XFOIL Version 6.96 Calculated polar for: E231 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 ------ -------- --------- --------- -------- -------- -------- -11.250 -0.2753 0.09672 0.09484 -0.0520 0.8824 0.0079 -11.000 -0.2740 0.09248 0.09060 -0.0537 0.8798 0.0080 -5.500 -0.3085 0.01502 0.00958 -0.0528 0.8172 0.0064 -5.250 -0.2851 0.01306 0.00729 -0.0513 0.8147 0.0051 -5.000 -0.2603 0.01240 0.00657 -0.0508 0.8123 0.0050 -4.750 -0.2356 0.01183 0.00595 -0.0502 0.8096 0.0049 -4.500 -0.2117 0.01119 0.00524 -0.0495 0.8069 0.0049 -4.250 -0.1887 0.01050 0.00445 -0.0485 0.8044 0.0050 -4.000 -0.1654 0.00989 0.00374 -0.0476 0.8017 0.0052 -3.750 -0.1401 0.00952 0.00333 -0.0471 0.7992 0.0056 -3.500 -0.1141 0.00922 0.00301 -0.0468 0.7964 0.0069 -3.250 -0.0881 0.00893 0.00269 -0.0464 0.7935 0.0103 -3.000 -0.0639 0.00847 0.00239 -0.0458 0.7908 0.0471 -2.750 -0.0388 0.00816 0.00222 -0.0454 0.7880 0.0922 -2.500 -0.0163 0.00761 0.00206 -0.0447 0.7850 0.1945 -2.250 0.0021 0.00677 0.00189 -0.0434 0.7815 0.3774 -2.000 0.0208 0.00606 0.00172 -0.0418 0.7779 0.5398 -1.750 0.0373 0.00537 0.00159 -0.0397 0.7744 0.7019 -1.500 0.0577 0.00508 0.00167 -0.0379 0.7707 0.8160 -1.250 0.0843 0.00507 0.00170 -0.0375 0.7667 0.8451 -1.000 0.1116 0.00509 0.00170 -0.0373 0.7628 0.8606 -0.750 0.1387 0.00516 0.00173 -0.0370 0.7590 0.8742 -0.500 0.1659 0.00519 0.00176 -0.0368 0.7547 0.8834 -0.250 0.1932 0.00522 0.00178 -0.0366 0.7500 0.8904 0.000 0.2203 0.00529 0.00179 -0.0363 0.7457 0.8979 0.250 0.2475 0.00532 0.00183 -0.0361 0.7408 0.9032 0.500 0.2746 0.00536 0.00186 -0.0359 0.7355 0.9085 0.750 0.3012 0.00542 0.00187 -0.0356 0.7303 0.9141 1.000 0.3282 0.00543 0.00191 -0.0353 0.7243 0.9181 1.250 0.3547 0.00549 0.00195 -0.0350 0.7183 0.9227 1.500 0.3807 0.00555 0.00199 -0.0346 0.7117 0.9278 1.750 0.4070 0.00558 0.00201 -0.0342 0.7043 0.9315 2.000 0.4335 0.00562 0.00206 -0.0339 0.6960 0.9349 2.250 0.4593 0.00568 0.00208 -0.0334 0.6871 0.9385 2.500 0.4848 0.00572 0.00211 -0.0330 0.6770 0.9420 2.750 0.5110 0.00575 0.00212 -0.0327 0.6659 0.9445 3.000 0.5373 0.00581 0.00215 -0.0325 0.6529 0.9467 3.250 0.5631 0.00589 0.00219 -0.0322 0.6384 0.9489 3.500 0.5879 0.00598 0.00224 -0.0317 0.6210 0.9512 3.750 0.6116 0.00609 0.00229 -0.0310 0.6006 0.9538 4.000 0.6336 0.00625 0.00236 -0.0300 0.5758 0.9564 4.250 0.6567 0.00642 0.00245 -0.0292 0.5478 0.9585 4.500 0.6792 0.00667 0.00258 -0.0283 0.5147 0.9609 4.750 0.7003 0.00696 0.00273 -0.0273 0.4793 0.9636 5.000 0.7205 0.00724 0.00289 -0.0260 0.4475 0.9667 5.250 0.7388 0.00751 0.00306 -0.0244 0.4178 0.9704 5.500 0.7622 0.00785 0.00326 -0.0240 0.3818 0.9726 5.750 0.7862 0.00823 0.00351 -0.0237 0.3478 0.9749 6.000 0.8108 0.00859 0.00374 -0.0236 0.3187 0.9772 6.250 0.8349 0.00892 0.00399 -0.0234 0.2927 0.9800 6.500 0.8565 0.00932 0.00427 -0.0227 0.2632 0.9833 6.750 0.8849 0.00975 0.00458 -0.0235 0.2348 0.9845 7.000 0.9137 0.01018 0.00491 -0.0245 0.2097 0.9857 7.250 0.9420 0.01060 0.00525 -0.0253 0.1880 0.9870 7.500 0.9684 0.01108 0.00563 -0.0258 0.1652 0.9890 7.750 0.9936 0.01152 0.00599 -0.0261 0.1446 0.9914 8.000 1.0174 0.01199 0.00638 -0.0261 0.1265 0.9942 8.250 1.0445 0.01248 0.00680 -0.0269 0.1087 0.9963 8.500 1.0705 0.01304 0.00728 -0.0275 0.0906 0.9988 8.750 1.0812 0.01340 0.00762 -0.0249 0.0807 1.0000 9.000 1.0751 0.01369 0.00787 -0.0189 0.0729 1.0000 9.250 1.0839 0.01416 0.00830 -0.0160 0.0633 1.0000 9.500 1.0969 0.01463 0.00876 -0.0138 0.0557 1.0000 9.750 1.1096 0.01519 0.00928 -0.0118 0.0472 1.0000 10.000 1.1219 0.01582 0.00986 -0.0099 0.0392 1.0000 10.250 1.1361 0.01638 0.01042 -0.0082 0.0337 1.0000 10.500 1.1493 0.01703 0.01106 -0.0065 0.0279 1.0000 10.750 1.1627 0.01768 0.01172 -0.0048 0.0242 1.0000 11.000 1.1760 0.01837 0.01242 -0.0033 0.0199 1.0000 11.250 1.1872 0.01920 0.01323 -0.0015 0.0154 1.0000 11.500 1.1983 0.02006 0.01408 0.0002 0.0115 1.0000 11.750 1.2102 0.02090 0.01494 0.0018 0.0090 1.0000 12.000 1.2139 0.02230 0.01632 0.0042 0.0041 1.0000 12.250 1.2237 0.02332 0.01741 0.0059 0.0036 1.0000 12.500 1.2336 0.02435 0.01849 0.0074 0.0031 1.0000 12.750 1.2414 0.02558 0.01982 0.0091 0.0026 1.0000 13.000 1.2486 0.02687 0.02119 0.0107 0.0021 1.0000 13.250 1.2605 0.02781 0.02220 0.0118 0.0023 1.0000 13.500 1.2644 0.02942 0.02389 0.0135 0.0019 1.0000 13.750 1.2676 0.03112 0.02570 0.0151 0.0018 1.0000 14.000 1.2695 0.03296 0.02765 0.0166 0.0017 1.0000 14.250 1.2620 0.03572 0.03056 0.0185 0.0016 1.0000 14.500 1.2682 0.03733 0.03226 0.0194 0.0016 1.0000 14.750 1.2666 0.03976 0.03480 0.0204 0.0016 1.0000 15.000 1.2716 0.04164 0.03677 0.0210 0.0015 1.0000 15.250 1.2747 0.04379 0.03901 0.0215 0.0015 1.0000 15.500 1.2784 0.04594 0.04125 0.0218 0.0014 1.0000 15.750 1.2573 0.05099 0.04651 0.0222 0.0015 1.0000 16.000 1.2620 0.05330 0.04889 0.0221 0.0014 1.0000 16.250 1.2654 0.05581 0.05150 0.0217 0.0014 1.0000 16.500 1.2525 0.06055 0.05639 0.0210 0.0014 1.0000 16.750 1.2444 0.06490 0.06086 0.0199 0.0014 1.0000 17.000 1.2359 0.06951 0.06560 0.0185 0.0013 1.0000 17.250 1.2274 0.07429 0.07051 0.0168 0.0013 1.0000 17.500 1.2201 0.07908 0.07541 0.0149 0.0013 1.0000 17.750 1.1948 0.08707 0.08358 0.0116 0.0013 1.0000 18.000 1.1887 0.09203 0.08864 0.0093 0.0013 1.0000 18.250 1.1715 0.09914 0.09589 0.0059 0.0013 1.0000 18.500 1.1513 0.10702 0.10391 0.0020 0.0013 1.0000 18.750 1.1391 0.11356 0.11057 -0.0014 0.0013 1.0000 19.000 1.1255 0.12051 0.11762 -0.0050 0.0013 1.0000 19.250 1.1121 0.12754 0.12476 -0.0088 0.0013 1.0000