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 = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.0323 0.10690 0.10290 -0.0508 1.0000 0.0236 -19.500 -1.0544 0.09904 0.09488 -0.0551 1.0000 0.0237 -19.250 -1.0727 0.09207 0.08776 -0.0589 1.0000 0.0238 -19.000 -1.0876 0.08579 0.08133 -0.0623 1.0000 0.0239 -18.750 -1.0997 0.08016 0.07557 -0.0652 1.0000 0.0240 -18.500 -1.1090 0.07512 0.07039 -0.0677 1.0000 0.0241 -18.250 -1.1161 0.07055 0.06569 -0.0699 1.0000 0.0242 -18.000 -1.1217 0.06639 0.06142 -0.0718 1.0000 0.0244 -17.750 -1.1271 0.06242 0.05737 -0.0734 1.0000 0.0246 -17.500 -1.1304 0.05887 0.05374 -0.0747 1.0000 0.0247 -17.250 -1.1321 0.05569 0.05048 -0.0758 1.0000 0.0249 -17.000 -1.1323 0.05283 0.04755 -0.0765 1.0000 0.0252 -16.750 -1.1314 0.05024 0.04489 -0.0769 1.0000 0.0254 -16.500 -1.1296 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0.00739 -0.0980 0.9566 0.0629 -7.000 -0.3612 0.01359 0.00703 -0.1002 0.9558 0.0672 -6.750 -0.3262 0.01326 0.00671 -0.1022 0.9551 0.0717 -6.500 -0.2905 0.01289 0.00639 -0.1045 0.9543 0.0778 -6.250 -0.2546 0.01254 0.00610 -0.1067 0.9536 0.0854 -6.000 -0.2248 0.01230 0.00588 -0.1076 0.9507 0.0929 -5.750 -0.1931 0.01202 0.00565 -0.1088 0.9483 0.1024 -5.500 -0.1593 0.01171 0.00542 -0.1106 0.9466 0.1148 -5.250 -0.1243 0.01138 0.00519 -0.1126 0.9451 0.1333 -5.000 -0.0883 0.01102 0.00495 -0.1149 0.9438 0.1579 -4.750 -0.0509 0.01062 0.00470 -0.1175 0.9427 0.1930 -4.500 -0.0118 0.01014 0.00444 -0.1207 0.9418 0.2404 -4.250 0.0316 0.00947 0.00410 -0.1251 0.9413 0.3213 -4.000 0.0792 0.00864 0.00372 -0.1307 0.9412 0.4346 -3.750 0.1210 0.00820 0.00368 -0.1343 0.9405 0.5349 -3.500 0.1547 0.00816 0.00373 -0.1354 0.9391 0.5664 -3.250 0.1874 0.00816 0.00373 -0.1363 0.9375 0.5805 -3.000 0.2149 0.00820 0.00381 -0.1361 0.9328 0.5894 -2.750 0.2465 0.00815 0.00374 -0.1366 0.9279 0.6003 -2.500 0.2790 0.00807 0.00368 -0.1371 0.9224 0.6101 -2.250 0.3074 0.00804 0.00363 -0.1368 0.9111 0.6190 -2.000 0.3365 0.00801 0.00360 -0.1365 0.8982 0.6247 -1.750 0.3667 0.00800 0.00355 -0.1366 0.8847 0.6311 -1.500 0.3965 0.00800 0.00349 -0.1366 0.8661 0.6363 -1.250 0.4252 0.00801 0.00345 -0.1363 0.8411 0.6386 -1.000 0.4540 0.00807 0.00342 -0.1362 0.8143 0.6405 -0.750 0.4808 0.00827 0.00338 -0.1355 0.7583 0.6422 -0.500 0.5004 0.00899 0.00350 -0.1334 0.6361 0.6441 -0.250 0.5196 0.00987 0.00379 -0.1317 0.5100 0.6466 0.000 0.5421 0.01061 0.00405 -0.1307 0.4111 0.6490 0.250 0.5670 0.01116 0.00424 -0.1302 0.3343 0.6507 0.500 0.5927 0.01165 0.00442 -0.1299 0.2707 0.6519 0.750 0.6189 0.01206 0.00460 -0.1296 0.2215 0.6531 1.000 0.6449 0.01244 0.00480 -0.1292 0.1806 0.6542 1.250 0.6715 0.01276 0.00499 -0.1290 0.1521 0.6552 1.500 0.6983 0.01305 0.00518 -0.1287 0.1322 0.6563 1.750 0.7252 0.01334 0.00539 -0.1284 0.1148 0.6576 2.000 0.7522 0.01362 0.00559 -0.1282 0.1022 0.6590 2.250 0.7794 0.01386 0.00579 -0.1280 0.0936 0.6602 2.500 0.8066 0.01411 0.00600 -0.1278 0.0865 0.6614 3.000 0.8607 0.01463 0.00644 -0.1273 0.0736 0.6639 3.250 0.8874 0.01491 0.00668 -0.1270 0.0688 0.6652 3.500 0.9144 0.01516 0.00692 -0.1268 0.0651 0.6665 3.750 0.9409 0.01546 0.00718 -0.1264 0.0619 0.6678 4.000 0.9677 0.01572 0.00745 -0.1261 0.0595 0.6690 4.250 0.9942 0.01600 0.00771 -0.1258 0.0569 0.6702 4.500 1.0201 0.01632 0.00801 -0.1253 0.0546 0.6715 4.750 1.0458 0.01661 0.00833 -0.1248 0.0528 0.6728 5.000 1.0714 0.01690 0.00864 -0.1243 0.0511 0.6741 5.250 1.0966 0.01722 0.00897 -0.1237 0.0494 0.6753 5.500 1.1212 0.01759 0.00934 -0.1230 0.0476 0.6765 5.750 1.1463 0.01792 0.00970 -0.1223 0.0462 0.6777 6.000 1.1710 0.01825 0.01006 -0.1217 0.0446 0.6790 6.250 1.1953 0.01862 0.01044 -0.1209 0.0432 0.6804 6.500 1.2188 0.01906 0.01087 -0.1201 0.0419 0.6818 6.750 1.2427 0.01944 0.01129 -0.1192 0.0408 0.6832 7.000 1.2663 0.01983 0.01171 -0.1184 0.0396 0.6847 7.250 1.2895 0.02024 0.01215 -0.1174 0.0384 0.6861 7.500 1.3121 0.02068 0.01260 -0.1164 0.0372 0.6876 7.750 1.3338 0.02119 0.01311 -0.1153 0.0361 0.6890 8.000 1.3558 0.02160 0.01359 -0.1141 0.0351 0.6905 8.250 1.3770 0.02204 0.01409 -0.1128 0.0341 0.6921 8.500 1.3974 0.02251 0.01460 -0.1114 0.0331 0.6935 8.750 1.4169 0.02302 0.01515 -0.1099 0.0323 0.6949 9.000 1.4350 0.02361 0.01576 -0.1081 0.0316 0.6964 9.250 1.4521 0.02414 0.01637 -0.1061 0.0310 0.6979 9.500 1.4676 0.02470 0.01700 -0.1039 0.0304 0.6995 9.750 1.4842 0.02531 0.01767 -0.1019 0.0298 0.7011 10.000 1.5010 0.02595 0.01836 -0.1000 0.0292 0.7028 10.250 1.5175 0.02662 0.01908 -0.0981 0.0286 0.7045 10.500 1.5334 0.02733 0.01984 -0.0962 0.0281 0.7062 10.750 1.5481 0.02814 0.02068 -0.0942 0.0276 0.7078 11.000 1.5622 0.02899 0.02158 -0.0921 0.0271 0.7094 11.250 1.5763 0.02981 0.02251 -0.0901 0.0267 0.7112 11.500 1.5897 0.03069 0.02348 -0.0880 0.0263 0.7129 11.750 1.6024 0.03162 0.02451 -0.0859 0.0259 0.7147 12.000 1.6142 0.03262 0.02560 -0.0837 0.0255 0.7165 12.250 1.6256 0.03367 0.02674 -0.0816 0.0252 0.7183 12.500 1.6360 0.03480 0.02795 -0.0794 0.0249 0.7201 12.750 1.6455 0.03601 0.02924 -0.0773 0.0246 0.7219 13.000 1.6539 0.03732 0.03063 -0.0751 0.0243 0.7238 13.250 1.6609 0.03879 0.03218 -0.0730 0.0240 0.7257 13.500 1.6658 0.04046 0.03392 -0.0708 0.0237 0.7274 13.750 1.6686 0.04235 0.03589 -0.0685 0.0235 0.7290 14.000 1.6734 0.04412 0.03779 -0.0666 0.0233 0.7305 14.250 1.6771 0.04605 0.03986 -0.0648 0.0232 0.7322 14.500 1.6794 0.04816 0.04211 -0.0631 0.0230 0.7338 14.750 1.6803 0.05047 0.04456 -0.0615 0.0228 0.7356 15.000 1.6799 0.05303 0.04726 -0.0602 0.0226 0.7376 15.250 1.6780 0.05586 0.05022 -0.0591 0.0225 0.7396 15.500 1.6750 0.05896 0.05345 -0.0583 0.0223 0.7415 15.750 1.6705 0.06242 0.05706 -0.0579 0.0222 0.7434 16.000 1.6649 0.06625 0.06102 -0.0579 0.0220 0.7452 16.250 1.6576 0.07054 0.06545 -0.0585 0.0219 0.7467 16.500 1.6485 0.07532 0.07039 -0.0596 0.0217 0.7480 16.750 1.6373 0.08069 0.07593 -0.0613 0.0216 0.7492 17.000 1.6234 0.08679 0.08219 -0.0638 0.0215 0.7504 17.250 1.6071 0.09361 0.08919 -0.0670 0.0214 0.7515 17.500 1.5873 0.10133 0.09709 -0.0710 0.0213 0.7525 17.750 1.5639 0.10993 0.10588 -0.0758 0.0212 0.7534 18.000 1.5379 0.11932 0.11546 -0.0813 0.0212 0.7541 18.250 1.5083 0.12971 0.12605 -0.0878 0.0211 0.7547