GOE 210 (DAIMLER) AIRFOIL (goe210-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 210 (DAIMLER) AIRFOIL (goe210-il) Reynolds number: 200,000 Max Cl/Cd: 82.33 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe210-il-200000.txt Download as CSV file: xf-goe210-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3543 0.09010 0.08671 -0.0217 1.0000 0.0283
-7.250 -0.3534 0.08753 0.08421 -0.0223 1.0000 0.0288
-7.000 -0.3501 0.08475 0.08148 -0.0237 1.0000 0.0295
-6.750 -0.3462 0.08197 0.07875 -0.0254 1.0000 0.0302
-6.500 -0.3410 0.07924 0.07606 -0.0278 1.0000 0.0310
-6.250 -0.3320 0.07668 0.07352 -0.0323 1.0000 0.0319
-6.000 -0.3207 0.07417 0.07099 -0.0364 1.0000 0.0323
-5.750 -0.3139 0.07174 0.06854 -0.0379 1.0000 0.0325
-5.500 -0.3092 0.06947 0.06624 -0.0381 0.9997 0.0326
-5.250 -0.2821 0.06183 0.05856 -0.0444 0.9957 0.0334
-5.000 -0.2582 0.05768 0.05441 -0.0469 0.9915 0.0347
-4.750 -0.2229 0.05365 0.05031 -0.0524 0.9866 0.0370
-4.500 -0.1550 0.05011 0.04621 -0.0642 0.9817 0.0438
-4.250 -0.1293 0.04366 0.03977 -0.0683 0.9759 0.0456
-4.000 -0.0949 0.04051 0.03659 -0.0721 0.9720 0.0487
-3.750 -0.0435 0.03696 0.03241 -0.0781 0.9667 0.0572
-3.500 -0.0142 0.03365 0.02920 -0.0808 0.9611 0.0608
-3.250 0.0297 0.03072 0.02593 -0.0851 0.9577 0.0724
-3.000 0.0701 0.02851 0.02338 -0.0883 0.9533 0.0855
-2.750 0.1065 0.02673 0.02130 -0.0905 0.9468 0.0989
-2.500 0.1443 0.02438 0.01878 -0.0933 0.9430 0.1134
-2.250 0.1748 0.02237 0.01678 -0.0946 0.9355 0.1306
-2.000 0.2211 0.01868 0.01206 -0.0945 0.9307 0.0674
-1.750 0.2557 0.01689 0.01000 -0.0954 0.9248 0.0653
-1.500 0.2872 0.01565 0.00853 -0.0956 0.9168 0.0648
-1.250 0.3182 0.01459 0.00730 -0.0956 0.9085 0.0645
-1.000 0.3488 0.01378 0.00638 -0.0954 0.8996 0.0664
-0.750 0.3761 0.01323 0.00574 -0.0945 0.8865 0.0691
-0.500 0.4023 0.01247 0.00494 -0.0935 0.8723 0.0705
-0.250 0.4284 0.01188 0.00437 -0.0926 0.8585 0.0742
0.000 0.4549 0.01158 0.00404 -0.0919 0.8461 0.0799
0.250 0.4815 0.01131 0.00375 -0.0912 0.8337 0.0919
0.500 0.5057 0.00885 0.00352 -0.0902 0.8213 1.0000
0.750 0.5320 0.00894 0.00337 -0.0893 0.8075 1.0000
1.000 0.5584 0.00904 0.00332 -0.0887 0.7951 1.0000
1.250 0.5852 0.00916 0.00330 -0.0881 0.7843 1.0000
1.500 0.6117 0.00928 0.00334 -0.0876 0.7723 1.0000
1.750 0.6381 0.00939 0.00338 -0.0871 0.7600 1.0000
2.000 0.6645 0.00950 0.00342 -0.0865 0.7474 1.0000
2.250 0.6908 0.00960 0.00347 -0.0860 0.7338 1.0000
2.500 0.7168 0.00969 0.00351 -0.0853 0.7180 1.0000
2.750 0.7425 0.00976 0.00351 -0.0845 0.6993 1.0000
3.000 0.7679 0.00983 0.00353 -0.0837 0.6764 1.0000
3.250 0.7931 0.00992 0.00354 -0.0828 0.6496 1.0000
3.500 0.8179 0.01004 0.00358 -0.0819 0.6161 1.0000
3.750 0.8422 0.01023 0.00364 -0.0810 0.5736 1.0000
4.000 0.8651 0.01058 0.00373 -0.0799 0.5152 1.0000
4.250 0.8859 0.01122 0.00396 -0.0785 0.4397 1.0000
4.500 0.9063 0.01200 0.00438 -0.0773 0.3721 1.0000
4.750 0.9279 0.01273 0.00483 -0.0764 0.3249 1.0000
5.000 0.9507 0.01336 0.00529 -0.0756 0.2936 1.0000
5.250 0.9740 0.01392 0.00573 -0.0750 0.2718 1.0000
5.500 0.9976 0.01444 0.00620 -0.0744 0.2556 1.0000
5.750 1.0218 0.01490 0.00665 -0.0738 0.2432 1.0000
6.000 1.0460 0.01534 0.00711 -0.0733 0.2324 1.0000
6.250 1.0700 0.01578 0.00757 -0.0727 0.2208 1.0000
6.500 1.0937 0.01623 0.00805 -0.0722 0.2084 1.0000
6.750 1.1172 0.01668 0.00851 -0.0716 0.1946 1.0000
7.000 1.1405 0.01712 0.00899 -0.0710 0.1799 1.0000
7.250 1.1636 0.01757 0.00945 -0.0704 0.1621 1.0000
7.500 1.1865 0.01805 0.00995 -0.0698 0.1448 1.0000
7.750 1.2098 0.01849 0.01045 -0.0692 0.1236 1.0000
8.000 1.2318 0.01908 0.01096 -0.0684 0.1006 1.0000
8.250 1.2521 0.01987 0.01166 -0.0675 0.0843 1.0000
8.500 1.2707 0.02087 0.01262 -0.0663 0.0704 1.0000
8.750 1.2867 0.02217 0.01391 -0.0648 0.0552 1.0000
9.000 1.3054 0.02319 0.01507 -0.0635 0.0392 1.0000
9.250 1.3221 0.02435 0.01624 -0.0619 0.0308 1.0000
9.500 1.3374 0.02555 0.01748 -0.0602 0.0270 1.0000
9.750 1.3481 0.02710 0.01915 -0.0579 0.0251 1.0000
10.000 1.3591 0.02853 0.02073 -0.0557 0.0237 1.0000
10.250 1.3687 0.02997 0.02229 -0.0534 0.0221 1.0000
10.500 1.3738 0.03157 0.02400 -0.0506 0.0209 1.0000
10.750 1.3762 0.03354 0.02611 -0.0476 0.0203 1.0000
11.000 1.3776 0.03582 0.02852 -0.0448 0.0198 1.0000
11.250 1.3792 0.03848 0.03135 -0.0421 0.0194 1.0000
11.500 1.3816 0.04146 0.03451 -0.0398 0.0191 1.0000
11.750 1.3850 0.04410 0.03738 -0.0377 0.0190 1.0000
12.000 1.3861 0.04702 0.04055 -0.0358 0.0189 1.0000
12.250 1.3844 0.05027 0.04406 -0.0340 0.0189 1.0000
12.500 1.3795 0.05385 0.04791 -0.0325 0.0189 1.0000
12.750 1.3712 0.05782 0.05214 -0.0313 0.0189 1.0000
13.000 1.3600 0.06218 0.05678 -0.0307 0.0190 1.0000
13.250 1.3463 0.06692 0.06177 -0.0307 0.0190 1.0000
13.500 1.3308 0.07207 0.06716 -0.0314 0.0190 1.0000
13.750 1.3131 0.07781 0.07313 -0.0328 0.0191 1.0000
14.000 1.2949 0.08394 0.07949 -0.0349 0.0192 1.0000
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Polar data table (+)
Polar graphs
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