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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.1686 0.08321 0.07959 -0.0638 1.0000 0.0235 -19.500 -1.1791 0.07802 0.07429 -0.0664 1.0000 0.0236 -19.250 -1.1874 0.07324 0.06939 -0.0688 1.0000 0.0237 -19.000 -1.1933 0.06892 0.06497 -0.0709 1.0000 0.0239 -18.750 -1.1977 0.06495 0.06090 -0.0727 1.0000 0.0240 -18.500 -1.1999 0.06137 0.05722 -0.0742 1.0000 0.0241 -18.250 -1.2001 0.05816 0.05391 -0.0755 1.0000 0.0242 -18.000 -1.1988 0.05527 0.05093 -0.0765 1.0000 0.0243 -17.750 -1.2060 0.05161 0.04718 -0.0774 1.0000 0.0246 -17.500 -1.2099 0.04849 0.04398 -0.0780 1.0000 0.0249 -17.250 -1.2096 0.04596 0.04140 -0.0782 1.0000 0.0252 -17.000 -1.2071 0.04378 0.03918 -0.0782 1.0000 0.0254 -16.750 -1.2039 0.04183 0.03718 -0.0780 1.0000 0.0257 -16.500 -1.1998 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0.00600 -0.1090 0.9693 0.0662 -7.000 -0.3214 0.01114 0.00572 -0.1113 0.9688 0.0705 -6.750 -0.2845 0.01079 0.00543 -0.1137 0.9682 0.0770 -6.500 -0.2508 0.01051 0.00520 -0.1154 0.9669 0.0846 -6.250 -0.2207 0.01029 0.00502 -0.1162 0.9644 0.0930 -6.000 -0.1868 0.01000 0.00479 -0.1179 0.9627 0.1043 -5.750 -0.1510 0.00964 0.00455 -0.1202 0.9615 0.1232 -5.500 -0.1149 0.00930 0.00433 -0.1224 0.9603 0.1486 -5.250 -0.0771 0.00888 0.00409 -0.1251 0.9594 0.1868 -5.000 -0.0376 0.00839 0.00382 -0.1283 0.9587 0.2393 -4.750 0.0065 0.00768 0.00348 -0.1329 0.9584 0.3330 -4.500 0.0527 0.00690 0.00313 -0.1380 0.9583 0.4475 -4.250 0.0935 0.00644 0.00300 -0.1413 0.9577 0.5398 -4.000 0.1272 0.00635 0.00295 -0.1425 0.9560 0.5661 -3.750 0.1598 0.00630 0.00290 -0.1432 0.9533 0.5815 -3.500 0.1874 0.00624 0.00287 -0.1429 0.9475 0.5920 -3.250 0.2175 0.00615 0.00276 -0.1430 0.9419 0.6017 -3.000 0.2465 0.00610 0.00272 -0.1428 0.9357 0.6089 -2.750 0.2750 0.00604 0.00264 -0.1426 0.9275 0.6136 -2.500 0.3055 0.00603 0.00256 -0.1428 0.9216 0.6172 -2.250 0.3335 0.00599 0.00257 -0.1425 0.9126 0.6224 -2.000 0.3624 0.00604 0.00259 -0.1423 0.9030 0.6283 -1.750 0.3915 0.00612 0.00264 -0.1422 0.8923 0.6338 -1.500 0.4207 0.00611 0.00263 -0.1422 0.8812 0.6377 -1.250 0.4495 0.00614 0.00264 -0.1420 0.8667 0.6403 -1.000 0.4775 0.00625 0.00272 -0.1417 0.8486 0.6444 -0.750 0.5056 0.00640 0.00280 -0.1414 0.8249 0.6486 -0.500 0.5334 0.00657 0.00281 -0.1410 0.7892 0.6506 -0.250 0.5582 0.00696 0.00288 -0.1401 0.7185 0.6519 0.000 0.5788 0.00773 0.00307 -0.1385 0.5937 0.6532 0.250 0.6005 0.00847 0.00330 -0.1374 0.4740 0.6553 0.500 0.6239 0.00912 0.00355 -0.1365 0.3814 0.6572 0.750 0.6476 0.00975 0.00381 -0.1357 0.2953 0.6589 1.000 0.6727 0.01026 0.00403 -0.1352 0.2302 0.6604 1.250 0.6985 0.01070 0.00423 -0.1348 0.1803 0.6616 1.500 0.7252 0.01105 0.00442 -0.1345 0.1475 0.6627 1.750 0.7525 0.01133 0.00459 -0.1343 0.1263 0.6639 2.000 0.7798 0.01161 0.00476 -0.1341 0.1076 0.6651 2.250 0.8071 0.01188 0.00495 -0.1339 0.0941 0.6663 2.500 0.8347 0.01211 0.00512 -0.1338 0.0846 0.6675 2.750 0.8621 0.01237 0.00532 -0.1336 0.0770 0.6687 3.000 0.8893 0.01263 0.00552 -0.1333 0.0713 0.6697 3.250 0.9168 0.01286 0.00573 -0.1332 0.0675 0.6706 3.500 0.9442 0.01307 0.00592 -0.1330 0.0642 0.6717 3.750 0.9709 0.01334 0.00617 -0.1326 0.0610 0.6733 4.000 0.9984 0.01351 0.00636 -0.1324 0.0593 0.6746 4.250 1.0252 0.01374 0.00658 -0.1321 0.0572 0.6758 4.500 1.0514 0.01404 0.00686 -0.1317 0.0547 0.6770 4.750 1.0778 0.01429 0.00712 -0.1313 0.0531 0.6782 5.000 1.1044 0.01451 0.00736 -0.1309 0.0515 0.6794 5.250 1.1306 0.01477 0.00762 -0.1304 0.0499 0.6806 5.500 1.1556 0.01515 0.00797 -0.1298 0.0478 0.6819 5.750 1.1815 0.01542 0.00826 -0.1293 0.0466 0.6833 6.000 1.2074 0.01568 0.00854 -0.1287 0.0452 0.6848 6.250 1.2327 0.01598 0.00883 -0.1282 0.0437 0.6861 6.500 1.2561 0.01649 0.00932 -0.1272 0.0416 0.6874 6.750 1.2818 0.01671 0.00957 -0.1267 0.0406 0.6884 7.000 1.3068 0.01701 0.00988 -0.1260 0.0393 0.6893 7.250 1.3312 0.01734 0.01021 -0.1253 0.0380 0.6904 7.500 1.3533 0.01788 0.01074 -0.1242 0.0365 0.6924 7.750 1.3775 0.01817 0.01109 -0.1234 0.0357 0.6940 8.000 1.4012 0.01849 0.01145 -0.1225 0.0348 0.6955 8.250 1.4243 0.01885 0.01183 -0.1215 0.0339 0.6969 8.500 1.4466 0.01924 0.01224 -0.1204 0.0330 0.6984 8.750 1.4667 0.01980 0.01281 -0.1189 0.0320 0.6998 9.000 1.4869 0.02030 0.01335 -0.1174 0.0313 0.7014 9.250 1.5081 0.02068 0.01377 -0.1160 0.0307 0.7031 9.500 1.5283 0.02110 0.01423 -0.1145 0.0301 0.7048 9.750 1.5477 0.02156 0.01472 -0.1129 0.0295 0.7064 10.000 1.5661 0.02204 0.01523 -0.1111 0.0290 0.7078 10.250 1.5805 0.02258 0.01579 -0.1086 0.0285 0.7089 10.500 1.5942 0.02327 0.01652 -0.1061 0.0279 0.7106 10.750 1.6060 0.02418 0.01749 -0.1033 0.0273 0.7128 11.000 1.6227 0.02476 0.01814 -0.1014 0.0271 0.7147 11.250 1.6383 0.02540 0.01885 -0.0993 0.0268 0.7164 11.500 1.6534 0.02609 0.01962 -0.0972 0.0264 0.7181 11.750 1.6676 0.02684 0.02043 -0.0950 0.0261 0.7199 12.000 1.6813 0.02763 0.02128 -0.0929 0.0258 0.7218 12.250 1.6944 0.02846 0.02217 -0.0907 0.0254 0.7236 12.500 1.7070 0.02934 0.02311 -0.0884 0.0251 0.7255 12.750 1.7183 0.03030 0.02412 -0.0861 0.0249 0.7273 13.000 1.7286 0.03136 0.02524 -0.0838 0.0246 0.7287 13.250 1.7370 0.03258 0.02652 -0.0814 0.0242 0.7311 13.500 1.7408 0.03415 0.02817 -0.0785 0.0239 0.7332 13.750 1.7397 0.03618 0.03032 -0.0753 0.0235 0.7349 14.000 1.7486 0.03744 0.03168 -0.0732 0.0234 0.7368 14.250 1.7563 0.03882 0.03314 -0.0712 0.0232 0.7388 14.500 1.7627 0.04034 0.03477 -0.0692 0.0231 0.7408 14.750 1.7678 0.04204 0.03656 -0.0672 0.0229 0.7428 15.000 1.7714 0.04392 0.03854 -0.0653 0.0227 0.7446 15.250 1.7735 0.04598 0.04070 -0.0635 0.0226 0.7462 15.500 1.7747 0.04821 0.04304 -0.0618 0.0224 0.7476 15.750 1.7743 0.05070 0.04564 -0.0604 0.0223 0.7499 16.000 1.7734 0.05336 0.04842 -0.0592 0.0221 0.7519 16.250 1.7707 0.05636 0.05154 -0.0583 0.0219 0.7537 16.500 1.7672 0.05960 0.05489 -0.0577 0.0218 0.7556 16.750 1.7617 0.06328 0.05869 -0.0575 0.0217 0.7575 17.000 1.7551 0.06733 0.06286 -0.0578 0.0216 0.7593 17.250 1.7466 0.07186 0.06751 -0.0585 0.0215 0.7611 17.500 1.7358 0.07696 0.07274 -0.0598 0.0214 0.7626 17.750 1.7224 0.08271 0.07862 -0.0618 0.0213 0.7639 18.000 1.7070 0.08905 0.08510 -0.0644 0.0212 0.7649 18.250 1.6882 0.09621 0.09241 -0.0677 0.0211 0.7660 18.500 1.6675 0.10392 0.10028 -0.0717 0.0211 0.7673 18.750 1.6434 0.11238 0.10890 -0.0763 0.0210 0.7683 19.000 1.6181 0.12127 0.11795 -0.0814 0.0210 0.7691 19.250 1.5917 0.13056 0.12740 -0.0871 0.0210 0.7699