GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il) Reynolds number: 100,000 Max Cl/Cd: 61.21 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe301-il-100000-n5.txt Download as CSV file: xf-goe301-il-100000-n5.csv |
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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2506 0.11836 0.11360 -0.0342 1.0000 0.0434
-9.000 -0.2597 0.11736 0.11270 -0.0332 1.0000 0.0435
-8.750 -0.2710 0.11649 0.11193 -0.0317 1.0000 0.0436
-8.500 -0.2574 0.11170 0.10717 -0.0321 0.9982 0.0439
-8.250 -0.2357 0.10676 0.10221 -0.0336 0.9951 0.0449
-8.000 -0.2169 0.10298 0.09843 -0.0369 0.9896 0.0465
-7.750 -0.1992 0.09952 0.09496 -0.0414 0.9826 0.0489
-7.500 -0.1859 0.09679 0.09225 -0.0483 0.9699 0.0511
-7.250 -0.1627 0.09329 0.08873 -0.0604 0.9555 0.0517
-7.000 -0.1403 0.08881 0.08423 -0.0670 0.9457 0.0520
-6.750 -0.1240 0.08425 0.07969 -0.0645 0.9409 0.0529
-6.500 -0.1026 0.08061 0.07604 -0.0665 0.9336 0.0548
-6.250 -0.0763 0.07695 0.07234 -0.0724 0.9244 0.0583
-6.000 -0.0323 0.07297 0.06815 -0.0895 0.9100 0.0612
-5.750 -0.0040 0.06841 0.06351 -0.0952 0.8992 0.0617
-5.500 0.0145 0.06447 0.05960 -0.0943 0.8911 0.0628
-5.250 0.0353 0.06157 0.05667 -0.0952 0.8780 0.0654
-5.000 0.0854 0.05820 0.05293 -0.1078 0.8637 0.0719
-4.750 0.1198 0.05423 0.04873 -0.1133 0.8518 0.0725
-4.500 0.1400 0.05064 0.04517 -0.1136 0.8410 0.0736
-4.250 0.1626 0.04807 0.04256 -0.1145 0.8277 0.0757
-3.750 0.2349 0.04242 0.03633 -0.1232 0.8036 0.0858
-3.500 0.2795 0.03735 0.03059 -0.1277 0.7936 0.0613
-3.250 0.3071 0.03496 0.02807 -0.1290 0.7818 0.0607
-3.000 0.3409 0.03262 0.02532 -0.1309 0.7711 0.0611
-2.500 0.4014 0.02869 0.02092 -0.1332 0.7500 0.0593
-2.250 0.4328 0.02697 0.01886 -0.1341 0.7401 0.0588
-2.000 0.4644 0.02547 0.01696 -0.1349 0.7304 0.0591
-1.750 0.4952 0.02432 0.01531 -0.1352 0.7202 0.0610
-1.250 0.5538 0.02229 0.01269 -0.1356 0.7011 0.0619
-1.000 0.5825 0.02149 0.01170 -0.1357 0.6920 0.0628
-0.750 0.6103 0.02088 0.01094 -0.1356 0.6824 0.0639
-0.500 0.6379 0.02046 0.01039 -0.1354 0.6730 0.0667
-0.250 0.6660 0.02005 0.00979 -0.1352 0.6639 0.0699
0.000 0.6931 0.01967 0.00924 -0.1348 0.6542 0.0716
0.250 0.7207 0.01921 0.00870 -0.1345 0.6456 0.0737
0.500 0.7465 0.01891 0.00843 -0.1341 0.6355 0.0770
0.750 0.7735 0.01874 0.00815 -0.1337 0.6269 0.0830
1.000 0.7988 0.01848 0.00793 -0.1331 0.6167 0.0877
1.250 0.8249 0.01835 0.00775 -0.1327 0.6076 0.0944
1.500 0.8515 0.01826 0.00761 -0.1323 0.5979 0.1041
1.750 0.8778 0.01825 0.00755 -0.1319 0.5878 0.1157
2.000 0.9049 0.01820 0.00748 -0.1316 0.5788 0.1370
2.500 0.9529 0.01685 0.00765 -0.1300 0.5580 1.0000
2.750 0.9783 0.01707 0.00769 -0.1294 0.5478 1.0000
3.000 1.0032 0.01731 0.00784 -0.1287 0.5370 1.0000
3.250 1.0285 0.01756 0.00796 -0.1282 0.5276 1.0000
3.500 1.0533 0.01782 0.00814 -0.1276 0.5178 1.0000
3.750 1.0782 0.01810 0.00836 -0.1270 0.5086 1.0000
4.000 1.1032 0.01837 0.00855 -0.1264 0.5002 1.0000
4.250 1.1276 0.01868 0.00884 -0.1258 0.4911 1.0000
4.500 1.1524 0.01898 0.00904 -0.1253 0.4833 1.0000
4.750 1.1762 0.01932 0.00941 -0.1246 0.4741 1.0000
5.000 1.2005 0.01965 0.00965 -0.1239 0.4661 1.0000
5.250 1.2238 0.02002 0.01004 -0.1232 0.4567 1.0000
5.500 1.2475 0.02038 0.01036 -0.1225 0.4485 1.0000
5.750 1.2702 0.02076 0.01075 -0.1216 0.4391 1.0000
6.000 1.2928 0.02116 0.01114 -0.1208 0.4300 1.0000
6.250 1.3150 0.02156 0.01154 -0.1199 0.4208 1.0000
6.500 1.3368 0.02200 0.01202 -0.1190 0.4118 1.0000
6.750 1.3588 0.02243 0.01243 -0.1180 0.4035 1.0000
7.000 1.3792 0.02289 0.01298 -0.1169 0.3938 1.0000
7.250 1.3999 0.02335 0.01342 -0.1158 0.3850 1.0000
7.500 1.4191 0.02383 0.01400 -0.1145 0.3749 1.0000
7.750 1.4384 0.02432 0.01453 -0.1132 0.3660 1.0000
8.000 1.4571 0.02484 0.01513 -0.1118 0.3572 1.0000
8.250 1.4753 0.02538 0.01576 -0.1104 0.3486 1.0000
8.500 1.4928 0.02593 0.01635 -0.1089 0.3403 1.0000
8.750 1.5095 0.02653 0.01708 -0.1073 0.3317 1.0000
9.000 1.5255 0.02714 0.01773 -0.1056 0.3241 1.0000
9.250 1.5401 0.02780 0.01854 -0.1037 0.3155 1.0000
9.750 1.5646 0.02922 0.02013 -0.0992 0.2998 1.0000
10.000 1.5759 0.03000 0.02096 -0.0969 0.2927 1.0000
10.250 1.5863 0.03088 0.02200 -0.0947 0.2845 1.0000
10.500 1.5959 0.03180 0.02294 -0.0924 0.2778 1.0000
10.750 1.6048 0.03285 0.02416 -0.0901 0.2699 1.0000
11.000 1.6128 0.03392 0.02527 -0.0879 0.2633 1.0000
11.250 1.6203 0.03515 0.02668 -0.0857 0.2560 1.0000
11.500 1.6269 0.03643 0.02803 -0.0836 0.2495 1.0000
11.750 1.6331 0.03783 0.02956 -0.0816 0.2428 1.0000
12.000 1.6368 0.03939 0.03123 -0.0795 0.2356 1.0000
12.250 1.6392 0.04111 0.03303 -0.0775 0.2282 1.0000
12.500 1.6387 0.04309 0.03512 -0.0755 0.2201 1.0000
12.750 1.6373 0.04526 0.03739 -0.0738 0.2120 1.0000
13.000 1.6337 0.04772 0.03995 -0.0722 0.2037 1.0000
13.250 1.6295 0.05044 0.04280 -0.0710 0.1953 1.0000
13.500 1.6241 0.05334 0.04576 -0.0700 0.1877 1.0000
13.750 1.6187 0.05652 0.04912 -0.0693 0.1799 1.0000
14.000 1.6115 0.05989 0.05254 -0.0687 0.1731 1.0000
14.250 1.6040 0.06360 0.05644 -0.0685 0.1655 1.0000
14.500 1.5943 0.06759 0.06048 -0.0684 0.1587 1.0000
14.750 1.5841 0.07192 0.06497 -0.0687 0.1513 1.0000
15.000 1.5727 0.07646 0.06956 -0.0691 0.1451 1.0000
15.250 1.5617 0.08116 0.07443 -0.0697 0.1389 1.0000
15.500 1.5496 0.08602 0.07934 -0.0705 0.1335 1.0000
15.750 1.5386 0.09101 0.08450 -0.0715 0.1280 1.0000
16.000 1.5259 0.09632 0.08992 -0.0727 0.1225 1.0000
16.250 1.5134 0.10167 0.09534 -0.0741 0.1173 1.0000
16.500 1.5001 0.10742 0.10128 -0.0759 0.1115 1.0000
16.750 1.4861 0.11325 0.10716 -0.0778 0.1057 1.0000
17.000 1.4725 0.11938 0.11351 -0.0801 0.0989 1.0000
17.250 1.4576 0.12574 0.11998 -0.0826 0.0915 1.0000
17.500 1.4427 0.13235 0.12678 -0.0854 0.0806 1.0000
17.750 1.4272 0.13906 0.13350 -0.0886 0.0693 1.0000
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