GOE 393 AIRFOIL (goe393-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 393 AIRFOIL (goe393-il) Reynolds number: 1,000,000 Max Cl/Cd: 113.4 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe393-il-1000000-n5.txt Download as CSV file: xf-goe393-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 393 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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.5879 0.15409 0.15248 0.0406 1.0000 0.0045
-8.000 -0.5637 0.01862 0.01540 -0.0548 1.0000 0.0172
-7.750 -0.5322 0.01730 0.01391 -0.0561 0.9723 0.0180
-7.500 -0.5049 0.01655 0.01297 -0.0561 0.9342 0.0184
-7.250 -0.4860 0.01634 0.01228 -0.0540 0.8072 0.0185
-7.000 -0.4612 0.01540 0.01099 -0.0538 0.7529 0.0192
-6.750 -0.4341 0.01542 0.01091 -0.0535 0.7225 0.0197
-6.500 -0.4067 0.01538 0.01078 -0.0533 0.7015 0.0201
-6.250 -0.3795 0.01517 0.01047 -0.0532 0.6838 0.0206
-6.000 -0.3522 0.01492 0.01012 -0.0530 0.6683 0.0211
-5.750 -0.3249 0.01453 0.00960 -0.0529 0.6539 0.0217
-5.500 -0.2977 0.01410 0.00901 -0.0528 0.6379 0.0223
-5.250 -0.2704 0.01359 0.00831 -0.0527 0.6207 0.0228
-5.000 -0.2431 0.01309 0.00764 -0.0525 0.6053 0.0232
-4.750 -0.2156 0.01269 0.00711 -0.0524 0.5945 0.0236
-4.500 -0.1880 0.01220 0.00647 -0.0523 0.5856 0.0239
-4.250 -0.1604 0.01174 0.00587 -0.0521 0.5765 0.0241
-4.000 -0.1327 0.01132 0.00534 -0.0520 0.5684 0.0242
-3.750 -0.1049 0.01095 0.00486 -0.0518 0.5607 0.0244
-3.500 -0.0771 0.01062 0.00443 -0.0516 0.5537 0.0245
-3.250 -0.0492 0.01034 0.00405 -0.0515 0.5457 0.0246
-3.000 -0.0212 0.01016 0.00381 -0.0513 0.5384 0.0248
-2.750 0.0064 0.00949 0.00299 -0.0512 0.5313 0.0256
-2.500 0.0342 0.00914 0.00255 -0.0510 0.5250 0.0263
-2.250 0.0622 0.00889 0.00225 -0.0508 0.5187 0.0269
-2.000 0.0902 0.00873 0.00203 -0.0507 0.5118 0.0275
-1.750 0.1183 0.00857 0.00184 -0.0505 0.5052 0.0280
-1.500 0.1463 0.00845 0.00167 -0.0504 0.4976 0.0285
-1.250 0.1744 0.00834 0.00153 -0.0502 0.4910 0.0289
-1.000 0.2025 0.00825 0.00140 -0.0501 0.4840 0.0294
-0.750 0.2306 0.00817 0.00129 -0.0500 0.4776 0.0298
-0.500 0.2588 0.00811 0.00120 -0.0498 0.4704 0.0302
-0.250 0.2869 0.00806 0.00111 -0.0497 0.4635 0.0306
0.000 0.3150 0.00801 0.00104 -0.0496 0.4555 0.0311
0.250 0.3431 0.00799 0.00099 -0.0495 0.4475 0.0318
0.500 0.3712 0.00798 0.00095 -0.0493 0.4380 0.0328
1.000 0.4273 0.00794 0.00090 -0.0491 0.4189 0.0434
1.250 0.4551 0.00793 0.00095 -0.0491 0.4046 0.0727
1.750 0.5111 0.00803 0.00101 -0.0489 0.3818 0.0818
2.000 0.5390 0.00810 0.00107 -0.0488 0.3702 0.0873
2.250 0.5669 0.00818 0.00112 -0.0487 0.3585 0.0900
2.500 0.5947 0.00827 0.00117 -0.0486 0.3465 0.0916
2.750 0.6225 0.00835 0.00123 -0.0485 0.3353 0.0946
3.000 0.6503 0.00843 0.00131 -0.0484 0.3247 0.0983
3.250 0.6781 0.00852 0.00139 -0.0483 0.3170 0.1038
3.500 0.7059 0.00858 0.00148 -0.0483 0.3088 0.1090
3.750 0.7336 0.00867 0.00157 -0.0482 0.3017 0.1144
4.000 0.7614 0.00873 0.00166 -0.0481 0.2954 0.1197
4.250 0.7891 0.00882 0.00178 -0.0480 0.2879 0.1322
4.500 0.8167 0.00881 0.00193 -0.0480 0.2791 0.2155
5.000 0.8698 0.00767 0.00233 -0.0479 0.2497 1.0000
5.250 0.8948 0.00837 0.00268 -0.0477 0.1797 1.0000
5.500 0.9206 0.00891 0.00304 -0.0475 0.1444 1.0000
6.000 0.9727 0.00977 0.00366 -0.0472 0.0969 1.0000
6.250 0.9992 0.01007 0.00392 -0.0470 0.0875 1.0000
6.500 1.0256 0.01038 0.00419 -0.0468 0.0794 1.0000
6.750 1.0523 0.01062 0.00444 -0.0466 0.0741 1.0000
7.000 1.0784 0.01095 0.00474 -0.0465 0.0661 1.0000
7.250 1.1042 0.01133 0.00506 -0.0463 0.0533 1.0000
7.500 1.1288 0.01194 0.00554 -0.0460 0.0335 1.0000
7.750 1.1539 0.01241 0.00599 -0.0457 0.0252 1.0000
8.000 1.1788 0.01291 0.00646 -0.0454 0.0181 1.0000
8.250 1.2036 0.01339 0.00692 -0.0451 0.0142 1.0000
8.500 1.2287 0.01380 0.00736 -0.0448 0.0123 1.0000
8.750 1.2533 0.01426 0.00783 -0.0445 0.0109 1.0000
9.000 1.2775 0.01478 0.00840 -0.0441 0.0095 1.0000
9.250 1.3020 0.01521 0.00888 -0.0437 0.0090 1.0000
9.500 1.3261 0.01569 0.00939 -0.0434 0.0083 1.0000
9.750 1.3496 0.01623 0.00996 -0.0429 0.0076 1.0000
10.000 1.3722 0.01687 0.01064 -0.0424 0.0069 1.0000
10.250 1.3951 0.01744 0.01128 -0.0420 0.0065 1.0000
10.500 1.4177 0.01801 0.01191 -0.0415 0.0062 1.0000
10.750 1.4397 0.01863 0.01258 -0.0409 0.0059 1.0000
11.000 1.4611 0.01928 0.01329 -0.0403 0.0056 1.0000
11.250 1.4818 0.01999 0.01405 -0.0397 0.0053 1.0000
11.500 1.5013 0.02079 0.01491 -0.0390 0.0051 1.0000
11.750 1.5189 0.02178 0.01599 -0.0380 0.0048 1.0000
12.000 1.5361 0.02272 0.01701 -0.0371 0.0046 1.0000
12.250 1.5533 0.02359 0.01797 -0.0362 0.0045 1.0000
12.500 1.5690 0.02453 0.01899 -0.0351 0.0044 1.0000
12.750 1.5832 0.02555 0.02009 -0.0340 0.0042 1.0000
13.000 1.5944 0.02664 0.02127 -0.0326 0.0041 1.0000
13.250 1.6012 0.02789 0.02261 -0.0308 0.0039 1.0000
13.500 1.6063 0.02943 0.02424 -0.0295 0.0038 1.0000
13.750 1.6102 0.03137 0.02628 -0.0288 0.0037 1.0000
14.000 1.6133 0.03380 0.02883 -0.0291 0.0036 1.0000
14.250 1.6155 0.03665 0.03179 -0.0299 0.0036 1.0000
14.500 1.6161 0.03986 0.03512 -0.0310 0.0035 1.0000
14.750 1.6144 0.04341 0.03877 -0.0321 0.0034 1.0000
15.000 1.6097 0.04734 0.04281 -0.0334 0.0034 1.0000
15.250 1.6024 0.05164 0.04723 -0.0347 0.0033 1.0000
15.500 1.5925 0.05627 0.05197 -0.0361 0.0033 1.0000
15.750 1.5802 0.06130 0.05713 -0.0377 0.0032 1.0000
16.000 1.5662 0.06661 0.06255 -0.0393 0.0032 1.0000
16.250 1.5505 0.07228 0.06835 -0.0412 0.0032 1.0000
16.500 1.5336 0.07829 0.07448 -0.0433 0.0032 1.0000
16.750 1.5170 0.08461 0.08093 -0.0458 0.0031 1.0000
17.000 1.4996 0.09121 0.08765 -0.0484 0.0031 1.0000
17.250 1.4812 0.09815 0.09472 -0.0512 0.0031 1.0000
17.500 1.4643 0.10498 0.10166 -0.0541 0.0031 1.0000
17.750 1.4453 0.11228 0.10908 -0.0572 0.0031 1.0000
18.000 1.4277 0.11953 0.11644 -0.0604 0.0031 1.0000
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