GOE 380 AIRFOIL (goe380-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 380 AIRFOIL (goe380-il) Reynolds number: 100,000 Max Cl/Cd: 59.98 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe380-il-100000-n5.txt Download as CSV file: xf-goe380-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 380 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2764 0.10731 0.10282 -0.0277 1.0000 0.0264
-7.750 -0.2823 0.10610 0.10171 -0.0267 1.0000 0.0264
-7.500 -0.2880 0.10479 0.10050 -0.0257 1.0000 0.0265
-7.250 -0.2914 0.10331 0.09911 -0.0256 1.0000 0.0265
-7.000 -0.2938 0.10175 0.09761 -0.0255 1.0000 0.0265
-6.750 -0.2916 0.09611 0.09206 -0.0213 1.0000 0.0271
-6.500 -0.2929 0.09325 0.08926 -0.0190 0.9999 0.0276
-6.250 -0.2708 0.08887 0.08487 -0.0232 0.9940 0.0287
-6.000 -0.2457 0.08481 0.08079 -0.0289 0.9872 0.0300
-5.750 -0.2197 0.08090 0.07684 -0.0349 0.9793 0.0316
-5.500 -0.1908 0.07713 0.07303 -0.0417 0.9707 0.0336
-5.250 -0.1490 0.07416 0.06994 -0.0526 0.9611 0.0352
-5.000 -0.1021 0.07083 0.06643 -0.0633 0.9539 0.0356
-4.750 -0.0894 0.06569 0.06137 -0.0633 0.9454 0.0362
-4.500 -0.0650 0.06128 0.05695 -0.0657 0.9402 0.0377
-4.250 -0.0378 0.05792 0.05352 -0.0690 0.9306 0.0397
-4.000 -0.0017 0.05451 0.04996 -0.0742 0.9230 0.0422
-3.750 0.0519 0.05271 0.04779 -0.0818 0.9141 0.0452
-3.500 0.0819 0.04905 0.04397 -0.0845 0.9041 0.0459
-3.250 0.1010 0.04451 0.03952 -0.0854 0.8968 0.0485
-3.000 0.1304 0.04171 0.03658 -0.0873 0.8863 0.0508
-2.750 0.1703 0.03799 0.03246 -0.0897 0.8760 0.0345
-2.250 0.2389 0.03129 0.02510 -0.0925 0.8550 0.0256
-2.000 0.2705 0.02869 0.02218 -0.0931 0.8409 0.0249
-1.750 0.3021 0.02614 0.01923 -0.0932 0.8255 0.0247
-1.500 0.3338 0.02364 0.01623 -0.0929 0.8098 0.0259
-1.250 0.3640 0.02149 0.01362 -0.0926 0.7943 0.0275
-1.000 0.3934 0.01982 0.01153 -0.0922 0.7792 0.0287
-0.750 0.4227 0.01834 0.00966 -0.0917 0.7639 0.0311
-0.500 0.4511 0.01735 0.00839 -0.0912 0.7478 0.0380
-0.250 0.4791 0.01638 0.00716 -0.0905 0.7314 0.0458
0.000 0.5067 0.01620 0.00684 -0.0900 0.7144 0.0698
0.250 0.5334 0.01610 0.00654 -0.0896 0.6971 0.1032
0.500 0.5603 0.01565 0.00592 -0.0891 0.6802 0.1160
0.750 0.5873 0.01542 0.00547 -0.0887 0.6637 0.1269
1.000 0.6139 0.01527 0.00515 -0.0882 0.6476 0.1350
1.250 0.6401 0.01520 0.00493 -0.0878 0.6322 0.1477
1.750 0.6890 0.01437 0.00485 -0.0866 0.6042 0.5465
2.250 0.7651 0.01410 0.00480 -0.0906 0.5746 1.0000
2.500 0.7897 0.01435 0.00488 -0.0898 0.5619 1.0000
2.750 0.8141 0.01461 0.00499 -0.0891 0.5498 1.0000
3.000 0.8385 0.01489 0.00515 -0.0884 0.5379 1.0000
3.250 0.8626 0.01517 0.00533 -0.0876 0.5254 1.0000
3.500 0.8866 0.01545 0.00555 -0.0869 0.5131 1.0000
3.750 0.9104 0.01574 0.00579 -0.0862 0.5008 1.0000
4.000 0.9338 0.01603 0.00606 -0.0853 0.4872 1.0000
4.250 0.9568 0.01632 0.00631 -0.0844 0.4723 1.0000
4.500 0.9795 0.01660 0.00656 -0.0835 0.4572 1.0000
4.750 1.0023 0.01690 0.00689 -0.0826 0.4430 1.0000
5.000 1.0252 0.01721 0.00721 -0.0818 0.4305 1.0000
5.250 1.0481 0.01753 0.00755 -0.0809 0.4188 1.0000
5.500 1.0707 0.01787 0.00790 -0.0800 0.4076 1.0000
5.750 1.0933 0.01823 0.00836 -0.0792 0.3958 1.0000
6.000 1.1156 0.01860 0.00881 -0.0783 0.3843 1.0000
6.250 1.1377 0.01900 0.00927 -0.0773 0.3737 1.0000
6.500 1.1596 0.01944 0.00976 -0.0764 0.3638 1.0000
6.750 1.1812 0.01988 0.01038 -0.0754 0.3529 1.0000
7.000 1.2026 0.02036 0.01098 -0.0744 0.3421 1.0000
7.250 1.2236 0.02087 0.01161 -0.0733 0.3317 1.0000
7.500 1.2428 0.02138 0.01225 -0.0719 0.3171 1.0000
7.750 1.2538 0.02191 0.01270 -0.0694 0.2781 1.0000
8.000 1.2678 0.02255 0.01341 -0.0673 0.2401 1.0000
8.250 1.2732 0.02388 0.01429 -0.0643 0.1747 1.0000
8.500 1.2693 0.02629 0.01596 -0.0605 0.0795 1.0000
8.750 1.2604 0.02906 0.01826 -0.0559 0.0258 1.0000
9.000 1.2621 0.03074 0.02009 -0.0523 0.0210 1.0000
9.250 1.2661 0.03226 0.02184 -0.0493 0.0192 1.0000
9.500 1.2690 0.03386 0.02369 -0.0464 0.0174 1.0000
9.750 1.2692 0.03574 0.02579 -0.0436 0.0157 1.0000
10.000 1.2664 0.03791 0.02819 -0.0410 0.0146 1.0000
10.250 1.2607 0.04047 0.03098 -0.0388 0.0140 1.0000
10.500 1.2536 0.04334 0.03407 -0.0370 0.0137 1.0000
10.750 1.2435 0.04675 0.03770 -0.0357 0.0133 1.0000
11.000 1.2331 0.05050 0.04165 -0.0351 0.0131 1.0000
11.250 1.2231 0.05449 0.04582 -0.0350 0.0129 1.0000
11.500 1.2133 0.05867 0.05016 -0.0351 0.0127 1.0000
11.750 1.2047 0.06279 0.05441 -0.0352 0.0126 1.0000
12.000 1.2024 0.06621 0.05793 -0.0352 0.0123 1.0000
12.250 1.2027 0.06928 0.06112 -0.0350 0.0121 1.0000
12.500 1.2044 0.07226 0.06425 -0.0347 0.0114 1.0000
12.750 1.2070 0.07516 0.06727 -0.0344 0.0107 1.0000
13.000 1.2126 0.07765 0.06987 -0.0336 0.0104 1.0000
13.250 1.2202 0.08001 0.07247 -0.0325 0.0101 1.0000
13.500 1.2272 0.08275 0.07538 -0.0315 0.0100 1.0000
13.750 1.2301 0.08622 0.07905 -0.0313 0.0098 1.0000
14.000 1.2298 0.09018 0.08322 -0.0317 0.0098 1.0000
14.250 1.2262 0.09470 0.08797 -0.0327 0.0098 1.0000
14.500 1.2202 0.09962 0.09312 -0.0343 0.0098 1.0000
14.750 1.2123 0.10503 0.09876 -0.0363 0.0098 1.0000
15.000 1.2031 0.11076 0.10471 -0.0389 0.0098 1.0000
15.250 1.1931 0.11679 0.11095 -0.0419 0.0099 1.0000
15.500 1.1820 0.12329 0.11766 -0.0454 0.0099 1.0000
15.750 1.1711 0.13001 0.12457 -0.0493 0.0100 1.0000
16.000 1.1600 0.13707 0.13181 -0.0536 0.0101 1.0000
16.250 1.1484 0.14458 0.13949 -0.0583 0.0102 1.0000
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Polar data table (+)
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