GOE 210 (DAIMLER) AIRFOIL (goe210-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 210 (DAIMLER) AIRFOIL (goe210-il) Reynolds number: 200,000 Max Cl/Cd: 77.86 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe210-il-200000-n5.txt Download as CSV file: xf-goe210-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 210 (DAIMLER) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3311 0.08895 0.08571 -0.0238 1.0000 0.0192
-7.000 -0.3324 0.08665 0.08348 -0.0236 1.0000 0.0195
-6.750 -0.3331 0.08432 0.08121 -0.0236 1.0000 0.0198
-6.500 -0.3151 0.08038 0.07729 -0.0289 0.9959 0.0206
-6.250 -0.2856 0.07563 0.07251 -0.0373 0.9892 0.0219
-6.000 -0.2443 0.07054 0.06732 -0.0500 0.9815 0.0234
-5.500 -0.1818 0.05786 0.05448 -0.0654 0.9678 0.0152
-5.250 -0.1468 0.05260 0.04909 -0.0726 0.9590 0.0153
-4.250 -0.0023 0.03183 0.02730 -0.0928 0.9243 0.0163
-4.000 0.0264 0.02929 0.02455 -0.0946 0.9132 0.0171
-3.750 0.0555 0.02801 0.02312 -0.0958 0.9027 0.0193
-3.500 0.0896 0.02441 0.01907 -0.0973 0.8934 0.0208
-3.250 0.1232 0.02056 0.01458 -0.0982 0.8839 0.0224
-3.000 0.1540 0.01832 0.01184 -0.0987 0.8740 0.0256
-2.750 0.1835 0.01710 0.01037 -0.0990 0.8644 0.0277
-2.500 0.2130 0.01604 0.00897 -0.0991 0.8553 0.0312
-2.250 0.2419 0.01519 0.00778 -0.0989 0.8458 0.0337
-2.000 0.2701 0.01400 0.00637 -0.0989 0.8373 0.0360
-1.750 0.2979 0.01348 0.00577 -0.0988 0.8287 0.0393
-1.500 0.3255 0.01290 0.00505 -0.0986 0.8204 0.0407
-1.250 0.3531 0.01245 0.00448 -0.0983 0.8119 0.0422
-1.000 0.3802 0.01211 0.00406 -0.0979 0.8011 0.0436
-0.750 0.4071 0.01189 0.00375 -0.0976 0.7897 0.0458
-0.500 0.4338 0.01160 0.00338 -0.0972 0.7763 0.0468
-0.250 0.4604 0.01142 0.00310 -0.0967 0.7612 0.0477
0.000 0.4872 0.01130 0.00288 -0.0963 0.7472 0.0493
0.250 0.5142 0.01122 0.00274 -0.0959 0.7353 0.0519
0.500 0.5412 0.01117 0.00263 -0.0956 0.7233 0.0575
0.750 0.5680 0.01107 0.00257 -0.0952 0.7092 0.0914
1.000 0.5910 0.00905 0.00263 -0.0943 0.6953 1.0000
1.250 0.6179 0.00915 0.00260 -0.0939 0.6817 1.0000
1.500 0.6449 0.00925 0.00261 -0.0936 0.6692 1.0000
1.750 0.6718 0.00936 0.00264 -0.0933 0.6559 1.0000
2.000 0.6985 0.00948 0.00267 -0.0930 0.6409 1.0000
2.250 0.7250 0.00961 0.00273 -0.0926 0.6238 1.0000
2.500 0.7512 0.00975 0.00279 -0.0922 0.6016 1.0000
2.750 0.7763 0.00997 0.00283 -0.0915 0.5662 1.0000
3.000 0.7997 0.01032 0.00292 -0.0906 0.5102 1.0000
3.250 0.8211 0.01091 0.00309 -0.0894 0.4367 1.0000
3.500 0.8428 0.01157 0.00338 -0.0884 0.3741 1.0000
3.750 0.8656 0.01215 0.00370 -0.0877 0.3270 1.0000
4.000 0.8890 0.01266 0.00405 -0.0871 0.2908 1.0000
4.250 0.9132 0.01311 0.00437 -0.0866 0.2641 1.0000
4.500 0.9374 0.01353 0.00471 -0.0861 0.2431 1.0000
4.750 0.9619 0.01392 0.00507 -0.0856 0.2268 1.0000
5.000 0.9863 0.01432 0.00543 -0.0851 0.2141 1.0000
5.250 1.0104 0.01474 0.00581 -0.0846 0.2018 1.0000
5.500 1.0349 0.01510 0.00620 -0.0842 0.1928 1.0000
5.750 1.0591 0.01549 0.00663 -0.0837 0.1858 1.0000
6.000 1.0835 0.01586 0.00706 -0.0832 0.1788 1.0000
6.250 1.1072 0.01628 0.00751 -0.0826 0.1714 1.0000
6.500 1.1303 0.01676 0.00798 -0.0820 0.1577 1.0000
6.750 1.1537 0.01720 0.00844 -0.0814 0.1365 1.0000
7.000 1.1751 0.01786 0.00891 -0.0807 0.0961 1.0000
7.250 1.1929 0.01896 0.00973 -0.0795 0.0675 1.0000
7.500 1.2137 0.01969 0.01047 -0.0786 0.0586 1.0000
7.750 1.2348 0.02036 0.01120 -0.0777 0.0502 1.0000
8.000 1.2560 0.02102 0.01195 -0.0768 0.0355 1.0000
8.250 1.2716 0.02237 0.01314 -0.0752 0.0163 1.0000
8.500 1.2893 0.02342 0.01433 -0.0737 0.0137 1.0000
8.750 1.3063 0.02450 0.01563 -0.0721 0.0122 1.0000
9.000 1.3211 0.02574 0.01710 -0.0702 0.0111 1.0000
9.250 1.3362 0.02683 0.01838 -0.0686 0.0103 1.0000
9.500 1.3489 0.02808 0.01981 -0.0666 0.0095 1.0000
9.750 1.3586 0.02948 0.02139 -0.0643 0.0090 1.0000
10.000 1.3645 0.03096 0.02309 -0.0615 0.0086 1.0000
10.250 1.3685 0.03262 0.02492 -0.0587 0.0083 1.0000
10.500 1.3705 0.03447 0.02693 -0.0559 0.0081 1.0000
10.750 1.3707 0.03657 0.02919 -0.0533 0.0079 1.0000
11.000 1.3689 0.03896 0.03173 -0.0510 0.0077 1.0000
11.250 1.3652 0.04170 0.03462 -0.0489 0.0075 1.0000
11.500 1.3594 0.04487 0.03793 -0.0470 0.0073 1.0000
11.750 1.3578 0.04773 0.04096 -0.0457 0.0071 1.0000
12.000 1.3590 0.05032 0.04376 -0.0448 0.0069 1.0000
12.250 1.3584 0.05321 0.04686 -0.0442 0.0066 1.0000
12.500 1.3554 0.05652 0.05036 -0.0438 0.0064 1.0000
12.750 1.3506 0.06016 0.05420 -0.0437 0.0062 1.0000
13.000 1.3440 0.06420 0.05843 -0.0439 0.0061 1.0000
13.250 1.3360 0.06858 0.06300 -0.0444 0.0060 1.0000
13.500 1.3267 0.07332 0.06794 -0.0453 0.0060 1.0000
13.750 1.3163 0.07845 0.07327 -0.0468 0.0059 1.0000
14.000 1.3047 0.08401 0.07902 -0.0487 0.0059 1.0000
14.250 1.2924 0.09004 0.08524 -0.0512 0.0059 1.0000
14.500 1.2795 0.09653 0.09192 -0.0542 0.0059 1.0000
14.750 1.2661 0.10347 0.09904 -0.0577 0.0059 1.0000
15.000 1.2524 0.11079 0.10654 -0.0616 0.0059 1.0000
15.250 1.2385 0.11848 0.11440 -0.0658 0.0059 1.0000
15.500 1.2244 0.12651 0.12258 -0.0704 0.0060 1.0000
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Polar data table (+)
Polar graphs
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