XFOIL Version 6.96 Calculated polar for: GOE 243 (MVA PR.3) 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 ------ -------- --------- --------- -------- -------- -------- -11.000 0.1629 0.09525 0.09257 -0.1067 0.7661 0.0297 -10.750 -0.1486 0.04983 0.04670 -0.1379 0.7905 0.0286 -10.500 -0.1730 0.04214 0.03875 -0.1476 0.7825 0.0286 -10.250 -0.1781 0.03679 0.03319 -0.1563 0.7760 0.0285 -10.000 -0.1628 0.03168 0.02784 -0.1675 0.7699 0.0286 -9.750 -0.1360 0.02739 0.02328 -0.1777 0.7637 0.0287 -9.500 -0.1045 0.02476 0.02045 -0.1842 0.7572 0.0288 -9.250 -0.0711 0.02298 0.01858 -0.1889 0.7513 0.0290 -9.000 -0.0373 0.02159 0.01708 -0.1928 0.7444 0.0292 -8.750 -0.0033 0.02047 0.01582 -0.1962 0.7377 0.0294 -8.500 0.0317 0.01939 0.01469 -0.1994 0.7335 0.0295 -8.250 0.0662 0.01845 0.01367 -0.2022 0.7283 0.0297 -8.000 0.1000 0.01765 0.01278 -0.2046 0.7229 0.0299 -7.750 0.1333 0.01695 0.01198 -0.2066 0.7171 0.0301 -7.500 0.1670 0.01625 0.01124 -0.2085 0.7128 0.0303 -7.250 0.2004 0.01564 0.01057 -0.2103 0.7076 0.0305 -7.000 0.2333 0.01510 0.00996 -0.2118 0.7021 0.0308 -6.750 0.2662 0.01463 0.00940 -0.2132 0.6963 0.0310 -6.500 0.2997 0.01414 0.00889 -0.2148 0.6918 0.0313 -6.250 0.3332 0.01372 0.00841 -0.2162 0.6865 0.0317 -6.000 0.3664 0.01336 0.00798 -0.2176 0.6807 0.0320 -5.750 0.3998 0.01309 0.00764 -0.2190 0.6752 0.0323 -5.500 0.4341 0.01255 0.00708 -0.2207 0.6700 0.0328 -5.250 0.4688 0.01210 0.00661 -0.2225 0.6644 0.0333 -5.000 0.5025 0.01181 0.00627 -0.2240 0.6581 0.0338 -4.750 0.5365 0.01152 0.00595 -0.2255 0.6530 0.0343 -4.500 0.5701 0.01125 0.00566 -0.2268 0.6467 0.0348 -4.250 0.6030 0.01105 0.00539 -0.2280 0.6394 0.0353 -4.000 0.6360 0.01084 0.00513 -0.2292 0.6329 0.0359 -3.750 0.6686 0.01067 0.00491 -0.2302 0.6253 0.0364 -3.500 0.7006 0.01053 0.00468 -0.2311 0.6168 0.0370 -3.250 0.7347 0.01024 0.00437 -0.2326 0.6096 0.0381 -3.000 0.7662 0.01014 0.00421 -0.2333 0.6017 0.0391 -2.750 0.7973 0.01007 0.00409 -0.2340 0.5945 0.0403 -2.500 0.8285 0.00999 0.00398 -0.2346 0.5864 0.0416 -2.250 0.8591 0.00995 0.00386 -0.2352 0.5767 0.0440 -2.000 0.8898 0.00991 0.00379 -0.2357 0.5675 0.0464 -1.750 0.9197 0.00990 0.00372 -0.2361 0.5569 0.0514 -1.500 0.9508 0.00982 0.00367 -0.2368 0.5475 0.0667 -1.250 0.9812 0.00976 0.00363 -0.2374 0.5371 0.1015 -1.000 1.0162 0.00924 0.00348 -0.2395 0.5266 0.2714 -0.750 1.0444 0.00936 0.00357 -0.2395 0.5150 0.2922 -0.500 1.0720 0.00953 0.00367 -0.2394 0.5019 0.3047 -0.250 1.1000 0.00966 0.00378 -0.2394 0.4904 0.3162 0.000 1.1267 0.00988 0.00391 -0.2391 0.4784 0.3228 0.250 1.1544 0.01002 0.00402 -0.2390 0.4678 0.3310 0.500 1.1811 0.01023 0.00416 -0.2388 0.4580 0.3388 0.750 1.2084 0.01039 0.00429 -0.2386 0.4492 0.3461 1.000 1.2346 0.01060 0.00446 -0.2383 0.4403 0.3553 1.250 1.2618 0.01075 0.00459 -0.2381 0.4334 0.3612 1.500 1.2878 0.01096 0.00474 -0.2377 0.4256 0.3665 1.750 1.3144 0.01113 0.00490 -0.2375 0.4189 0.3734 2.000 1.3407 0.01130 0.00505 -0.2372 0.4121 0.3785 2.250 1.3653 0.01156 0.00524 -0.2366 0.4043 0.3829 2.500 1.3914 0.01172 0.00539 -0.2363 0.3983 0.3871 2.750 1.4168 0.01191 0.00557 -0.2358 0.3917 0.3947 3.000 1.4406 0.01217 0.00579 -0.2351 0.3852 0.4013 3.250 1.4659 0.01234 0.00596 -0.2347 0.3809 0.4070 3.500 1.4907 0.01252 0.00615 -0.2341 0.3759 0.4147 3.750 1.5139 0.01276 0.00638 -0.2333 0.3703 0.4223 4.000 1.5351 0.01305 0.00664 -0.2322 0.3645 0.4289 4.250 1.5563 0.01322 0.00684 -0.2309 0.3602 0.4371 4.500 1.5762 0.01349 0.00711 -0.2295 0.3543 0.4456 4.750 1.5951 0.01389 0.00746 -0.2280 0.3473 0.4527 5.000 1.6177 0.01414 0.00774 -0.2272 0.3424 0.4625 5.250 1.6385 0.01447 0.00808 -0.2261 0.3366 0.4717 5.500 1.6566 0.01494 0.00851 -0.2246 0.3294 0.4803 5.750 1.6777 0.01527 0.00887 -0.2236 0.3239 0.4897 6.000 1.6961 0.01573 0.00931 -0.2221 0.3168 0.4970 6.250 1.7138 0.01625 0.00982 -0.2207 0.3095 0.5047 6.500 1.7317 0.01676 0.01032 -0.2192 0.3015 0.5121 6.750 1.7468 0.01743 0.01093 -0.2174 0.2922 0.5181 7.000 1.7613 0.01814 0.01161 -0.2156 0.2810 0.5239 7.250 1.7739 0.01898 0.01241 -0.2136 0.2677 0.5295 7.500 1.7817 0.02013 0.01345 -0.2109 0.2500 0.5349 7.750 1.7841 0.02166 0.01483 -0.2077 0.2271 0.5392 8.000 1.7825 0.02352 0.01653 -0.2042 0.2019 0.5430 8.250 1.7860 0.02512 0.01806 -0.2014 0.1879 0.5473 8.500 1.7946 0.02642 0.01935 -0.1994 0.1811 0.5515 8.750 1.8046 0.02766 0.02058 -0.1975 0.1769 0.5556 9.000 1.8134 0.02902 0.02194 -0.1957 0.1728 0.5592 9.250 1.8255 0.03016 0.02310 -0.1942 0.1707 0.5622 9.500 1.8375 0.03132 0.02431 -0.1928 0.1694 0.5666 9.750 1.8494 0.03250 0.02554 -0.1914 0.1680 0.5704 10.000 1.8596 0.03386 0.02694 -0.1899 0.1668 0.5742 10.250 1.8702 0.03521 0.02832 -0.1885 0.1656 0.5777 10.500 1.8790 0.03675 0.02989 -0.1870 0.1644 0.5805 10.750 1.8881 0.03828 0.03146 -0.1857 0.1632 0.5832 11.000 1.8955 0.04001 0.03324 -0.1842 0.1621 0.5866 11.250 1.9028 0.04175 0.03502 -0.1828 0.1609 0.5899 11.500 1.9080 0.04374 0.03707 -0.1813 0.1597 0.5929 11.750 1.9138 0.04568 0.03907 -0.1799 0.1587 0.5959 12.000 1.9187 0.04778 0.04122 -0.1786 0.1580 0.5987 12.250 1.9276 0.04945 0.04295 -0.1775 0.1577 0.6011 12.500 1.9348 0.05136 0.04493 -0.1764 0.1575 0.6044 12.750 1.9427 0.05319 0.04683 -0.1754 0.1572 0.6075 13.000 1.9492 0.05519 0.04890 -0.1743 0.1568 0.6104 13.250 1.9556 0.05722 0.05100 -0.1733 0.1564 0.6132 13.500 1.9615 0.05932 0.05316 -0.1723 0.1560 0.6160 13.750 1.9658 0.06158 0.05550 -0.1713 0.1557 0.6185 14.000 1.9707 0.06379 0.05776 -0.1704 0.1553 0.6207 14.250 1.9739 0.06625 0.06031 -0.1695 0.1549 0.6237 14.500 1.9786 0.06852 0.06265 -0.1686 0.1545 0.6265 14.750 1.9808 0.07112 0.06533 -0.1677 0.1539 0.6292 15.000 1.9848 0.07348 0.06775 -0.1670 0.1533 0.6320 15.250 1.9864 0.07616 0.07049 -0.1662 0.1526 0.6346 15.500 1.9889 0.07872 0.07311 -0.1654 0.1519 0.6372 15.750 1.9897 0.08151 0.07596 -0.1647 0.1513 0.6396 16.000 1.9905 0.08432 0.07885 -0.1641 0.1506 0.6428 16.250 1.9907 0.08719 0.08179 -0.1635 0.1498 0.6457 16.500 1.9889 0.09032 0.08498 -0.1629 0.1488 0.6483 16.750 1.9883 0.09325 0.08796 -0.1624 0.1479 0.6509