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 = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.2574 0.07089 0.06684 -0.0687 1.0000 0.0193 -19.500 -1.2653 0.06638 0.06222 -0.0708 1.0000 0.0194 -19.250 -1.2703 0.06238 0.05813 -0.0726 1.0000 0.0196 -19.000 -1.2730 0.05881 0.05447 -0.0741 1.0000 0.0197 -18.750 -1.2740 0.05560 0.05117 -0.0753 1.0000 0.0199 -18.500 -1.2734 0.05269 0.04818 -0.0763 1.0000 0.0200 -18.250 -1.2713 0.05005 0.04546 -0.0770 1.0000 0.0202 -18.000 -1.2683 0.04761 0.04295 -0.0776 1.0000 0.0203 -17.750 -1.2643 0.04542 0.04067 -0.0779 1.0000 0.0205 -17.500 -1.2595 0.04339 0.03858 -0.0780 1.0000 0.0206 -17.250 -1.2549 0.04148 0.03660 -0.0779 1.0000 0.0207 -17.000 -1.2526 0.03950 0.03456 -0.0776 1.0000 0.0209 -16.750 -1.2504 0.03766 0.03267 -0.0769 1.0000 0.0212 -16.500 -1.2473 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0.6412 2.750 0.8648 0.01220 0.00487 -0.1348 0.0606 0.6423 3.000 0.8925 0.01239 0.00505 -0.1346 0.0576 0.6434 3.250 0.9199 0.01261 0.00524 -0.1344 0.0544 0.6446 3.500 0.9473 0.01281 0.00543 -0.1342 0.0524 0.6457 3.750 0.9746 0.01302 0.00563 -0.1340 0.0504 0.6469 4.000 1.0016 0.01326 0.00583 -0.1337 0.0484 0.6480 4.250 1.0286 0.01349 0.00605 -0.1334 0.0469 0.6491 4.500 1.0555 0.01371 0.00628 -0.1330 0.0454 0.6501 4.750 1.0821 0.01396 0.00651 -0.1327 0.0438 0.6511 5.000 1.1084 0.01423 0.00676 -0.1322 0.0423 0.6521 5.250 1.1347 0.01448 0.00702 -0.1318 0.0412 0.6534 5.500 1.1610 0.01471 0.00727 -0.1314 0.0402 0.6549 5.750 1.1870 0.01497 0.00754 -0.1309 0.0390 0.6562 6.000 1.2127 0.01525 0.00783 -0.1304 0.0377 0.6575 6.250 1.2378 0.01557 0.00815 -0.1297 0.0364 0.6587 6.500 1.2634 0.01583 0.00843 -0.1292 0.0355 0.6600 6.750 1.2886 0.01611 0.00873 -0.1285 0.0342 0.6613 7.000 1.3134 0.01642 0.00904 -0.1279 0.0329 0.6626 7.250 1.3376 0.01677 0.00938 -0.1271 0.0316 0.6639 7.500 1.3620 0.01708 0.00972 -0.1263 0.0308 0.6652 7.750 1.3860 0.01741 0.01007 -0.1255 0.0298 0.6665 8.000 1.4095 0.01776 0.01043 -0.1245 0.0288 0.6677 8.250 1.4325 0.01815 0.01081 -0.1235 0.0279 0.6690 8.500 1.4551 0.01855 0.01123 -0.1225 0.0272 0.6703 8.750 1.4774 0.01893 0.01164 -0.1213 0.0266 0.6717 9.000 1.4991 0.01932 0.01207 -0.1201 0.0260 0.6735 9.250 1.5202 0.01974 0.01252 -0.1188 0.0253 0.6751 9.500 1.5407 0.02018 0.01299 -0.1173 0.0247 0.6767 9.750 1.5602 0.02066 0.01349 -0.1157 0.0241 0.6782 10.000 1.5787 0.02119 0.01405 -0.1140 0.0235 0.6799 10.250 1.5971 0.02166 0.01457 -0.1122 0.0232 0.6815 10.500 1.6124 0.02214 0.01510 -0.1098 0.0229 0.6832 10.750 1.6287 0.02267 0.01568 -0.1077 0.0226 0.6848 11.000 1.6451 0.02324 0.01629 -0.1056 0.0223 0.6864 11.250 1.6615 0.02383 0.01693 -0.1036 0.0220 0.6878 11.500 1.6772 0.02447 0.01761 -0.1016 0.0217 0.6891 11.750 1.6926 0.02514 0.01833 -0.0995 0.0214 0.6907 12.000 1.7074 0.02585 0.01910 -0.0974 0.0211 0.6928 12.250 1.7214 0.02661 0.01992 -0.0953 0.0208 0.6949 12.500 1.7344 0.02745 0.02081 -0.0930 0.0205 0.6970 12.750 1.7464 0.02837 0.02180 -0.0907 0.0202 0.6989 13.000 1.7572 0.02937 0.02286 -0.0883 0.0200 0.7008 13.250 1.7693 0.03027 0.02384 -0.0861 0.0198 0.7027 13.500 1.7810 0.03122 0.02487 -0.0839 0.0197 0.7046 13.750 1.7918 0.03225 0.02596 -0.0818 0.0196 0.7063 14.000 1.8017 0.03335 0.02714 -0.0795 0.0194 0.7079 14.250 1.8113 0.03450 0.02836 -0.0774 0.0192 0.7093 14.500 1.8198 0.03575 0.02970 -0.0753 0.0191 0.7113 14.750 1.8281 0.03705 0.03108 -0.0732 0.0188 0.7133 15.000 1.8351 0.03847 0.03260 -0.0711 0.0187 0.7154 15.250 1.8409 0.04003 0.03424 -0.0691 0.0185 0.7174 15.500 1.8459 0.04171 0.03601 -0.0671 0.0183 0.7195 15.750 1.8497 0.04355 0.03794 -0.0653 0.0182 0.7217 16.000 1.8523 0.04554 0.04002 -0.0635 0.0180 0.7238 16.250 1.8535 0.04773 0.04230 -0.0619 0.0179 0.7258 16.500 1.8535 0.05015 0.04482 -0.0604 0.0178 0.7275 17.000 1.8497 0.05580 0.05068 -0.0583 0.0175 0.7308 17.250 1.8452 0.05913 0.05412 -0.0577 0.0174 0.7326 17.500 1.8383 0.06296 0.05807 -0.0575 0.0173 0.7343 17.750 1.8294 0.06729 0.06253 -0.0578 0.0172 0.7360 18.000 1.8178 0.07226 0.06764 -0.0587 0.0171 0.7376 18.250 1.8023 0.07808 0.07361 -0.0604 0.0170 0.7391 18.500 1.7829 0.08484 0.08053 -0.0629 0.0170 0.7403 18.750 1.7594 0.09266 0.08852 -0.0664 0.0169 0.7414 19.000 1.7294 0.10198 0.09802 -0.0712 0.0169 0.7422 19.250 1.6939 0.11256 0.10881 -0.0770 0.0169 0.7428