XFOIL Version 6.96 Calculated polar for: NASA/LANGLEY LS(1)-0013 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.750 -1.0364 0.09867 0.09453 0.0012 1.0000 0.0256 -15.500 -1.0720 0.08714 0.08274 -0.0064 1.0000 0.0255 -15.250 -1.1007 0.07823 0.07357 -0.0118 1.0000 0.0255 -15.000 -1.1248 0.07103 0.06609 -0.0155 1.0000 0.0256 -14.750 -1.1449 0.06501 0.05978 -0.0180 1.0000 0.0258 -14.500 -1.1523 0.06107 0.05573 -0.0191 1.0000 0.0260 -14.250 -1.1564 0.05774 0.05230 -0.0197 1.0000 0.0263 -14.000 -1.1589 0.05473 0.04918 -0.0201 1.0000 0.0266 -13.750 -1.1603 0.05194 0.04626 -0.0202 1.0000 0.0269 -13.500 -1.1608 0.04932 0.04350 -0.0200 1.0000 0.0272 -13.250 -1.1603 0.04687 0.04091 -0.0196 1.0000 0.0276 -13.000 -1.1585 0.04460 0.03846 -0.0190 1.0000 0.0281 -12.750 -1.1557 0.04246 0.03615 -0.0182 1.0000 0.0287 -12.500 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0.9374 0.0519 -7.750 -0.8062 0.02019 0.01181 -0.0065 0.9272 0.0542 -7.500 -0.7838 0.01964 0.01125 -0.0060 0.9187 0.0569 -7.250 -0.7613 0.01917 0.01071 -0.0053 0.9113 0.0598 -7.000 -0.7372 0.01873 0.01017 -0.0048 0.9042 0.0627 -6.750 -0.7153 0.01813 0.00960 -0.0041 0.8974 0.0664 -6.500 -0.6914 0.01769 0.00911 -0.0037 0.8914 0.0707 -6.250 -0.6670 0.01725 0.00863 -0.0033 0.8854 0.0754 -6.000 -0.6435 0.01679 0.00816 -0.0028 0.8804 0.0813 -5.750 -0.6183 0.01638 0.00773 -0.0026 0.8751 0.0881 -5.500 -0.5932 0.01594 0.00731 -0.0024 0.8696 0.0978 -5.250 -0.5686 0.01552 0.00691 -0.0020 0.8649 0.1104 -5.000 -0.5430 0.01510 0.00655 -0.0019 0.8605 0.1276 -4.750 -0.5171 0.01462 0.00618 -0.0019 0.8556 0.1527 -4.500 -0.4922 0.01409 0.00582 -0.0018 0.8511 0.1918 -4.250 -0.4680 0.01348 0.00546 -0.0016 0.8473 0.2501 -4.000 -0.4422 0.01286 0.00515 -0.0018 0.8425 0.3168 -3.750 -0.4167 0.01225 0.00484 -0.0018 0.8382 0.3865 -3.500 -0.3929 0.01153 0.00462 -0.0015 0.8344 0.4872 -3.000 -0.3404 0.01116 0.00478 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0.8073 2.000 0.2280 0.01137 0.00500 0.0000 0.7159 0.8115 2.250 0.2565 0.01128 0.00490 0.0000 0.6964 0.8156 2.500 0.2842 0.01121 0.00485 0.0003 0.6770 0.8188 2.750 0.3122 0.01117 0.00481 0.0005 0.6560 0.8223 3.000 0.3404 0.01116 0.00478 0.0006 0.6291 0.8264 3.500 0.3929 0.01153 0.00462 0.0015 0.4870 0.8344 3.750 0.4167 0.01225 0.00484 0.0018 0.3863 0.8382 4.000 0.4422 0.01287 0.00515 0.0018 0.3167 0.8425 4.250 0.4680 0.01348 0.00546 0.0016 0.2501 0.8473 4.500 0.4922 0.01409 0.00582 0.0018 0.1918 0.8511 4.750 0.5172 0.01462 0.00618 0.0019 0.1527 0.8556 5.000 0.5430 0.01510 0.00655 0.0019 0.1276 0.8605 5.250 0.5686 0.01552 0.00691 0.0020 0.1104 0.8649 5.500 0.5933 0.01594 0.00731 0.0023 0.0978 0.8695 5.750 0.6184 0.01638 0.00773 0.0025 0.0881 0.8751 6.000 0.6436 0.01679 0.00816 0.0028 0.0812 0.8804 6.250 0.6670 0.01725 0.00863 0.0033 0.0753 0.8854 6.500 0.6915 0.01769 0.00912 0.0037 0.0706 0.8914 6.750 0.7154 0.01813 0.00960 0.0041 0.0664 0.8974 7.000 0.7373 0.01873 0.01017 0.0048 0.0627 0.9042 7.250 0.7614 0.01917 0.01071 0.0052 0.0598 0.9113 7.500 0.7840 0.01964 0.01125 0.0059 0.0569 0.9187 7.750 0.8063 0.02019 0.01182 0.0065 0.0542 0.9272 8.000 0.8279 0.02082 0.01250 0.0072 0.0519 0.9374 8.250 0.8514 0.02138 0.01317 0.0076 0.0496 0.9490 8.500 0.8766 0.02202 0.01388 0.0075 0.0475 0.9634 8.750 0.9032 0.02271 0.01460 0.0069 0.0455 1.0000 9.000 0.9257 0.02363 0.01555 0.0070 0.0438 1.0000 9.250 0.9491 0.02441 0.01644 0.0071 0.0420 1.0000 9.500 0.9716 0.02526 0.01735 0.0073 0.0404 1.0000 9.750 0.9931 0.02613 0.01827 0.0076 0.0391 1.0000 10.000 1.0136 0.02708 0.01925 0.0079 0.0380 1.0000 10.250 1.0330 0.02826 0.02046 0.0084 0.0369 1.0000 10.500 1.0528 0.02931 0.02170 0.0090 0.0358 1.0000 10.750 1.0712 0.03041 0.02294 0.0097 0.0345 1.0000 11.000 1.0883 0.03150 0.02415 0.0104 0.0334 1.0000 11.250 1.1038 0.03262 0.02537 0.0113 0.0326 1.0000 11.500 1.1166 0.03376 0.02658 0.0125 0.0320 1.0000 11.750 1.1286 0.03505 0.02791 0.0136 0.0314 1.0000 12.000 1.1390 0.03667 0.02964 0.0147 0.0308 1.0000 12.250 1.1466 0.03847 0.03170 0.0160 0.0301 1.0000 12.500 1.1523 0.04042 0.03389 0.0171 0.0294 1.0000 12.750 1.1565 0.04247 0.03616 0.0181 0.0287 1.0000 13.000 1.1594 0.04460 0.03847 0.0189 0.0281 1.0000 13.250 1.1613 0.04686 0.04089 0.0195 0.0276 1.0000 13.500 1.1619 0.04931 0.04349 0.0199 0.0272 1.0000 13.750 1.1614 0.05193 0.04625 0.0200 0.0269 1.0000 14.000 1.1601 0.05472 0.04916 0.0199 0.0266 1.0000 14.250 1.1579 0.05769 0.05224 0.0195 0.0263 1.0000 14.500 1.1538 0.06103 0.05569 0.0189 0.0260 1.0000 14.750 1.1458 0.06507 0.05985 0.0178 0.0258 1.0000 15.000 1.1257 0.07111 0.06618 0.0153 0.0256 1.0000 15.250 1.1016 0.07835 0.07369 0.0115 0.0255 1.0000 15.500 1.0727 0.08732 0.08293 0.0060 0.0255 1.0000 15.750 1.0369 0.09893 0.09480 -0.0017 0.0256 1.0000