XFOIL Version 6.96 Calculated polar for: DOUGLAS LA203A AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -10.250 -0.0814 0.09880 0.09570 -0.0891 0.7292 0.0287 -10.000 -0.0727 0.09621 0.09309 -0.0904 0.7260 0.0291 -9.750 -0.0645 0.09347 0.09036 -0.0919 0.7228 0.0297 -9.500 -0.0062 0.07358 0.07053 -0.1019 0.7105 0.0319 -9.250 0.0017 0.07104 0.06800 -0.1025 0.7080 0.0321 -9.000 0.0098 0.06848 0.06544 -0.1032 0.7053 0.0322 -8.750 0.0175 0.06592 0.06287 -0.1040 0.7025 0.0324 -8.500 0.0247 0.06324 0.06016 -0.1049 0.6996 0.0326 -8.250 -0.1498 0.03637 0.03281 -0.1470 0.7061 0.0322 -8.000 -0.1310 0.03453 0.03087 -0.1491 0.7032 0.0323 -7.750 -0.1361 0.02010 0.01514 -0.1588 0.7004 0.0307 -7.500 -0.1098 0.01841 0.01315 -0.1599 0.6970 0.0310 -7.250 -0.0820 0.01736 0.01192 -0.1607 0.6947 0.0313 -7.000 -0.0532 0.01685 0.01131 -0.1613 0.6922 0.0316 -6.750 -0.0256 0.01537 0.00963 -0.1622 0.6897 0.0321 -6.500 0.0028 0.01461 0.00880 -0.1628 0.6871 0.0324 -6.250 0.0315 0.01416 0.00830 -0.1633 0.6843 0.0327 -6.000 0.0605 0.01381 0.00789 -0.1637 0.6811 0.0330 -5.750 0.0898 0.01340 0.00745 -0.1642 0.6790 0.0334 -5.500 0.1191 0.01300 0.00702 -0.1646 0.6767 0.0338 -5.250 0.1485 0.01262 0.00661 -0.1650 0.6741 0.0342 -5.000 0.1779 0.01225 0.00620 -0.1655 0.6713 0.0346 -4.750 0.2074 0.01191 0.00582 -0.1659 0.6686 0.0350 -4.500 0.2369 0.01165 0.00549 -0.1662 0.6657 0.0355 -4.250 0.2667 0.01142 0.00522 -0.1667 0.6631 0.0359 -4.000 0.2967 0.01101 0.00480 -0.1672 0.6606 0.0364 -3.750 0.3270 0.01056 0.00436 -0.1679 0.6577 0.0372 -3.500 0.3571 0.01035 0.00416 -0.1684 0.6548 0.0378 -3.250 0.3870 0.01020 0.00400 -0.1688 0.6518 0.0386 -3.000 0.4169 0.01008 0.00384 -0.1692 0.6484 0.0395 -2.750 0.4473 0.00992 0.00368 -0.1698 0.6458 0.0403 -2.500 0.4776 0.00978 0.00353 -0.1702 0.6430 0.0409 -2.250 0.5092 0.00944 0.00321 -0.1712 0.6399 0.0421 -2.000 0.5398 0.00930 0.00307 -0.1717 0.6368 0.0432 -1.750 0.5700 0.00921 0.00297 -0.1722 0.6335 0.0444 -1.500 0.6002 0.00917 0.00289 -0.1727 0.6298 0.0457 -1.250 0.6313 0.00900 0.00274 -0.1734 0.6272 0.0472 -1.000 0.6622 0.00888 0.00265 -0.1740 0.6240 0.0494 -0.750 0.6926 0.00881 0.00259 -0.1745 0.6205 0.0515 -0.500 0.7232 0.00873 0.00249 -0.1751 0.6170 0.0543 -0.250 0.7533 0.00872 0.00245 -0.1756 0.6130 0.0577 0.000 0.7842 0.00862 0.00241 -0.1762 0.6101 0.0638 0.250 0.8151 0.00853 0.00239 -0.1768 0.6067 0.0767 0.750 0.8893 0.00757 0.00237 -0.1818 0.5992 0.4543 1.000 0.9224 0.00744 0.00250 -0.1831 0.5950 0.5795 1.250 0.9530 0.00742 0.00258 -0.1836 0.5919 0.6159 1.500 0.9829 0.00745 0.00265 -0.1840 0.5883 0.6369 1.750 1.0123 0.00751 0.00273 -0.1842 0.5845 0.6536 2.000 1.0411 0.00760 0.00280 -0.1844 0.5802 0.6667 2.250 1.0701 0.00769 0.00289 -0.1845 0.5763 0.6782 2.500 1.0995 0.00772 0.00298 -0.1848 0.5726 0.6907 2.750 1.1285 0.00780 0.00305 -0.1849 0.5686 0.7001 3.000 1.1570 0.00788 0.00314 -0.1851 0.5644 0.7068 3.250 1.1853 0.00800 0.00324 -0.1851 0.5599 0.7118 3.500 1.2145 0.00805 0.00331 -0.1854 0.5560 0.7167 3.750 1.2432 0.00812 0.00340 -0.1856 0.5514 0.7221 4.000 1.2711 0.00823 0.00350 -0.1856 0.5465 0.7276 4.250 1.2991 0.00835 0.00362 -0.1856 0.5416 0.7336 4.500 1.3277 0.00842 0.00371 -0.1858 0.5361 0.7400 4.750 1.3549 0.00854 0.00383 -0.1857 0.5291 0.7466 5.000 1.3825 0.00866 0.00396 -0.1857 0.5218 0.7529 5.250 1.4095 0.00880 0.00408 -0.1855 0.5128 0.7590 5.500 1.4362 0.00895 0.00423 -0.1854 0.5030 0.7656 5.750 1.4614 0.00918 0.00441 -0.1849 0.4910 0.7725 6.000 1.4877 0.00935 0.00458 -0.1847 0.4786 0.7793 6.250 1.5131 0.00956 0.00478 -0.1843 0.4669 0.7872 6.750 1.5629 0.01004 0.00523 -0.1834 0.4447 0.8038 7.000 1.5873 0.01030 0.00547 -0.1829 0.4341 0.8129 7.250 1.6100 0.01062 0.00577 -0.1821 0.4220 0.8222 7.500 1.6332 0.01091 0.00605 -0.1814 0.4088 0.8326 7.750 1.6544 0.01128 0.00639 -0.1803 0.3938 0.8445 8.000 1.6740 0.01170 0.00678 -0.1789 0.3772 0.8572 8.250 1.6912 0.01221 0.00723 -0.1772 0.3583 0.8715 8.500 1.7044 0.01283 0.00778 -0.1747 0.3369 0.8887 8.750 1.7101 0.01351 0.00840 -0.1708 0.3115 0.9139 9.000 1.7027 0.01420 0.00904 -0.1644 0.2878 0.9999 9.250 1.7018 0.01557 0.01021 -0.1602 0.2544 0.9999 9.500 1.7016 0.01705 0.01153 -0.1565 0.2260 0.9999 9.750 1.7011 0.01873 0.01307 -0.1531 0.2017 0.9999 10.000 1.7017 0.02052 0.01475 -0.1503 0.1794 0.9999 10.250 1.7018 0.02250 0.01663 -0.1477 0.1598 0.9999 10.500 1.7033 0.02448 0.01854 -0.1455 0.1435 0.9999 10.750 1.7054 0.02648 0.02048 -0.1434 0.1291 0.9999 11.000 1.7071 0.02855 0.02249 -0.1414 0.1163 0.9999 11.250 1.7087 0.03064 0.02454 -0.1395 0.1052 0.9999 11.500 1.7111 0.03269 0.02657 -0.1377 0.0957 0.9999 11.750 1.7131 0.03478 0.02864 -0.1359 0.0874 0.9999 12.000 1.7145 0.03696 0.03081 -0.1341 0.0802 0.9999 12.250 1.7155 0.03924 0.03307 -0.1324 0.0736 0.9999 12.500 1.7185 0.04137 0.03521 -0.1309 0.0683 0.9999 12.750 1.7203 0.04364 0.03747 -0.1294 0.0633 0.9999 13.000 1.7231 0.04587 0.03973 -0.1281 0.0590 0.9999 13.250 1.7255 0.04820 0.04207 -0.1268 0.0553 0.9999 13.500 1.7289 0.05043 0.04432 -0.1256 0.0521 0.9999 13.750 1.7303 0.05293 0.04683 -0.1244 0.0491 0.9999 14.000 1.7348 0.05512 0.04905 -0.1234 0.0467 0.9999 14.250 1.7357 0.05775 0.05170 -0.1223 0.0444 0.9999 14.500 1.7395 0.06006 0.05405 -0.1214 0.0426 0.9999 14.750 1.7420 0.06255 0.05659 -0.1205 0.0408 0.9999 15.000 1.7435 0.06516 0.05921 -0.1196 0.0389 0.9999 15.250 1.7442 0.06792 0.06202 -0.1187 0.0376 0.9999 15.500 1.7488 0.07025 0.06439 -0.1180 0.0363 0.9999 15.750 1.7500 0.07300 0.06719 -0.1173 0.0351 0.9999 16.000 1.7506 0.07579 0.07001 -0.1167 0.0339 0.9999 16.250 1.7495 0.07885 0.07312 -0.1160 0.0328 0.9999 16.500 1.7530 0.08135 0.07569 -0.1155 0.0320 0.9999 16.750 1.7543 0.08417 0.07856 -0.1151 0.0312 0.9999 17.000 1.7549 0.08706 0.08150 -0.1146 0.0303 0.9999 17.250 1.7535 0.09023 0.08471 -0.1143 0.0295 0.9999