XFOIL Version 6.96 Calculated polar for: NASA/LANGLEY NLF(2)-0415 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 ------ -------- --------- --------- -------- -------- -------- -13.000 -0.2521 0.08587 0.08261 -0.1417 0.8775 0.0081 -12.750 -0.2676 0.07639 0.07310 -0.1473 0.8751 0.0081 -12.500 -0.2999 0.06674 0.06336 -0.1524 0.8725 0.0081 -12.250 -0.3187 0.06161 0.05814 -0.1543 0.8699 0.0084 -12.000 -0.3500 0.05565 0.05203 -0.1551 0.8669 0.0079 -11.750 -0.3688 0.05168 0.04792 -0.1549 0.8645 0.0079 -11.500 -0.3823 0.04847 0.04456 -0.1543 0.8623 0.0083 -11.250 -0.3971 0.04519 0.04111 -0.1531 0.8601 0.0083 -11.000 -0.4139 0.04170 0.03742 -0.1511 0.8581 0.0084 -10.750 -0.4301 0.03817 0.03366 -0.1483 0.8561 0.0086 -10.500 -0.4393 0.03542 0.03070 -0.1456 0.8541 0.0085 -10.250 -0.4477 0.03214 0.02710 -0.1423 0.8522 0.0088 -10.000 -0.4484 0.02968 0.02435 -0.1395 0.8507 0.0090 -9.750 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0.3813 0.01008 0.00447 -0.1175 0.8228 0.6024 0.000 0.4080 0.01015 0.00454 -0.1176 0.8223 0.6031 0.250 0.4346 0.01023 0.00463 -0.1177 0.8217 0.6039 0.500 0.4613 0.01030 0.00472 -0.1178 0.8211 0.6046 0.750 0.4879 0.01038 0.00482 -0.1179 0.8206 0.6052 1.000 0.5145 0.01046 0.00493 -0.1179 0.8201 0.6057 1.250 0.5459 0.01033 0.00482 -0.1188 0.8181 0.6063 1.500 0.5758 0.01001 0.00451 -0.1192 0.8119 0.6070 1.750 0.6027 0.00972 0.00425 -0.1189 0.8054 0.6076 2.000 0.6374 0.00944 0.00396 -0.1204 0.8006 0.6082 2.250 0.6550 0.00940 0.00401 -0.1183 0.7947 0.6089 2.500 0.6834 0.00918 0.00380 -0.1184 0.7882 0.6096 2.750 0.7020 0.00911 0.00380 -0.1165 0.7802 0.6104 3.000 0.7221 0.00897 0.00372 -0.1149 0.7690 0.6111 3.250 0.7350 0.00889 0.00369 -0.1117 0.7506 0.6119 3.500 0.7237 0.00888 0.00316 -0.1027 0.6419 0.6128 3.750 0.6845 0.01030 0.00399 -0.0891 0.5300 0.6136 4.000 0.6506 0.01207 0.00513 -0.0777 0.4015 0.6145 4.250 0.6438 0.01333 0.00593 -0.0719 0.3014 0.6153 4.500 0.6507 0.01420 0.00649 -0.0686 0.2318 0.6162 4.750 0.6636 0.01486 0.00694 -0.0664 0.1839 0.6171 5.000 0.6792 0.01544 0.00736 -0.0647 0.1470 0.6181 5.250 0.6974 0.01589 0.00772 -0.0634 0.1257 0.6192 5.500 0.7166 0.01630 0.00808 -0.0623 0.1090 0.6201 5.750 0.7363 0.01670 0.00844 -0.0613 0.0959 0.6209 6.000 0.7559 0.01709 0.00882 -0.0603 0.0848 0.6219 6.250 0.7757 0.01749 0.00921 -0.0593 0.0748 0.6228 6.500 0.7958 0.01787 0.00960 -0.0584 0.0669 0.6238 6.750 0.8155 0.01830 0.01002 -0.0574 0.0596 0.6248 7.000 0.8360 0.01868 0.01044 -0.0566 0.0545 0.6259 7.250 0.8555 0.01914 0.01088 -0.0556 0.0479 0.6270 7.500 0.8759 0.01954 0.01131 -0.0548 0.0436 0.6282 7.750 0.8952 0.02002 0.01178 -0.0539 0.0386 0.6294 8.000 0.9156 0.02043 0.01224 -0.0531 0.0357 0.6306 8.250 0.9356 0.02088 0.01271 -0.0522 0.0325 0.6319 8.500 0.9550 0.02139 0.01323 -0.0513 0.0297 0.6332 8.750 0.9752 0.02183 0.01373 -0.0505 0.0276 0.6345 9.250 1.0141 0.02284 0.01481 -0.0488 0.0211 0.6371 9.500 1.0329 0.02341 0.01539 -0.0479 0.0171 0.6385 9.750 1.0516 0.02400 0.01602 -0.0470 0.0138 0.6400 10.000 1.0700 0.02464 0.01670 -0.0461 0.0117 0.6417 10.250 1.0880 0.02534 0.01744 -0.0451 0.0101 0.6435 10.500 1.1058 0.02608 0.01826 -0.0441 0.0092 0.6455 10.750 1.1235 0.02680 0.01907 -0.0430 0.0086 0.6474 11.000 1.1410 0.02755 0.01989 -0.0420 0.0082 0.6495 11.250 1.1578 0.02835 0.02078 -0.0410 0.0077 0.6514 11.500 1.1741 0.02922 0.02175 -0.0399 0.0074 0.6535 11.750 1.1892 0.03022 0.02285 -0.0387 0.0071 0.6557 12.000 1.2032 0.03128 0.02402 -0.0374 0.0068 0.6580 12.250 1.2171 0.03233 0.02522 -0.0361 0.0067 0.6605 12.500 1.2305 0.03343 0.02644 -0.0348 0.0065 0.6631 12.750 1.2428 0.03463 0.02776 -0.0334 0.0063 0.6657 13.000 1.2545 0.03584 0.02912 -0.0321 0.0062 0.6684 13.250 1.2649 0.03717 0.03059 -0.0306 0.0060 0.6715 13.500 1.2748 0.03856 0.03212 -0.0292 0.0058 0.6749 13.750 1.2833 0.04007 0.03376 -0.0277 0.0057 0.6784 14.000 1.2912 0.04162 0.03545 -0.0263 0.0056 0.6819 14.250 1.2977 0.04330 0.03728 -0.0248 0.0054 0.6859 14.500 1.3026 0.04516 0.03930 -0.0233 0.0053 0.6903 14.750 1.3049 0.04731 0.04161 -0.0218 0.0052 0.6948 15.000 1.3056 0.04966 0.04412 -0.0203 0.0051 0.6995 15.250 1.3042 0.05227 0.04691 -0.0189 0.0051 0.7048 15.750 1.2952 0.05845 0.05346 -0.0165 0.0049 0.7168 16.000 1.2864 0.06228 0.05748 -0.0157 0.0049 0.7238 16.250 1.2780 0.06623 0.06164 -0.0154 0.0049 0.7311 16.500 1.2665 0.07083 0.06645 -0.0155 0.0048 0.7398 16.750 1.2495 0.07657 0.07241 -0.0164 0.0048 0.7481 17.000 1.2347 0.08241 0.07848 -0.0181 0.0048 0.7586 17.250 1.2182 0.08906 0.08536 -0.0207 0.0048 0.7704 17.750 1.1792 0.10548 0.10227 -0.0295 0.0048 0.7982 18.000 1.1554 0.11601 0.11304 -0.0360 0.0048 0.8114 18.250 1.1315 0.12720 0.12446 -0.0430 0.0049 0.8257