XFOIL Version 6.96 Calculated polar for: NASA SC(2)-0518 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 ------ -------- --------- --------- -------- -------- -------- -13.500 -0.6674 0.09721 0.09053 -0.0576 1.0000 0.1282 -13.250 -0.7426 0.08201 0.07513 -0.0646 1.0000 0.1254 -13.000 -0.8187 0.07098 0.06383 -0.0680 1.0000 0.1234 -12.750 -0.8722 0.06437 0.05697 -0.0680 1.0000 0.1225 -12.500 -0.9109 0.06009 0.05248 -0.0660 1.0000 0.1223 -12.250 -0.9432 0.05711 0.04933 -0.0624 1.0000 0.1224 -12.000 -0.9705 0.05472 0.04680 -0.0583 1.0000 0.1227 -11.750 -0.9877 0.05230 0.04418 -0.0553 1.0000 0.1234 -11.500 -0.9997 0.05007 0.04174 -0.0524 1.0000 0.1244 -11.250 -1.0082 0.04797 0.03937 -0.0496 1.0000 0.1257 -11.000 -1.0140 0.04601 0.03708 -0.0470 1.0000 0.1271 -10.750 -1.0064 0.04396 0.03492 -0.0452 1.0000 0.1289 -10.500 -0.9925 0.04258 0.03358 -0.0438 1.0000 0.1310 -10.250 -0.9796 0.04134 0.03232 -0.0422 1.0000 0.1333 -10.000 -0.9687 0.04001 0.03087 -0.0406 1.0000 0.1357 -9.750 -0.9584 0.03864 0.02926 -0.0392 1.0000 0.1383 -9.500 -0.9461 0.03724 0.02763 -0.0379 1.0000 0.1407 -9.250 -0.9283 0.03603 0.02656 -0.0365 1.0000 0.1435 -9.000 -0.9119 0.03509 0.02563 -0.0353 1.0000 0.1465 -8.750 -0.8956 0.03415 0.02459 -0.0342 1.0000 0.1501 -8.500 -0.8788 0.03323 0.02344 -0.0333 1.0000 0.1535 -8.250 -0.8602 0.03225 0.02265 -0.0318 1.0000 0.1571 -8.000 -0.8420 0.03153 0.02200 -0.0307 1.0000 0.1613 -7.750 -0.8235 0.03081 0.02116 -0.0298 1.0000 0.1662 -7.500 -0.8053 0.03003 0.02049 -0.0285 1.0000 0.1710 -7.250 -0.7870 0.02942 0.01999 -0.0273 1.0000 0.1765 -7.000 -0.7674 0.02884 0.01931 -0.0266 1.0000 0.1830 -6.750 -0.7501 0.02820 0.01893 -0.0251 1.0000 0.1901 -6.500 -0.7303 0.02766 0.01839 -0.0245 1.0000 0.1995 -6.250 -0.7119 0.02707 0.01804 -0.0235 1.0000 0.2099 -6.000 -0.6923 0.02649 0.01766 -0.0228 1.0000 0.2235 -5.750 -0.6711 0.02585 0.01727 -0.0227 1.0000 0.2433 -5.500 -0.6468 0.02496 0.01678 -0.0237 1.0000 0.2779 -5.250 -0.6134 0.02334 0.01634 -0.0274 1.0000 0.3923 -5.000 -0.6041 0.02468 0.01845 -0.0222 1.0000 0.4942 -4.750 -0.5669 0.02597 0.01965 -0.0241 0.9964 0.5517 -4.500 -0.5331 0.02795 0.02158 -0.0236 0.9912 0.5740 -4.250 -0.5059 0.02959 0.02317 -0.0220 0.9846 0.5897 -4.000 -0.4796 0.03170 0.02529 -0.0190 0.9789 0.5981 -3.750 -0.4501 0.03278 0.02630 -0.0190 0.9733 0.6135 -3.500 -0.4306 0.03471 0.02825 -0.0144 0.9668 0.6186 -3.250 -0.3931 0.03590 0.02936 -0.0156 0.9621 0.6342 -3.000 -0.3831 0.03734 0.03084 -0.0097 0.9552 0.6389 -2.750 -0.3489 0.03789 0.03130 -0.0115 0.9499 0.6547 -2.500 -0.3266 0.03930 0.03273 -0.0075 0.9445 0.6596 -2.250 -0.3006 0.03951 0.03289 -0.0086 0.9374 0.6751 -2.000 -0.2791 0.04091 0.03433 -0.0036 0.9320 0.6816 -1.750 -0.2533 0.04157 0.03496 -0.0035 0.9258 0.6988 -1.500 -0.2390 0.04256 0.03600 0.0024 0.9189 0.7075 -1.250 -0.2037 0.04289 0.03629 0.0009 0.9136 0.7230 -1.000 -0.1852 0.04318 0.03659 0.0038 0.9066 0.7309 -0.750 -0.1574 0.04298 0.03635 0.0012 0.8985 0.7429 -0.500 -0.1185 0.04297 0.03635 0.0014 0.8937 0.7492 -0.250 -0.1060 0.04286 0.03624 0.0032 0.8828 0.7577 0.000 -0.0646 0.04252 0.03588 0.0005 0.8758 0.7665 0.250 -0.0456 0.04237 0.03576 0.0023 0.8659 0.7730 0.500 -0.0060 0.04194 0.03532 -0.0006 0.8571 0.7796 0.750 0.0233 0.04155 0.03492 -0.0023 0.8463 0.7846 1.000 0.0622 0.04083 0.03423 -0.0028 0.8371 0.7896 1.250 0.0933 0.04032 0.03374 -0.0033 0.8255 0.7948 1.500 0.1516 0.03910 0.03253 -0.0081 0.8155 0.7985 1.750 0.1858 0.03841 0.03185 -0.0100 0.8013 0.8021 2.000 0.2630 0.03619 0.02968 -0.0152 0.7949 0.8062 2.250 0.2971 0.03513 0.02866 -0.0154 0.7818 0.8090 2.500 0.3653 0.03314 0.02671 -0.0203 0.7743 0.8129 2.750 0.3927 0.03227 0.02588 -0.0200 0.7598 0.8154 3.000 0.4445 0.03064 0.02427 -0.0230 0.7469 0.8173 3.250 0.4886 0.02923 0.02286 -0.0249 0.7297 0.8189 3.500 0.5167 0.02837 0.02202 -0.0248 0.7074 0.8203 3.750 0.5407 0.02745 0.02112 -0.0233 0.6817 0.8225 4.000 0.5659 0.02653 0.02018 -0.0217 0.6495 0.8250 4.250 0.5855 0.02592 0.01949 -0.0196 0.6033 0.8270 4.500 0.6026 0.02555 0.01878 -0.0172 0.5232 0.8289 4.750 0.6096 0.02603 0.01850 -0.0135 0.4156 0.8312 5.000 0.6166 0.02697 0.01881 -0.0108 0.3435 0.8331 5.250 0.6316 0.02781 0.01925 -0.0096 0.2966 0.8344 5.500 0.6531 0.02861 0.01974 -0.0096 0.2654 0.8362 5.750 0.6801 0.02943 0.02031 -0.0106 0.2423 0.8386 6.000 0.7011 0.02986 0.02062 -0.0097 0.2266 0.8405 6.250 0.7271 0.03046 0.02111 -0.0099 0.2130 0.8421 6.500 0.7563 0.03119 0.02166 -0.0107 0.2019 0.8438 6.750 0.7844 0.03179 0.02224 -0.0114 0.1920 0.8456 7.000 0.8163 0.03266 0.02305 -0.0127 0.1836 0.8476 7.250 0.8474 0.03343 0.02376 -0.0140 0.1758 0.8496 7.500 0.8814 0.03451 0.02481 -0.0159 0.1690 0.8518 7.750 0.9128 0.03544 0.02582 -0.0174 0.1626 0.8545 8.000 0.9452 0.03659 0.02675 -0.0186 0.1572 0.8572 8.250 0.9647 0.03729 0.02774 -0.0175 0.1527 0.8600 8.500 0.9904 0.03821 0.02874 -0.0178 0.1480 0.8625 8.750 1.0258 0.03974 0.03005 -0.0199 0.1435 0.8650 9.000 1.0450 0.04088 0.03160 -0.0193 0.1399 0.8676 9.250 1.0713 0.04228 0.03316 -0.0201 0.1360 0.8701 9.500 1.0965 0.04339 0.03426 -0.0204 0.1327 0.8727 9.750 1.1181 0.04509 0.03603 -0.0202 0.1298 0.8756 10.000 1.1274 0.04672 0.03808 -0.0182 0.1273 0.8789 10.250 1.1415 0.04859 0.04023 -0.0173 0.1248 0.8826 10.500 1.1632 0.05037 0.04212 -0.0176 0.1223 0.8862 10.750 1.1853 0.05169 0.04338 -0.0174 0.1200 0.8899 11.000 1.1934 0.05422 0.04615 -0.0159 0.1182 0.8933 11.250 1.1845 0.05691 0.04932 -0.0128 0.1169 0.8964 11.500 1.1721 0.05985 0.05267 -0.0097 0.1159 0.8994 11.750 1.1546 0.06306 0.05624 -0.0064 0.1152 0.9024 12.000 1.1318 0.06691 0.06043 -0.0036 0.1149 0.9054 12.250 1.1013 0.07176 0.06564 -0.0017 0.1149 0.9082 12.500 1.0603 0.07815 0.07239 -0.0013 0.1154 0.9103 12.750 1.0049 0.08712 0.08172 -0.0034 0.1165 0.9115 13.000 0.9510 0.09810 0.09296 -0.0081 0.1179 0.9122 13.250 0.9227 0.10769 0.10268 -0.0128 0.1188 0.9137