XFOIL Version 6.96 Calculated polar for: GOE 301 (FRIEDRICHSHAFEN G 13) 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.1457 0.08727 0.08535 -0.0704 0.9100 0.0106 -9.000 -0.1380 0.08472 0.08268 -0.0716 0.8838 0.0109 -8.750 -0.1322 0.08181 0.07965 -0.0729 0.8555 0.0113 -8.500 -0.1381 0.07601 0.07372 -0.0763 0.8185 0.0125 -8.250 -0.1300 0.07434 0.07179 -0.0771 0.7604 0.0127 -8.000 -0.1174 0.07235 0.06966 -0.0791 0.7285 0.0128 -7.750 -0.1026 0.06998 0.06720 -0.0820 0.7112 0.0131 -7.250 -0.0722 0.05863 0.05573 -0.0975 0.6907 0.0153 -7.000 -0.0505 0.05646 0.05349 -0.1007 0.6807 0.0155 -6.750 -0.0277 0.05424 0.05122 -0.1040 0.6721 0.0158 -6.500 -0.0040 0.05185 0.04876 -0.1075 0.6636 0.0162 -6.250 0.0282 0.04151 0.03821 -0.1212 0.6584 0.0185 -6.000 0.0544 0.03976 0.03638 -0.1234 0.6515 0.0187 -5.750 0.0808 0.03797 0.03450 -0.1254 0.6449 0.0190 -5.500 0.1135 0.01550 0.01056 -0.1395 0.6429 0.0236 -5.250 0.1403 0.01386 0.00861 -0.1399 0.6364 0.0244 -5.000 0.1674 0.01278 0.00727 -0.1400 0.6297 0.0248 -4.750 0.1951 0.01207 0.00639 -0.1401 0.6239 0.0252 -4.500 0.2229 0.01154 0.00571 -0.1401 0.6181 0.0255 -4.250 0.2507 0.01115 0.00519 -0.1400 0.6123 0.0257 -4.000 0.2788 0.01081 0.00475 -0.1400 0.6067 0.0259 -3.750 0.3068 0.01051 0.00434 -0.1400 0.6000 0.0261 -3.500 0.3345 0.01008 0.00381 -0.1399 0.5938 0.0267 -3.250 0.3627 0.00989 0.00358 -0.1399 0.5878 0.0272 -3.000 0.3907 0.00974 0.00339 -0.1398 0.5813 0.0276 -2.750 0.4188 0.00958 0.00318 -0.1398 0.5753 0.0280 -2.500 0.4469 0.00944 0.00299 -0.1397 0.5676 0.0284 -2.250 0.4748 0.00932 0.00281 -0.1396 0.5600 0.0288 -2.000 0.5028 0.00919 0.00264 -0.1396 0.5516 0.0292 -1.750 0.5307 0.00910 0.00249 -0.1395 0.5437 0.0297 -1.500 0.5585 0.00902 0.00236 -0.1394 0.5337 0.0301 -1.250 0.5863 0.00898 0.00225 -0.1393 0.5225 0.0305 -1.000 0.6137 0.00897 0.00217 -0.1391 0.5085 0.0309 -0.750 0.6409 0.00894 0.00206 -0.1389 0.4914 0.0318 -0.500 0.6678 0.00900 0.00204 -0.1387 0.4730 0.0329 -0.250 0.6948 0.00906 0.00203 -0.1385 0.4575 0.0339 0.000 0.7220 0.00912 0.00203 -0.1383 0.4453 0.0349 0.250 0.7491 0.00919 0.00203 -0.1381 0.4331 0.0360 0.500 0.7761 0.00927 0.00205 -0.1379 0.4201 0.0370 0.750 0.8034 0.00931 0.00207 -0.1377 0.4099 0.0395 1.000 0.8305 0.00939 0.00212 -0.1375 0.4022 0.0421 1.250 0.8583 0.00942 0.00215 -0.1375 0.3970 0.0452 1.500 0.8857 0.00948 0.00221 -0.1374 0.3910 0.0499 1.750 0.9129 0.00956 0.00228 -0.1372 0.3852 0.0540 2.000 0.9403 0.00961 0.00234 -0.1371 0.3793 0.0585 2.250 0.9673 0.00971 0.00242 -0.1369 0.3723 0.0617 2.500 0.9945 0.00978 0.00249 -0.1368 0.3666 0.0667 2.750 1.0216 0.00986 0.00257 -0.1367 0.3606 0.0713 3.250 1.0755 0.01003 0.00275 -0.1364 0.3489 0.0869 3.500 1.1023 0.01001 0.00291 -0.1363 0.3416 0.2013 4.000 1.1514 0.00902 0.00337 -0.1355 0.3250 1.0000 4.250 1.1779 0.00918 0.00350 -0.1353 0.3177 1.0000 4.500 1.2037 0.00939 0.00364 -0.1349 0.3086 1.0000 4.750 1.2295 0.00959 0.00379 -0.1346 0.2987 1.0000 5.000 1.2548 0.00983 0.00397 -0.1342 0.2880 1.0000 5.250 1.2798 0.01008 0.00416 -0.1338 0.2776 1.0000 5.500 1.3047 0.01033 0.00436 -0.1334 0.2666 1.0000 5.750 1.3292 0.01060 0.00457 -0.1328 0.2558 1.0000 6.000 1.3535 0.01088 0.00481 -0.1323 0.2469 1.0000 6.250 1.3782 0.01112 0.00502 -0.1318 0.2388 1.0000 6.500 1.4020 0.01141 0.00527 -0.1312 0.2307 1.0000 6.750 1.4265 0.01165 0.00550 -0.1307 0.2244 1.0000 7.000 1.4499 0.01195 0.00577 -0.1301 0.2174 1.0000 7.250 1.4740 0.01219 0.00601 -0.1295 0.2120 1.0000 7.500 1.4972 0.01248 0.00629 -0.1289 0.2056 1.0000 7.750 1.5200 0.01279 0.00658 -0.1281 0.1987 1.0000 8.000 1.5405 0.01324 0.00695 -0.1270 0.1845 1.0000 8.250 1.5575 0.01390 0.00746 -0.1253 0.1598 1.0000 8.500 1.5728 0.01463 0.00805 -0.1234 0.1365 1.0000 8.750 1.5906 0.01515 0.00852 -0.1218 0.1265 1.0000 9.000 1.6077 0.01564 0.00897 -0.1201 0.1194 1.0000 9.250 1.6258 0.01601 0.00936 -0.1185 0.1160 1.0000 9.500 1.6427 0.01644 0.00981 -0.1168 0.1123 1.0000 9.750 1.6586 0.01693 0.01030 -0.1150 0.1082 1.0000 10.000 1.6751 0.01740 0.01079 -0.1133 0.1042 1.0000 10.250 1.6921 0.01784 0.01126 -0.1117 0.1010 1.0000 10.500 1.7062 0.01844 0.01186 -0.1097 0.0954 1.0000 10.750 1.7201 0.01907 0.01249 -0.1078 0.0900 1.0000 11.000 1.7216 0.02043 0.01368 -0.1042 0.0651 1.0000 11.250 1.7216 0.02196 0.01513 -0.1005 0.0488 1.0000 11.500 1.7255 0.02332 0.01648 -0.0977 0.0394 1.0000 11.750 1.7260 0.02500 0.01812 -0.0947 0.0286 1.0000 12.000 1.7241 0.02695 0.02004 -0.0917 0.0181 1.0000 12.250 1.7294 0.02848 0.02161 -0.0897 0.0153 1.0000 12.500 1.7350 0.03004 0.02321 -0.0879 0.0137 1.0000 12.750 1.7409 0.03166 0.02489 -0.0863 0.0125 1.0000 13.000 1.7468 0.03336 0.02665 -0.0849 0.0116 1.0000 13.250 1.7508 0.03529 0.02865 -0.0836 0.0108 1.0000 13.500 1.7535 0.03745 0.03088 -0.0824 0.0100 1.0000 13.750 1.7580 0.03951 0.03302 -0.0815 0.0096 1.0000 14.000 1.7612 0.04179 0.03537 -0.0806 0.0092 1.0000 14.250 1.7627 0.04428 0.03795 -0.0799 0.0088 1.0000 14.500 1.7630 0.04698 0.04072 -0.0792 0.0084 1.0000 14.750 1.7621 0.04989 0.04370 -0.0786 0.0081 1.0000 15.000 1.7593 0.05308 0.04698 -0.0781 0.0077 1.0000 15.250 1.7572 0.05622 0.05021 -0.0778 0.0075 1.0000 15.500 1.7546 0.05947 0.05356 -0.0775 0.0073 1.0000 15.750 1.7510 0.06292 0.05710 -0.0773 0.0071 1.0000 16.000 1.7464 0.06657 0.06084 -0.0773 0.0069 1.0000 16.250 1.7405 0.07042 0.06478 -0.0774 0.0067 1.0000 16.500 1.7337 0.07446 0.06892 -0.0776 0.0065 1.0000 16.750 1.7262 0.07870 0.07325 -0.0779 0.0063 1.0000 17.000 1.7177 0.08315 0.07779 -0.0784 0.0062 1.0000 17.250 1.7081 0.08781 0.08255 -0.0791 0.0060 1.0000 17.500 1.6972 0.09271 0.08756 -0.0799 0.0059 1.0000