XFOIL Version 6.96 Calculated polar for: AG19 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.500 -0.5320 0.10933 0.10441 0.0143 1.0000 0.0369 -8.250 -0.5300 0.10654 0.10169 0.0097 1.0000 0.0384 -8.000 -0.5267 0.10350 0.09871 0.0052 1.0000 0.0388 -7.750 -0.5203 0.09994 0.09521 0.0005 1.0000 0.0391 -7.500 -0.5093 0.09571 0.09100 -0.0055 1.0000 0.0392 -7.250 -0.5072 0.09098 0.08632 0.0031 1.0000 0.0421 -7.000 -0.4975 0.08741 0.08278 0.0012 1.0000 0.0439 -6.750 -0.4864 0.08339 0.07879 -0.0026 1.0000 0.0451 -6.500 -0.4732 0.07905 0.07446 -0.0073 1.0000 0.0458 -6.250 -0.4576 0.07441 0.06982 -0.0126 1.0000 0.0462 -6.000 -0.4394 0.06938 0.06477 -0.0183 1.0000 0.0455 -5.750 -0.4080 0.05969 0.05487 -0.0295 1.0000 0.0257 -5.500 -0.3871 0.05459 0.04967 -0.0336 1.0000 0.0245 -5.250 -0.3619 0.04900 0.04390 -0.0384 1.0000 0.0234 -5.000 -0.3341 0.04318 0.03781 -0.0429 1.0000 0.0224 -4.750 -0.3049 0.03750 0.03172 -0.0466 1.0000 0.0216 -4.500 -0.2753 0.03241 0.02605 -0.0491 1.0000 0.0210 -4.250 -0.2457 0.02815 0.02119 -0.0506 1.0000 0.0207 -4.000 -0.2166 0.02482 0.01727 -0.0513 1.0000 0.0209 -3.750 -0.1883 0.02230 0.01424 -0.0514 1.0000 0.0219 -3.500 -0.1605 0.02064 0.01217 -0.0512 1.0000 0.0253 -3.250 -0.1329 0.01906 0.01022 -0.0508 1.0000 0.0274 -3.000 -0.1063 0.01716 0.00818 -0.0505 1.0000 0.0299 -2.750 -0.0798 0.01601 0.00694 -0.0501 1.0000 0.0342 -2.500 -0.0534 0.01511 0.00594 -0.0498 1.0000 0.0444 -2.250 -0.0266 0.01421 0.00500 -0.0494 1.0000 0.0595 -2.000 0.0001 0.01337 0.00432 -0.0493 1.0000 0.0997 -1.750 0.0264 0.01257 0.00394 -0.0493 1.0000 0.1972 -1.500 0.0523 0.01184 0.00375 -0.0493 1.0000 0.3492 -1.250 0.0777 0.01106 0.00361 -0.0489 1.0000 0.5490 -1.000 0.0960 0.00991 0.00341 -0.0459 1.0000 1.0000 -0.750 0.1221 0.00998 0.00327 -0.0457 1.0000 1.0000 -0.500 0.1478 0.01007 0.00320 -0.0454 1.0000 1.0000 -0.250 0.1861 0.01017 0.00314 -0.0478 0.9887 1.0000 0.000 0.2292 0.01025 0.00305 -0.0509 0.9713 1.0000 0.250 0.2690 0.01031 0.00300 -0.0532 0.9506 1.0000 0.500 0.3077 0.01035 0.00297 -0.0552 0.9282 1.0000 0.750 0.3430 0.01040 0.00294 -0.0563 0.9021 1.0000 1.000 0.3756 0.01047 0.00292 -0.0567 0.8733 1.0000 1.250 0.4048 0.01055 0.00293 -0.0564 0.8408 1.0000 1.500 0.4322 0.01067 0.00294 -0.0556 0.8064 1.0000 1.750 0.4583 0.01083 0.00302 -0.0546 0.7692 1.0000 2.000 0.4839 0.01101 0.00307 -0.0535 0.7298 1.0000 2.250 0.5094 0.01124 0.00316 -0.0525 0.6873 1.0000 2.500 0.5348 0.01151 0.00327 -0.0515 0.6415 1.0000 2.750 0.5600 0.01183 0.00341 -0.0506 0.5918 1.0000 3.000 0.5850 0.01220 0.00364 -0.0497 0.5400 1.0000 3.250 0.6099 0.01263 0.00386 -0.0489 0.4885 1.0000 3.500 0.6350 0.01309 0.00413 -0.0482 0.4392 1.0000 3.750 0.6601 0.01359 0.00445 -0.0476 0.3936 1.0000 4.000 0.6854 0.01410 0.00482 -0.0472 0.3521 1.0000 4.250 0.7106 0.01464 0.00530 -0.0467 0.3137 1.0000 4.500 0.7360 0.01518 0.00576 -0.0463 0.2784 1.0000 4.750 0.7612 0.01576 0.00626 -0.0459 0.2460 1.0000 5.000 0.7864 0.01635 0.00682 -0.0455 0.2156 1.0000 5.250 0.8115 0.01699 0.00742 -0.0452 0.1877 1.0000 5.500 0.8363 0.01768 0.00815 -0.0448 0.1620 1.0000 5.750 0.8610 0.01842 0.00891 -0.0444 0.1398 1.0000 6.000 0.8855 0.01921 0.00972 -0.0439 0.1188 1.0000 6.250 0.9096 0.02010 0.01067 -0.0434 0.1022 1.0000 6.500 0.9332 0.02106 0.01164 -0.0430 0.0857 1.0000 6.750 0.9564 0.02217 0.01282 -0.0424 0.0728 1.0000 7.000 0.9791 0.02333 0.01407 -0.0418 0.0598 1.0000 7.250 1.0018 0.02458 0.01558 -0.0411 0.0496 1.0000 7.500 1.0237 0.02602 0.01721 -0.0404 0.0404 1.0000 7.750 1.0438 0.02784 0.01919 -0.0395 0.0341 1.0000 8.000 1.0642 0.02966 0.02128 -0.0386 0.0288 1.0000 8.250 1.0823 0.03177 0.02358 -0.0378 0.0244 1.0000 8.500 1.1001 0.03451 0.02676 -0.0365 0.0219 1.0000 8.750 1.1155 0.03755 0.03022 -0.0354 0.0201 1.0000 9.000 1.1294 0.04010 0.03305 -0.0345 0.0182 1.0000 9.500 1.1423 0.04745 0.04123 -0.0325 0.0155 1.0000 9.750 1.1413 0.05189 0.04619 -0.0316 0.0149 1.0000 10.000 1.1330 0.05672 0.05145 -0.0310 0.0147 1.0000 10.250 1.1177 0.06143 0.05648 -0.0308 0.0146 1.0000 10.500 1.0994 0.06679 0.06207 -0.0329 0.0147 1.0000 10.750 1.0808 0.07368 0.06916 -0.0382 0.0149 1.0000 11.000 1.0619 0.08258 0.07820 -0.0458 0.0152 1.0000 11.250 1.0431 0.09250 0.08819 -0.0534 0.0158 1.0000 11.500 1.0249 0.10206 0.09776 -0.0593 0.0163 1.0000