XFOIL Version 6.94 Calculated polar for: GOE 143 (MVA H.20) AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.2872 0.01005 0.00290 -0.0552 0.6556 0.0706 0.500 0.3419 0.01009 0.00265 -0.0545 0.5829 0.0743 1.000 0.3973 0.01005 0.00245 -0.0540 0.5298 0.0820 1.500 0.4526 0.01015 0.00239 -0.0536 0.4752 0.0929 2.000 0.5085 0.01024 0.00239 -0.0533 0.4378 0.1128 2.500 0.5604 0.00814 0.00251 -0.0526 0.4102 1.0000 3.000 0.6162 0.00848 0.00266 -0.0522 0.3834 1.0000 3.500 0.6720 0.00883 0.00287 -0.0519 0.3588 1.0000 4.000 0.7276 0.00918 0.00310 -0.0515 0.3350 1.0000 4.500 0.7827 0.00959 0.00334 -0.0511 0.3006 1.0000 5.000 0.8375 0.01002 0.00368 -0.0507 0.2712 1.0000 5.500 0.8904 0.01078 0.00415 -0.0501 0.2077 1.0000 6.000 0.9404 0.01199 0.00494 -0.0493 0.1427 1.0000 6.500 0.9919 0.01292 0.00573 -0.0485 0.1222 1.0000 7.000 1.0430 0.01380 0.00657 -0.0476 0.1134 1.0000 7.500 1.0941 0.01459 0.00736 -0.0468 0.1057 1.0000 8.000 1.1448 0.01535 0.00817 -0.0460 0.1003 1.0000 8.500 1.1954 0.01608 0.00896 -0.0451 0.0947 1.0000 9.000 1.2450 0.01686 0.00979 -0.0441 0.0869 1.0000 9.500 1.2956 0.01745 0.01048 -0.0433 0.0790 1.0000 10.000 1.3462 0.01803 0.01107 -0.0424 0.0583 1.0000 10.500 1.3847 0.01994 0.01278 -0.0403 0.0330 1.0000 11.000 1.4184 0.02215 0.01510 -0.0376 0.0284 1.0000 11.500 1.4520 0.02403 0.01717 -0.0349 0.0271 1.0000 12.000 1.4693 0.02687 0.02017 -0.0306 0.0246 1.0000 12.500 1.4790 0.02963 0.02313 -0.0257 0.0241 1.0000 13.000 1.4827 0.03343 0.02711 -0.0224 0.0227 1.0000 13.500 1.4718 0.03956 0.03341 -0.0210 0.0219 1.0000 14.000 1.4706 0.04562 0.03972 -0.0215 0.0214 1.0000 14.500 1.4662 0.05274 0.04711 -0.0233 0.0206 1.0000 15.000 1.4551 0.06109 0.05569 -0.0258 0.0200 1.0000 15.500 1.4412 0.06994 0.06471 -0.0287 0.0194 1.0000 16.000 1.4268 0.07847 0.07336 -0.0309 0.0189 1.0000 16.500 1.4138 0.08726 0.08233 -0.0335 0.0185 1.0000 17.000 1.3964 0.09790 0.09326 -0.0384 0.0180 1.0000 17.500 1.3754 0.10965 0.10527 -0.0442 0.0172 1.0000 18.000 1.3614 0.11974 0.11556 -0.0487 0.0168 1.0000 18.500 1.3496 0.12981 0.12579 -0.0536 0.0164 1.0000 19.000 1.3412 0.13880 0.13486 -0.0577 0.0155 1.0000 20.000 1.2983 0.16583 0.16245 -0.0741 0.0150 1.0000