GOE 14 AIRFOIL (goe14-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 14 AIRFOIL (goe14-il) Reynolds number: 1,000,000 Max Cl/Cd: 111.29 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe14-il-1000000-n5.txt Download as CSV file: xf-goe14-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 14 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.1722 0.10000 0.09738 -0.0287 0.7283 0.0179
-8.500 -0.1635 0.09715 0.09450 -0.0303 0.7195 0.0179
-8.250 -0.1547 0.09435 0.09168 -0.0319 0.7114 0.0179
-8.000 -0.1454 0.09160 0.08891 -0.0335 0.7029 0.0179
-7.750 -0.1354 0.08916 0.08643 -0.0349 0.6937 0.0178
-7.500 -0.1278 0.08550 0.08276 -0.0380 0.6850 0.0180
-7.250 -0.1182 0.08274 0.07995 -0.0403 0.6746 0.0180
-7.000 -0.1038 0.07923 0.07641 -0.0448 0.6634 0.0181
-6.750 -0.0887 0.07631 0.07344 -0.0478 0.6514 0.0182
-6.500 -0.0720 0.07414 0.07122 -0.0499 0.6364 0.0183
-6.250 -0.0539 0.07188 0.06889 -0.0526 0.6182 0.0185
-6.000 -0.0345 0.06949 0.06641 -0.0557 0.5968 0.0187
-5.750 -0.0140 0.06696 0.06378 -0.0591 0.5757 0.0189
-5.500 0.0081 0.06477 0.06150 -0.0622 0.5568 0.0203
-5.250 0.0312 0.06184 0.05848 -0.0661 0.5407 0.0203
-5.000 0.0596 0.05806 0.05459 -0.0718 0.5272 0.0207
-4.750 0.0806 0.05606 0.05252 -0.0737 0.5137 0.0201
-4.500 0.1071 0.05303 0.04941 -0.0775 0.5037 0.0196
-4.250 0.1345 0.05024 0.04651 -0.0809 0.4933 0.0196
-4.000 0.1626 0.04755 0.04373 -0.0841 0.4839 0.0197
-3.750 0.1911 0.04499 0.04106 -0.0870 0.4743 0.0198
-3.500 0.2202 0.04247 0.03845 -0.0897 0.4656 0.0198
-3.250 0.2495 0.04006 0.03591 -0.0921 0.4556 0.0198
-3.000 0.2797 0.03758 0.03331 -0.0943 0.4466 0.0202
-2.750 0.3097 0.03520 0.03079 -0.0963 0.4376 0.0203
-2.500 0.3419 0.03223 0.02765 -0.0984 0.4314 0.0206
-2.250 0.3743 0.02909 0.02431 -0.1001 0.4252 0.0209
-2.000 0.4036 0.02707 0.02213 -0.1011 0.4191 0.0210
-1.750 0.4324 0.02552 0.02047 -0.1018 0.4133 0.0211
-1.250 0.4963 0.01293 0.00637 -0.1038 0.4034 0.0237
-1.000 0.5237 0.01162 0.00484 -0.1037 0.3976 0.0239
-0.750 0.5515 0.01111 0.00423 -0.1036 0.3914 0.0242
-0.500 0.5793 0.01089 0.00395 -0.1035 0.3851 0.0246
-0.250 0.6073 0.01073 0.00376 -0.1034 0.3801 0.0250
0.000 0.6353 0.01058 0.00357 -0.1033 0.3745 0.0255
0.250 0.6631 0.01046 0.00341 -0.1032 0.3684 0.0259
0.500 0.6910 0.01035 0.00325 -0.1031 0.3634 0.0263
0.750 0.7189 0.01026 0.00313 -0.1029 0.3577 0.0267
1.000 0.7466 0.01023 0.00305 -0.1028 0.3510 0.0271
1.250 0.7744 0.01019 0.00298 -0.1027 0.3453 0.0275
1.500 0.8022 0.01016 0.00293 -0.1025 0.3391 0.0282
1.750 0.8298 0.01018 0.00293 -0.1024 0.3330 0.0289
2.000 0.8576 0.01019 0.00292 -0.1023 0.3276 0.0297
2.250 0.8851 0.01023 0.00293 -0.1021 0.3201 0.0307
2.500 0.9125 0.01029 0.00296 -0.1020 0.3131 0.0322
2.750 0.9402 0.01032 0.00298 -0.1019 0.3072 0.0341
3.000 0.9675 0.01037 0.00302 -0.1018 0.3013 0.0372
3.250 0.9949 0.01045 0.00311 -0.1016 0.2963 0.0453
3.500 1.0224 0.01056 0.00324 -0.1015 0.2915 0.0527
3.750 1.0495 0.01071 0.00335 -0.1013 0.2854 0.0570
4.000 1.0766 0.01090 0.00354 -0.1012 0.2795 0.0591
4.250 1.1037 0.01103 0.00365 -0.1010 0.2737 0.0613
4.500 1.1303 0.01120 0.00379 -0.1008 0.2674 0.0631
4.750 1.1572 0.01137 0.00396 -0.1006 0.2622 0.0647
5.000 1.1840 0.01152 0.00410 -0.1005 0.2571 0.0667
5.250 1.2104 0.01169 0.00424 -0.1002 0.2519 0.0683
5.500 1.2368 0.01181 0.00436 -0.1001 0.2477 0.0692
5.750 1.2636 0.01191 0.00448 -0.0999 0.2447 0.0699
6.000 1.2900 0.01205 0.00461 -0.0997 0.2405 0.0708
6.250 1.3158 0.01223 0.00478 -0.0995 0.2356 0.0718
6.500 1.3417 0.01241 0.00495 -0.0992 0.2317 0.0729
6.750 1.3680 0.01253 0.00510 -0.0991 0.2293 0.0737
7.000 1.3939 0.01269 0.00527 -0.0988 0.2258 0.0744
7.250 1.4193 0.01289 0.00546 -0.0985 0.2214 0.0752
7.500 1.4443 0.01311 0.00567 -0.0982 0.2174 0.0763
7.750 1.4698 0.01329 0.00588 -0.0979 0.2148 0.0776
8.000 1.4952 0.01346 0.00608 -0.0977 0.2125 0.0791
8.250 1.5202 0.01366 0.00630 -0.0973 0.2096 0.0803
8.500 1.5447 0.01388 0.00654 -0.0969 0.2064 0.0815
8.750 1.5686 0.01415 0.00681 -0.0965 0.2028 0.0830
9.000 1.5925 0.01439 0.00708 -0.0960 0.1992 0.0851
9.250 1.6164 0.01463 0.00734 -0.0956 0.1949 0.0876
9.500 1.6388 0.01497 0.00766 -0.0949 0.1890 0.0904
9.750 1.6611 0.01530 0.00799 -0.0943 0.1834 0.0947
10.000 1.6823 0.01568 0.00836 -0.0935 0.1754 0.1018
10.500 1.7170 0.01592 0.00963 -0.0911 0.1481 1.0000
11.000 1.7437 0.01735 0.01094 -0.0873 0.1266 1.0000
11.500 1.7718 0.01866 0.01224 -0.0839 0.1169 1.0000
11.750 1.7856 0.01936 0.01294 -0.0823 0.1134 1.0000
12.000 1.7980 0.02018 0.01377 -0.0807 0.1097 1.0000
12.250 1.8117 0.02094 0.01456 -0.0793 0.1068 1.0000
12.500 1.8252 0.02174 0.01540 -0.0780 0.1042 1.0000
12.750 1.8360 0.02276 0.01643 -0.0766 0.1006 1.0000
13.000 1.8451 0.02395 0.01764 -0.0751 0.0968 1.0000
13.250 1.8574 0.02495 0.01868 -0.0740 0.0946 1.0000
13.500 1.8681 0.02610 0.01986 -0.0729 0.0915 1.0000
13.750 1.8744 0.02764 0.02141 -0.0716 0.0869 1.0000
14.000 1.8813 0.02920 0.02300 -0.0705 0.0827 1.0000
14.250 1.8817 0.03136 0.02514 -0.0691 0.0751 1.0000
14.500 1.8768 0.03411 0.02787 -0.0677 0.0659 1.0000
14.750 1.8684 0.03731 0.03107 -0.0664 0.0579 1.0000
15.000 1.8606 0.04060 0.03439 -0.0654 0.0523 1.0000
15.250 1.8529 0.04399 0.03783 -0.0647 0.0477 1.0000
15.500 1.8417 0.04796 0.04186 -0.0642 0.0434 1.0000
15.750 1.8270 0.05256 0.04652 -0.0641 0.0381 1.0000
16.000 1.8010 0.05879 0.05280 -0.0643 0.0293 1.0000
16.250 1.7746 0.06539 0.05947 -0.0651 0.0222 1.0000
16.500 1.7506 0.07182 0.06599 -0.0659 0.0184 1.0000
16.750 1.7335 0.07743 0.07170 -0.0668 0.0170 1.0000
17.000 1.7175 0.08292 0.07729 -0.0678 0.0160 1.0000
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Polar data table (+)
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