XFOIL Version 6.96 Calculated polar for: NLR-7301 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -14.500 -0.8017 0.08033 0.07296 -0.0637 1.0000 0.0570 -14.250 -0.8432 0.07181 0.06411 -0.0681 1.0000 0.0571 -14.000 -0.8706 0.06582 0.05782 -0.0705 1.0000 0.0574 -13.750 -0.8909 0.06102 0.05272 -0.0718 1.0000 0.0578 -13.500 -0.9064 0.05695 0.04835 -0.0724 1.0000 0.0582 -13.250 -0.9114 0.05399 0.04519 -0.0724 1.0000 0.0587 -13.000 -0.9039 0.05220 0.04339 -0.0721 1.0000 0.0593 -12.750 -0.8977 0.05044 0.04158 -0.0717 1.0000 0.0600 -12.500 -0.8930 0.04866 0.03973 -0.0711 1.0000 0.0608 -12.250 -0.8899 0.04687 0.03783 -0.0703 1.0000 0.0617 -12.000 -0.8882 0.04511 0.03593 -0.0690 1.0000 0.0627 -11.750 -0.8890 0.04347 0.03409 -0.0671 1.0000 0.0638 -11.500 -0.8895 0.04223 0.03276 -0.0646 1.0000 0.0646 -11.250 -0.8880 0.04145 0.03202 -0.0617 1.0000 0.0653 -11.000 -0.8917 0.04076 0.03133 -0.0581 1.0000 0.0660 -10.750 -0.8986 0.04012 0.03068 -0.0539 1.0000 0.0666 -10.500 -0.9060 0.03946 0.02998 -0.0496 1.0000 0.0673 -10.250 -0.8917 0.03834 0.02875 -0.0488 0.9973 0.0687 -10.000 -0.8674 0.03702 0.02723 -0.0498 0.9935 0.0707 -9.750 -0.8426 0.03608 0.02637 -0.0505 0.9898 0.0723 -9.500 -0.8185 0.03512 0.02537 -0.0512 0.9857 0.0743 -9.250 -0.7920 0.03411 0.02423 -0.0520 0.9823 0.0768 -9.000 -0.7633 0.03320 0.02337 -0.0531 0.9796 0.0789 -8.750 -0.7410 0.03240 0.02258 -0.0532 0.9746 0.0813 -8.500 -0.7147 0.03159 0.02166 -0.0538 0.9706 0.0846 -8.250 -0.6873 0.03079 0.02096 -0.0548 0.9675 0.0874 -8.000 -0.6590 0.03006 0.02020 -0.0557 0.9650 0.0911 -7.750 -0.6413 0.02943 0.01960 -0.0548 0.9596 0.0942 -7.500 -0.6178 0.02877 0.01899 -0.0550 0.9557 0.0982 -7.250 -0.5907 0.02811 0.01833 -0.0557 0.9527 0.1030 -7.000 -0.5611 0.02745 0.01771 -0.0569 0.9502 0.1086 -6.750 -0.5445 0.02692 0.01723 -0.0558 0.9445 0.1136 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0.6472 -1.750 -0.0538 0.02568 0.01852 -0.0469 0.8721 0.6560 -1.500 -0.0164 0.02557 0.01833 -0.0493 0.8701 0.6674 -1.250 -0.0106 0.02597 0.01878 -0.0450 0.8610 0.6705 -1.000 0.0154 0.02611 0.01895 -0.0443 0.8564 0.6739 -0.750 0.0471 0.02611 0.01895 -0.0447 0.8527 0.6778 -0.500 0.0832 0.02595 0.01878 -0.0462 0.8499 0.6823 -0.250 0.1107 0.02574 0.01855 -0.0471 0.8431 0.6881 0.000 0.1423 0.02532 0.01814 -0.0472 0.8327 0.6912 0.250 0.1807 0.02442 0.01724 -0.0470 0.8173 0.6933 0.500 0.2187 0.02321 0.01600 -0.0463 0.7958 0.6956 0.750 0.2508 0.02238 0.01515 -0.0455 0.7762 0.6981 1.000 0.2816 0.02181 0.01459 -0.0452 0.7603 0.7012 1.250 0.3055 0.02150 0.01430 -0.0442 0.7410 0.7051 1.500 0.3344 0.02104 0.01382 -0.0442 0.7172 0.7091 1.750 0.3595 0.02067 0.01344 -0.0438 0.6811 0.7127 2.000 0.3921 0.02009 0.01259 -0.0429 0.5967 0.7145 2.250 0.4110 0.02064 0.01205 -0.0400 0.4219 0.7166 2.500 0.4208 0.02171 0.01241 -0.0371 0.2976 0.7194 2.750 0.4375 0.02251 0.01274 -0.0356 0.2237 0.7225 3.000 0.4590 0.02308 0.01300 -0.0350 0.1851 0.7255 3.250 0.4828 0.02355 0.01326 -0.0347 0.1626 0.7288 3.500 0.5083 0.02397 0.01352 -0.0349 0.1474 0.7323 3.750 0.5333 0.02436 0.01382 -0.0349 0.1361 0.7355 4.000 0.5544 0.02479 0.01420 -0.0336 0.1277 0.7379 4.250 0.5754 0.02527 0.01460 -0.0326 0.1209 0.7405 4.500 0.5982 0.02569 0.01503 -0.0318 0.1145 0.7434 4.750 0.6211 0.02620 0.01546 -0.0313 0.1095 0.7464 5.000 0.6456 0.02669 0.01594 -0.0311 0.1047 0.7497 5.250 0.6704 0.02728 0.01642 -0.0311 0.1011 0.7532 5.500 0.6968 0.02783 0.01698 -0.0312 0.0971 0.7566 5.750 0.7179 0.02838 0.01751 -0.0302 0.0940 0.7591 6.000 0.7401 0.02900 0.01811 -0.0293 0.0912 0.7620 6.250 0.7637 0.02961 0.01876 -0.0288 0.0883 0.7654 6.500 0.7880 0.03026 0.01937 -0.0285 0.0860 0.7689 6.750 0.8141 0.03102 0.02006 -0.0286 0.0843 0.7724 7.000 0.8424 0.03185 0.02095 -0.0291 0.0823 0.7760 7.250 0.8668 0.03263 0.02178 -0.0286 0.0806 0.7787 7.500 0.8903 0.03341 0.02259 -0.0281 0.0792 0.7815 7.750 0.9142 0.03421 0.02336 -0.0277 0.0780 0.7847 8.000 0.9391 0.03516 0.02434 -0.0276 0.0768 0.7886 8.250 0.9638 0.03622 0.02556 -0.0274 0.0753 0.7928 8.500 0.9877 0.03727 0.02671 -0.0273 0.0739 0.7968 8.750 1.0079 0.03821 0.02773 -0.0264 0.0728 0.8000 9.000 1.0287 0.03917 0.02875 -0.0257 0.0719 0.8035 9.250 1.0506 0.04023 0.02983 -0.0253 0.0711 0.8073 9.500 1.0728 0.04150 0.03115 -0.0251 0.0705 0.8113 9.750 1.0908 0.04317 0.03309 -0.0244 0.0698 0.8152 10.000 1.1037 0.04479 0.03497 -0.0228 0.0691 0.8186 10.250 1.1144 0.04648 0.03690 -0.0211 0.0686 0.8226 10.500 1.1231 0.04828 0.03892 -0.0193 0.0681 0.8272 10.750 1.1310 0.05028 0.04116 -0.0178 0.0676 0.8320 11.000 1.1346 0.05227 0.04337 -0.0158 0.0672 0.8361 11.250 1.1363 0.05437 0.04569 -0.0138 0.0668 0.8405 11.500 1.1368 0.05660 0.04813 -0.0122 0.0664 0.8451 11.750 1.1363 0.05900 0.05071 -0.0108 0.0660 0.8497 12.000 1.1329 0.06136 0.05325 -0.0091 0.0656 0.8539 12.250 1.1272 0.06404 0.05612 -0.0077 0.0654 0.8586 12.500 1.1204 0.06700 0.05926 -0.0068 0.0651 0.8638 12.750 1.1103 0.07032 0.06278 -0.0062 0.0648 0.8685 13.000 1.0951 0.07423 0.06689 -0.0058 0.0646 0.8733 13.250 1.0709 0.07950 0.07243 -0.0065 0.0645 0.8779