0537 1.0000 0.1000 -10.750 -0.8216 0.06474 0.05843 -0.0523 1.0000 0.0987 -10.500 -0.8457 0.05988 0.05330 -0.0518 1.0000 0.0974 -10.250 -0.8564 0.05552 0.04862 -0.0514 1.0000 0.0971 -10.000 -0.8569 0.05164 0.04442 -0.0514 1.0000 0.0975 -9.750 -0.8503 0.04806 0.04047 -0.0516 1.0000 0.0984 -9.500 -0.8382 0.04467 0.03668 -0.0520 1.0000 0.0993 -9.250 -0.8215 0.04158 0.03316 -0.0526 1.0000 0.1004 -9.000 -0.8009 0.03902 0.03013 -0.0534 1.0000 0.1022 -8.750 -0.7798 0.03657 0.02746 -0.0537 1.0000 0.1047 -8.500 -0.7584 0.03509 0.02599 -0.0534 1.0000 0.1076 -8.250 -0.7353 0.03362 0.02438 -0.0533 1.0000 0.1106 -8.000 -0.7105 0.03218 0.02267 -0.0534 1.0000 0.1141 -7.750 -0.6861 0.03070 0.02104 -0.0535 1.0000 0.1180 -7.500 -0.6628 0.02965 0.02005 -0.0531 1.0000 0.1224 -7.250 -0.6379 0.02870 0.01899 -0.0529 1.0000 0.1274 -7.000 -0.6137 0.02764 0.01790 -0.0524 1.0000 0.1329 -6.750 -0.5901 0.02683 0.01719 -0.0519 1.0000 0.1392 -6.500 -0.5647 0.02608 0.01633 -0.0517 1.0000 0.1467 -6.250 -0.5418 0.02528 0.01576 -0.0509 1.0000 0.1554 -6.000 -0.5176 0.02456 0.01513 -0.0504 1.0000 0.1658 -5.750 -0.4924 0.02392 0.01462 -0.0502 1.0000 0.1805 -5.500 -0.4664 0.02321 0.01419 -0.0502 1.0000 0.2008 -5.250 -0.4364 0.02235 0.01374 -0.0513 1.0000 0.2410 -5.000 -0.4045 0.02114 0.01457 -0.0527 1.0000 0.4733 -4.750 -0.3999 0.02290 0.01658 -0.0455 1.0000 0.5681 -4.500 -0.3824 0.02432 0.01790 -0.0422 1.0000 0.6055 -4.250 -0.3713 0.02570 0.01924 -0.0372 1.0000 0.6245 -4.000 -0.3599 0.02693 0.02043 -0.0324 1.0000 0.6404 -3.750 -0.3462 0.02796 0.02139 -0.0285 1.0000 0.6557 -3.500 -0.3294 0.02882 0.02220 -0.0256 1.0000 0.6715 -3.250 -0.3266 0.02972 0.02312 -0.0186 1.0000 0.6788 -3.000 -0.3116 0.03038 0.02375 -0.0154 1.0000 0.6934 -2.750 -0.2929 0.03101 0.02432 -0.0134 1.0000 0.7097 -2.500 -0.2910 0.03143 0.02478 -0.0066 1.0000 0.7178 -2.250 -0.2751 0.03179 0.02511 -0.0040 1.0000 0.7324 -1.750 -0.2520 0.03241 0.02572 0.0034 1.0000 0.7625 -1.500 -0.2411 0.03272 0.02604 0.0073 1.0000 0.7820 -1.250 -0.2347 0.03272 0.02605 0.0122 1.0000 0.8004 -1.000 -0.2216 0.03269 0.02602 0.0149 1.0000 0.8161 -0.750 -0.2123 0.03218 0.02552 0.0184 1.0000 0.8251 -0.500 -0.1834 0.03233 0.02564 0.0163 1.0000 0.8326 -0.250 -0.1686 0.03197 0.02528 0.0181 1.0000 0.8386 0.000 -0.1280 0.03230 0.02559 0.0141 0.9946 0.8448 0.250 -0.0803 0.03256 0.02585 0.0092 0.9841 0.8499 0.500 -0.0384 0.03264 0.02594 0.0057 0.9729 0.8542 0.750 0.0065 0.03284 0.02615 0.0013 0.9615 0.8583 1.000 0.0574 0.03310 0.02643 -0.0042 0.9493 0.8616 1.250 0.1053 0.03291 0.02628 -0.0083 0.9351 0.8647 1.500 0.1547 0.03249 0.02591 -0.0123 0.9194 0.8677 1.750 0.2056 0.03179 0.02529 -0.0161 0.9008 0.8706 2.000 0.2602 0.03078 0.02435 -0.0201 0.8810 0.8732 2.250 0.3148 0.02965 0.02331 -0.0239 0.8629 0.8757 2.500 0.3650 0.02833 0.02210 -0.0266 0.8454 0.8781 2.750 0.4088 0.02666 0.02056 -0.0276 0.8264 0.8806 3.000 0.4535 0.02496 0.01898 -0.0286 0.8063 0.8823 3.250 0.4928 0.02341 0.01756 -0.0288 0.7772 0.8833 3.500 0.5320 0.02196 0.01615 -0.0287 0.7222 0.8845 3.750 0.5977 0.02179 0.01420 -0.0322 0.4061 0.8865 4.000 0.6065 0.02351 0.01484 -0.0296 0.2659 0.8878 4.250 0.6280 0.02467 0.01554 -0.0292 0.2160 0.8887 4.500 0.6544 0.02571 0.01627 -0.0297 0.1908 0.8894 4.750 0.6852 0.02671 0.01711 -0.0308 0.1734 0.8902 5.000 0.7188 0.02781 0.01800 -0.0325 0.1598 0.8911 5.250 0.7499 0.02855 0.01881 -0.0334 0.1501 0.8926 5.500 0.7823 0.02966 0.01978 -0.0346 0.1420 0.8944 5.750 0.8126 0.03048 0.02072 -0.0353 0.1346 0.8958 6.000 0.8485 0.03202 0.02207 -0.0374 0.1280 0.8969 6.250 0.8777 0.03296 0.02329 -0.0379 0.1225 0.8980 6.500 0.9084 0.03412 0.02448 -0.0389 0.1173 0.8991 6.750 0.9398 0.03594 0.02635 -0.0402 0.1128 0.9003 7.000 0.9666 0.03746 0.02824 -0.0404 0.1091 0.9017 7.250 0.9946 0.03899 0.02990 -0.0409 0.1053 0.9035 7.500 1.0249 0.04110 0.03195 -0.0424 0.1017 0.9053 7.750 1.0429 0.04326 0.03457 -0.0412 0.0996 0.9068 8.000 1.0593 0.04571 0.03750 -0.0398 0.0981 0.9081 8.250 1.0731 0.04844 0.04068 -0.0383 0.0966 0.9093 8.500 1.0846 0.05122 0.04385 -0.0367 0.0951 0.9105 8.750 1.0956 0.05395 0.04689 -0.0353 0.0934 0.9119 9.000 1.1037 0.05709 0.05034 -0.0338 0.0925 0.9132 9.250 1.0918 0.06210 0.05593 -0.0303 0.0938 0.9143 9.500 1.0713 0.06752 0.06186 -0.0267 0.0958 0.9154 9.750 1.0502 0.07233 0.06700 -0.0235 0.0976 0.9167 10.000 1.0366 0.07724 0.07211 -0.0219 0.0992 0.9182 10.250 1.0451 0.08231 0.07723 -0.0222 0.1005 0.9198