GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL (goe300-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL (goe300-il) Reynolds number: 1,000,000 Max Cl/Cd: 130.41 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe300-il-1000000.txt Download as CSV file: xf-goe300-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 300 (FRIEDRICHSHAFEN G20) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.2790 0.01649 0.01262 -0.0997 0.8928 0.0207
-7.250 -0.2553 0.01403 0.00991 -0.0997 0.8842 0.0216
-7.000 -0.2296 0.01296 0.00864 -0.0994 0.8749 0.0226
-6.750 -0.2030 0.01216 0.00766 -0.0992 0.8643 0.0233
-6.500 -0.1765 0.01146 0.00684 -0.0989 0.8530 0.0248
-6.250 -0.1495 0.01108 0.00636 -0.0986 0.8406 0.0261
-6.000 -0.1222 0.01071 0.00585 -0.0983 0.8275 0.0274
-5.750 -0.0948 0.01037 0.00545 -0.0980 0.8135 0.0293
-5.500 -0.0671 0.01026 0.00526 -0.0977 0.7976 0.0309
-5.250 -0.0395 0.01008 0.00494 -0.0974 0.7809 0.0322
-5.000 -0.0118 0.00997 0.00479 -0.0971 0.7642 0.0342
-4.750 0.0162 0.01007 0.00484 -0.0969 0.7476 0.0358
-4.500 0.0442 0.01011 0.00477 -0.0966 0.7310 0.0373
-4.250 0.0719 0.00998 0.00457 -0.0964 0.7145 0.0390
-3.750 0.1281 0.01033 0.00481 -0.0960 0.6796 0.0417
-3.500 0.1561 0.01042 0.00480 -0.0958 0.6637 0.0431
-3.250 0.1838 0.01009 0.00435 -0.0956 0.6504 0.0447
-3.000 0.2120 0.01013 0.00436 -0.0955 0.6380 0.0459
-2.750 0.2402 0.01029 0.00450 -0.0954 0.6265 0.0471
-2.500 0.2683 0.01031 0.00445 -0.0952 0.6153 0.0485
-2.250 0.2965 0.01025 0.00433 -0.0951 0.6051 0.0499
-2.000 0.3247 0.01031 0.00432 -0.0949 0.5957 0.0508
-1.750 0.3521 0.00969 0.00358 -0.0948 0.5864 0.0527
-1.500 0.3803 0.00966 0.00353 -0.0947 0.5777 0.0539
-1.250 0.4082 0.00960 0.00342 -0.0946 0.5684 0.0551
-1.000 0.4364 0.00955 0.00333 -0.0945 0.5592 0.0565
-0.750 0.4642 0.00945 0.00316 -0.0944 0.5505 0.0577
-0.500 0.4924 0.00931 0.00299 -0.0943 0.5432 0.0586
0.000 0.5480 0.00895 0.00253 -0.0940 0.5278 0.0609
0.500 0.6036 0.00871 0.00224 -0.0938 0.5107 0.0637
1.000 0.6594 0.00866 0.00214 -0.0936 0.4952 0.0666
1.500 0.7152 0.00864 0.00208 -0.0934 0.4778 0.0693
1.750 0.7429 0.00867 0.00207 -0.0933 0.4676 0.0701
2.000 0.7702 0.00860 0.00194 -0.0931 0.4548 0.0733
2.250 0.7978 0.00864 0.00196 -0.0930 0.4400 0.0759
2.500 0.8251 0.00874 0.00200 -0.0929 0.4241 0.0787
2.750 0.8522 0.00886 0.00207 -0.0927 0.4073 0.0815
3.000 0.8791 0.00897 0.00211 -0.0926 0.3898 0.0859
3.250 0.9060 0.00911 0.00221 -0.0924 0.3746 0.0916
3.750 0.9601 0.00935 0.00241 -0.0921 0.3539 0.1062
4.000 0.9869 0.00950 0.00254 -0.0919 0.3454 0.1161
4.250 1.0142 0.00958 0.00265 -0.0918 0.3386 0.1291
4.500 1.0409 0.00972 0.00280 -0.0917 0.3315 0.1511
4.750 1.0658 0.00839 0.00311 -0.0915 0.3268 1.0000
5.000 1.0927 0.00854 0.00323 -0.0913 0.3216 1.0000
5.250 1.1190 0.00875 0.00339 -0.0911 0.3147 1.0000
5.500 1.1461 0.00888 0.00353 -0.0910 0.3097 1.0000
5.750 1.1726 0.00906 0.00368 -0.0908 0.3036 1.0000
6.000 1.1989 0.00926 0.00385 -0.0906 0.2976 1.0000
6.250 1.2257 0.00940 0.00400 -0.0904 0.2912 1.0000
6.500 1.2515 0.00964 0.00419 -0.0902 0.2828 1.0000
6.750 1.2780 0.00980 0.00435 -0.0900 0.2740 1.0000
7.000 1.3035 0.01005 0.00455 -0.0897 0.2612 1.0000
7.250 1.3279 0.01041 0.00481 -0.0893 0.2394 1.0000
7.500 1.3480 0.01117 0.00529 -0.0883 0.1930 1.0000
7.750 1.3695 0.01178 0.00576 -0.0875 0.1734 1.0000
8.000 1.3929 0.01218 0.00613 -0.0869 0.1647 1.0000
8.250 1.4164 0.01256 0.00649 -0.0864 0.1589 1.0000
8.500 1.4393 0.01297 0.00688 -0.0857 0.1527 1.0000
8.750 1.4639 0.01321 0.00716 -0.0854 0.1496 1.0000
9.000 1.4873 0.01354 0.00750 -0.0848 0.1453 1.0000
9.250 1.5095 0.01397 0.00792 -0.0841 0.1400 1.0000
9.500 1.5332 0.01424 0.00822 -0.0836 0.1364 1.0000
9.750 1.5564 0.01453 0.00855 -0.0831 0.1325 1.0000
10.000 1.5780 0.01495 0.00895 -0.0823 0.1271 1.0000
10.250 1.6002 0.01529 0.00931 -0.0816 0.1222 1.0000
10.500 1.6209 0.01572 0.00972 -0.0808 0.1143 1.0000
10.750 1.6412 0.01616 0.01015 -0.0798 0.1069 1.0000
11.000 1.6588 0.01676 0.01069 -0.0786 0.0960 1.0000
11.250 1.6721 0.01755 0.01139 -0.0766 0.0816 1.0000
11.500 1.6779 0.01862 0.01234 -0.0736 0.0652 1.0000
11.750 1.6775 0.02010 0.01370 -0.0699 0.0450 1.0000
12.000 1.6754 0.02181 0.01531 -0.0664 0.0303 1.0000
12.250 1.6805 0.02316 0.01667 -0.0641 0.0254 1.0000
12.500 1.6853 0.02461 0.01816 -0.0619 0.0224 1.0000
12.750 1.6940 0.02585 0.01946 -0.0603 0.0210 1.0000
13.000 1.6995 0.02739 0.02106 -0.0587 0.0195 1.0000
13.250 1.7025 0.02925 0.02299 -0.0571 0.0181 1.0000
13.500 1.7102 0.03077 0.02458 -0.0559 0.0174 1.0000
13.750 1.7156 0.03257 0.02645 -0.0549 0.0166 1.0000
14.000 1.7183 0.03471 0.02865 -0.0539 0.0158 1.0000
14.250 1.7171 0.03734 0.03137 -0.0529 0.0151 1.0000
14.500 1.7161 0.04006 0.03419 -0.0522 0.0145 1.0000
14.750 1.7184 0.04249 0.03671 -0.0518 0.0142 1.0000
15.000 1.7188 0.04521 0.03952 -0.0514 0.0138 1.0000
15.250 1.7177 0.04816 0.04256 -0.0512 0.0134 1.0000
15.500 1.7148 0.05140 0.04589 -0.0511 0.0130 1.0000
15.750 1.7099 0.05497 0.04955 -0.0512 0.0127 1.0000
16.000 1.7025 0.05897 0.05365 -0.0514 0.0124 1.0000
16.250 1.6917 0.06350 0.05829 -0.0519 0.0121 1.0000
16.500 1.6760 0.06882 0.06373 -0.0526 0.0117 1.0000
16.750 1.6652 0.07357 0.06859 -0.0534 0.0116 1.0000
17.000 1.6587 0.07776 0.07289 -0.0542 0.0114 1.0000
17.250 1.6503 0.08228 0.07751 -0.0551 0.0112 1.0000
17.500 1.6407 0.08708 0.08241 -0.0562 0.0111 1.0000
17.750 1.6303 0.09208 0.08753 -0.0574 0.0109 1.0000
18.000 1.6187 0.09731 0.09286 -0.0588 0.0107 1.0000
18.250 1.6067 0.10267 0.09833 -0.0603 0.0106 1.0000
18.500 1.5944 0.10820 0.10395 -0.0620 0.0104 1.0000
18.750 1.5823 0.11373 0.10958 -0.0639 0.0103 1.0000
19.000 1.5694 0.11942 0.11538 -0.0659 0.0102 1.0000
19.250 1.5570 0.12513 0.12119 -0.0680 0.0101 1.0000
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