GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il) Reynolds number: 500,000 Max Cl/Cd: 114.65 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe303-il-500000.txt Download as CSV file: xf-goe303-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2828 0.12029 0.11791 -0.0363 1.0000 0.0220
-10.500 -0.2908 0.11769 0.11534 -0.0380 1.0000 0.0222
-10.250 -0.2984 0.11533 0.11302 -0.0381 1.0000 0.0222
-10.000 -0.2943 0.11212 0.10984 -0.0360 1.0000 0.0224
-9.750 -0.2946 0.11026 0.10802 -0.0335 1.0000 0.0225
-9.500 -0.2912 0.10811 0.10589 -0.0327 0.9995 0.0227
-9.250 -0.2754 0.10473 0.10250 -0.0357 0.9979 0.0231
-9.000 -0.2595 0.10120 0.09897 -0.0393 0.9960 0.0237
-8.750 -0.2433 0.09745 0.09522 -0.0434 0.9942 0.0245
-8.500 -0.2296 0.09307 0.09084 -0.0492 0.9901 0.0261
-8.250 -0.2169 0.08692 0.08468 -0.0621 0.9841 0.0265
-8.000 -0.2032 0.08300 0.08077 -0.0628 0.9807 0.0268
-7.750 -0.1832 0.08018 0.07794 -0.0643 0.9775 0.0272
-7.500 -0.1607 0.07680 0.07456 -0.0689 0.9742 0.0278
-7.250 -0.1387 0.07318 0.07093 -0.0742 0.9697 0.0287
-7.000 -0.1178 0.06914 0.06687 -0.0804 0.9620 0.0301
-6.750 -0.0873 0.06004 0.05765 -0.0978 0.9512 0.0318
-6.500 -0.0696 0.05795 0.05555 -0.0980 0.9454 0.0322
-6.250 -0.0513 0.05587 0.05345 -0.0989 0.9371 0.0328
-6.000 -0.0287 0.05307 0.05058 -0.1019 0.9295 0.0338
-5.750 0.0147 0.04552 0.04270 -0.1144 0.9186 0.0374
-5.500 0.0300 0.04150 0.03862 -0.1158 0.9103 0.0381
-5.250 0.0501 0.04012 0.03720 -0.1158 0.9009 0.0388
-5.000 0.0726 0.03850 0.03551 -0.1164 0.8915 0.0399
-4.750 0.1079 0.03144 0.02790 -0.1219 0.8825 0.0451
-4.500 0.1298 0.03007 0.02651 -0.1219 0.8718 0.0458
-4.250 0.1537 0.02889 0.02526 -0.1220 0.8617 0.0466
-4.000 0.1790 0.02744 0.02368 -0.1223 0.8505 0.0483
-3.750 0.2081 0.02364 0.01940 -0.1234 0.8385 0.0544
-3.500 0.2332 0.02261 0.01831 -0.1234 0.8256 0.0555
-3.250 0.2626 0.01593 0.01060 -0.1235 0.8142 0.0427
-3.000 0.2896 0.01426 0.00857 -0.1232 0.8000 0.0421
-2.750 0.3169 0.01312 0.00714 -0.1228 0.7850 0.0420
-2.500 0.3441 0.01229 0.00606 -0.1225 0.7700 0.0420
-2.250 0.3713 0.01171 0.00529 -0.1221 0.7546 0.0424
-2.000 0.3983 0.01127 0.00468 -0.1217 0.7388 0.0428
-1.500 0.4526 0.01075 0.00391 -0.1210 0.7092 0.0442
-1.250 0.4796 0.01031 0.00339 -0.1208 0.6962 0.0455
-1.000 0.5068 0.01005 0.00308 -0.1205 0.6841 0.0469
-0.750 0.5341 0.00993 0.00290 -0.1203 0.6724 0.0485
-0.500 0.5613 0.00984 0.00275 -0.1200 0.6601 0.0504
-0.250 0.5888 0.00976 0.00262 -0.1198 0.6479 0.0526
0.000 0.6161 0.00964 0.00249 -0.1196 0.6361 0.0579
0.250 0.6433 0.00960 0.00242 -0.1193 0.6252 0.0689
0.500 0.6708 0.00947 0.00239 -0.1192 0.6149 0.1082
0.750 0.6982 0.00942 0.00242 -0.1191 0.6059 0.1489
1.000 0.7254 0.00936 0.00246 -0.1190 0.5968 0.2043
1.250 0.7442 0.00792 0.00268 -0.1176 0.5888 0.8365
1.500 0.7798 0.00785 0.00266 -0.1190 0.5794 1.0000
1.750 0.8071 0.00795 0.00271 -0.1188 0.5701 1.0000
2.000 0.8339 0.00810 0.00275 -0.1186 0.5612 1.0000
2.250 0.8611 0.00821 0.00282 -0.1184 0.5521 1.0000
2.500 0.8880 0.00836 0.00289 -0.1181 0.5437 1.0000
2.750 0.9149 0.00849 0.00297 -0.1179 0.5347 1.0000
3.000 0.9417 0.00863 0.00306 -0.1176 0.5261 1.0000
3.250 0.9683 0.00878 0.00317 -0.1174 0.5168 1.0000
3.500 0.9950 0.00892 0.00327 -0.1171 0.5075 1.0000
3.750 1.0211 0.00910 0.00339 -0.1168 0.4980 1.0000
4.000 1.0476 0.00924 0.00351 -0.1165 0.4872 1.0000
4.250 1.0737 0.00941 0.00365 -0.1162 0.4757 1.0000
4.500 1.0993 0.00960 0.00379 -0.1158 0.4635 1.0000
4.750 1.1247 0.00981 0.00395 -0.1153 0.4502 1.0000
5.000 1.1498 0.01003 0.00413 -0.1148 0.4355 1.0000
5.250 1.1746 0.01027 0.00432 -0.1143 0.4188 1.0000
5.500 1.1989 0.01054 0.00453 -0.1137 0.3989 1.0000
5.750 1.2215 0.01092 0.00479 -0.1128 0.3740 1.0000
6.000 1.2433 0.01138 0.00510 -0.1119 0.3449 1.0000
6.250 1.2649 0.01185 0.00544 -0.1109 0.3198 1.0000
6.500 1.2867 0.01230 0.00579 -0.1099 0.3016 1.0000
6.750 1.3087 0.01272 0.00615 -0.1090 0.2875 1.0000
7.000 1.3308 0.01312 0.00651 -0.1081 0.2764 1.0000
7.250 1.3524 0.01355 0.00689 -0.1071 0.2675 1.0000
7.500 1.3751 0.01388 0.00724 -0.1063 0.2603 1.0000
7.750 1.3960 0.01431 0.00764 -0.1053 0.2526 1.0000
8.000 1.4183 0.01464 0.00800 -0.1044 0.2468 1.0000
8.250 1.4396 0.01501 0.00839 -0.1034 0.2405 1.0000
8.500 1.4597 0.01544 0.00882 -0.1023 0.2341 1.0000
8.750 1.4811 0.01576 0.00919 -0.1013 0.2276 1.0000
9.250 1.5200 0.01654 0.01001 -0.0987 0.2141 1.0000
9.500 1.5359 0.01702 0.01049 -0.0968 0.2070 1.0000
9.750 1.5548 0.01737 0.01090 -0.0954 0.2003 1.0000
10.000 1.5705 0.01788 0.01141 -0.0936 0.1918 1.0000
10.250 1.5885 0.01830 0.01187 -0.0922 0.1814 1.0000
10.500 1.6037 0.01888 0.01243 -0.0904 0.1673 1.0000
10.750 1.6148 0.01971 0.01316 -0.0881 0.1454 1.0000
11.000 1.6195 0.02097 0.01424 -0.0851 0.1186 1.0000
11.250 1.6233 0.02233 0.01551 -0.0821 0.1008 1.0000
11.500 1.6296 0.02360 0.01675 -0.0796 0.0903 1.0000
11.750 1.6370 0.02483 0.01799 -0.0773 0.0827 1.0000
12.000 1.6426 0.02624 0.01941 -0.0750 0.0758 1.0000
12.250 1.6513 0.02746 0.02068 -0.0732 0.0700 1.0000
12.500 1.6561 0.02904 0.02227 -0.0712 0.0635 1.0000
12.750 1.6616 0.03061 0.02386 -0.0694 0.0562 1.0000
13.000 1.6640 0.03250 0.02575 -0.0675 0.0472 1.0000
13.250 1.6624 0.03485 0.02807 -0.0655 0.0368 1.0000
13.500 1.6588 0.03749 0.03070 -0.0637 0.0292 1.0000
13.750 1.6554 0.04026 0.03350 -0.0622 0.0254 1.0000
14.000 1.6532 0.04303 0.03635 -0.0610 0.0233 1.0000
14.250 1.6477 0.04626 0.03965 -0.0600 0.0217 1.0000
14.500 1.6451 0.04931 0.04282 -0.0593 0.0207 1.0000
14.750 1.6420 0.05253 0.04615 -0.0587 0.0198 1.0000
15.000 1.6365 0.05613 0.04986 -0.0584 0.0190 1.0000
15.250 1.6282 0.06020 0.05403 -0.0583 0.0184 1.0000
15.500 1.6166 0.06484 0.05879 -0.0584 0.0178 1.0000
15.750 1.6050 0.06961 0.06368 -0.0588 0.0174 1.0000
16.000 1.5976 0.07388 0.06808 -0.0592 0.0171 1.0000
16.250 1.5887 0.07847 0.07280 -0.0598 0.0168 1.0000
16.500 1.5788 0.08330 0.07775 -0.0606 0.0165 1.0000
16.750 1.5678 0.08835 0.08293 -0.0616 0.0162 1.0000
17.000 1.5564 0.09355 0.08825 -0.0627 0.0159 1.0000
17.250 1.5448 0.09888 0.09369 -0.0640 0.0157 1.0000
17.500 1.5331 0.10432 0.09924 -0.0655 0.0155 1.0000
17.750 1.5210 0.10985 0.10488 -0.0672 0.0153 1.0000
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