XFOIL Version 6.96 Calculated polar for: NASA SC(2)-0710 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 ------ -------- --------- --------- -------- -------- -------- -10.250 -0.5548 0.10018 0.09471 -0.0281 1.0000 0.1510 -10.000 -0.5415 0.09774 0.09227 -0.0262 1.0000 0.1563 -9.750 -0.5938 0.09314 0.08787 -0.0319 1.0000 0.1632 -9.500 -0.5674 0.08982 0.08453 -0.0284 1.0000 0.1672 -9.250 -0.5599 0.08723 0.08195 -0.0267 1.0000 0.1720 -9.000 -0.6431 0.08106 0.07599 -0.0349 1.0000 0.1792 -8.750 -0.6085 0.07923 0.07420 -0.0275 1.0000 0.1833 -8.500 -0.6886 0.04997 0.04340 -0.0526 1.0000 0.0911 -8.250 -0.6715 0.04493 0.03796 -0.0537 1.0000 0.0849 -8.000 -0.6507 0.03986 0.03236 -0.0555 1.0000 0.0819 -7.750 -0.6252 0.03569 0.02761 -0.0572 1.0000 0.0810 -7.500 -0.5988 0.03308 0.02458 -0.0582 1.0000 0.0836 -7.250 -0.5702 0.03078 0.02177 -0.0592 1.0000 0.0871 -7.000 -0.5415 0.02845 0.01901 -0.0599 1.0000 0.0896 -6.750 -0.5165 0.02672 0.01734 -0.0600 1.0000 0.0950 -6.500 -0.4888 0.02547 0.01581 -0.0601 1.0000 0.1012 -6.250 -0.4627 0.02389 0.01424 -0.0601 1.0000 0.1076 -6.000 -0.4356 0.02291 0.01316 -0.0600 1.0000 0.1157 -5.750 -0.4094 0.02171 0.01208 -0.0598 1.0000 0.1244 -5.500 -0.3818 0.02074 0.01112 -0.0598 1.0000 0.1358 -5.250 -0.3533 0.01981 0.01035 -0.0601 1.0000 0.1513 -5.000 -0.3225 0.01887 0.00962 -0.0611 1.0000 0.1788 -4.750 -0.2717 0.01605 0.00914 -0.0675 1.0000 0.4973 -4.500 -0.2619 0.01718 0.01056 -0.0616 1.0000 0.6322 -4.250 -0.2516 0.01826 0.01160 -0.0561 1.0000 0.6668 -4.000 -0.2383 0.01922 0.01248 -0.0517 1.0000 0.6942 -3.750 -0.2293 0.02003 0.01326 -0.0462 1.0000 0.7119 -3.500 -0.2187 0.02068 0.01387 -0.0412 1.0000 0.7290 -3.250 -0.2080 0.02119 0.01435 -0.0364 1.0000 0.7458 -3.000 -0.1983 0.02158 0.01472 -0.0314 1.0000 0.7628 -2.750 -0.1886 0.02184 0.01496 -0.0266 1.0000 0.7806 -2.500 -0.1786 0.02198 0.01508 -0.0220 1.0000 0.7995 -2.250 -0.1652 0.02206 0.01512 -0.0183 1.0000 0.8209 -2.000 -0.1584 0.02181 0.01487 -0.0131 1.0000 0.8390 -1.750 -0.1463 0.02151 0.01455 -0.0096 1.0000 0.8560 -1.500 -0.1289 0.02119 0.01421 -0.0075 1.0000 0.8700 -1.250 -0.1066 0.02096 0.01393 -0.0069 1.0000 0.8815 -1.000 -0.0844 0.02070 0.01366 -0.0063 1.0000 0.8912 -0.750 -0.0620 0.02042 0.01337 -0.0058 1.0000 0.8992 -0.500 -0.0340 0.02036 0.01330 -0.0067 1.0000 0.9062 -0.250 -0.0106 0.02015 0.01309 -0.0066 1.0000 0.9125 0.000 0.0166 0.02012 0.01308 -0.0074 1.0000 0.9184 0.250 0.0438 0.02010 0.01310 -0.0083 1.0000 0.9234 0.500 0.0695 0.02009 0.01312 -0.0088 1.0000 0.9285 0.750 0.0987 0.02024 0.01333 -0.0102 1.0000 0.9329 1.000 0.1264 0.02038 0.01354 -0.0113 1.0000 0.9370 1.250 0.1534 0.02056 0.01380 -0.0124 1.0000 0.9410 1.500 0.1816 0.02085 0.01419 -0.0138 1.0000 0.9453 1.750 0.2276 0.02121 0.01469 -0.0184 0.9900 0.9486 2.000 0.3128 0.02089 0.01456 -0.0287 0.9556 0.9500 2.250 0.3775 0.01986 0.01374 -0.0342 0.9249 0.9523 2.500 0.4327 0.01845 0.01255 -0.0372 0.8934 0.9549 2.750 0.4792 0.01656 0.01090 -0.0375 0.8476 0.9579 3.000 0.5386 0.01666 0.00844 -0.0376 0.2980 0.9581 3.250 0.5558 0.01848 0.00929 -0.0362 0.1843 0.9619 3.500 0.5800 0.01955 0.01011 -0.0358 0.1557 0.9657 3.750 0.6080 0.02057 0.01102 -0.0361 0.1375 0.9694 4.250 0.6707 0.02284 0.01317 -0.0379 0.1140 0.9774 4.500 0.7048 0.02436 0.01475 -0.0391 0.1059 0.9825 4.750 0.7392 0.02596 0.01628 -0.0408 0.0974 0.9885 5.000 0.7722 0.02771 0.01837 -0.0417 0.0922 1.0000 5.250 0.8029 0.02929 0.02009 -0.0426 0.0861 1.0000 5.500 0.8339 0.03258 0.02345 -0.0440 0.0827 1.0000 5.750 0.8611 0.03491 0.02634 -0.0438 0.0813 1.0000 6.000 0.8859 0.03760 0.02960 -0.0435 0.0793 1.0000 6.250 0.9081 0.04081 0.03335 -0.0430 0.0780 1.0000 6.500 0.9278 0.04498 0.03800 -0.0424 0.0794 1.0000 6.750 0.9464 0.04978 0.04308 -0.0423 0.0815 1.0000 7.000 0.8966 0.07201 0.06791 -0.0400 0.1799 1.0000 7.250 0.9197 0.07584 0.07169 -0.0401 0.1741 1.0000 7.500 0.8913 0.08115 0.07728 -0.0415 0.1649 1.0000 7.750 0.9080 0.08479 0.08094 -0.0415 0.1593 1.0000 8.000 0.9037 0.09045 0.08664 -0.0423 0.1550 1.0000 8.250 0.8517 0.09781 0.09413 -0.0496 0.1509 1.0000 8.500 0.8475 0.10359 0.09990 -0.0540 0.1459 1.0000 8.750 0.8934 0.10527 0.10156 -0.0462 0.1405 1.0000 9.000 0.8401 0.11564 0.11192 -0.0615 0.1384 1.0000 9.250 0.8310 0.12150 0.11775 -0.0671 0.1322 1.0000