GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il) Reynolds number: 100,000 Max Cl/Cd: 53.71 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe318-il-100000-n5.txt Download as CSV file: xf-goe318-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 318 (HANSA-BRANDENBURG VI.5) 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3866 0.09383 0.08968 -0.0050 0.8997 0.0502
-7.500 -0.3822 0.09090 0.08668 -0.0069 0.8713 0.0525
-7.250 -0.3743 0.08748 0.08317 -0.0163 0.8507 0.0564
-7.000 -0.3572 0.08331 0.07877 -0.0283 0.8356 0.0572
-6.750 -0.3499 0.07838 0.07386 -0.0271 0.8250 0.0581
-6.500 -0.3400 0.07513 0.07058 -0.0249 0.8147 0.0594
-6.250 -0.3259 0.07190 0.06728 -0.0258 0.8046 0.0612
-6.000 -0.3092 0.06844 0.06371 -0.0285 0.7959 0.0638
-5.750 -0.2790 0.06339 0.05827 -0.0392 0.7871 0.0708
-5.500 -0.2674 0.06049 0.05544 -0.0371 0.7792 0.0731
-5.250 -0.2475 0.05749 0.05233 -0.0385 0.7711 0.0762
-5.000 -0.2132 0.05368 0.04793 -0.0454 0.7641 0.0842
-4.750 -0.1820 0.04619 0.03985 -0.0480 0.7577 0.0572
-4.500 -0.1624 0.04301 0.03665 -0.0482 0.7513 0.0558
-4.250 -0.1375 0.03983 0.03325 -0.0493 0.7438 0.0540
-4.000 -0.1110 0.03672 0.02978 -0.0501 0.7378 0.0527
-3.750 -0.0827 0.03396 0.02663 -0.0510 0.7309 0.0531
-3.500 -0.0545 0.03155 0.02378 -0.0514 0.7245 0.0543
-3.250 -0.0264 0.02934 0.02117 -0.0517 0.7185 0.0537
-3.000 0.0022 0.02741 0.01885 -0.0519 0.7118 0.0533
-2.750 0.0303 0.02577 0.01680 -0.0518 0.7064 0.0533
-2.500 0.0594 0.02436 0.01507 -0.0520 0.6994 0.0535
-2.250 0.0879 0.02332 0.01367 -0.0518 0.6934 0.0552
-2.000 0.1165 0.02247 0.01252 -0.0517 0.6873 0.0566
-1.750 0.1451 0.02158 0.01142 -0.0516 0.6807 0.0569
-1.500 0.1728 0.02081 0.01043 -0.0512 0.6754 0.0572
-1.250 0.2013 0.01998 0.00955 -0.0513 0.6681 0.0579
-1.000 0.2285 0.01926 0.00877 -0.0510 0.6618 0.0589
-0.750 0.2562 0.01871 0.00821 -0.0508 0.6540 0.0602
-0.500 0.2831 0.01823 0.00768 -0.0504 0.6463 0.0619
-0.250 0.3105 0.01787 0.00730 -0.0502 0.6366 0.0654
0.000 0.3374 0.01757 0.00686 -0.0496 0.6274 0.0697
0.250 0.3647 0.01720 0.00647 -0.0493 0.6162 0.0737
0.500 0.3924 0.01697 0.00618 -0.0491 0.6056 0.0790
0.750 0.4201 0.01675 0.00590 -0.0487 0.5973 0.0897
1.000 0.4486 0.01643 0.00580 -0.0489 0.5882 0.1548
1.500 0.5051 0.01442 0.00562 -0.0486 0.5719 1.0000
1.750 0.5329 0.01453 0.00560 -0.0484 0.5634 1.0000
2.000 0.5604 0.01464 0.00557 -0.0483 0.5544 1.0000
2.250 0.5882 0.01476 0.00563 -0.0482 0.5441 1.0000
2.500 0.6157 0.01488 0.00565 -0.0481 0.5342 1.0000
2.750 0.6432 0.01499 0.00567 -0.0479 0.5236 1.0000
3.000 0.6707 0.01512 0.00578 -0.0478 0.5115 1.0000
3.250 0.6981 0.01527 0.00587 -0.0477 0.4994 1.0000
3.500 0.7254 0.01542 0.00597 -0.0476 0.4872 1.0000
3.750 0.7525 0.01559 0.00609 -0.0474 0.4748 1.0000
4.000 0.7795 0.01578 0.00623 -0.0473 0.4618 1.0000
4.250 0.8063 0.01600 0.00639 -0.0471 0.4483 1.0000
4.500 0.8331 0.01626 0.00662 -0.0470 0.4343 1.0000
4.750 0.8596 0.01655 0.00687 -0.0469 0.4202 1.0000
5.000 0.8860 0.01687 0.00717 -0.0467 0.4064 1.0000
5.250 0.9122 0.01722 0.00752 -0.0466 0.3931 1.0000
5.500 0.9382 0.01761 0.00789 -0.0464 0.3806 1.0000
5.750 0.9641 0.01802 0.00828 -0.0463 0.3695 1.0000
6.000 0.9897 0.01846 0.00871 -0.0461 0.3597 1.0000
6.250 1.0155 0.01891 0.00922 -0.0460 0.3506 1.0000
6.500 1.0409 0.01938 0.00968 -0.0457 0.3438 1.0000
6.750 1.0666 0.01987 0.01027 -0.0456 0.3368 1.0000
7.000 1.0919 0.02038 0.01083 -0.0454 0.3314 1.0000
7.250 1.1173 0.02092 0.01146 -0.0452 0.3264 1.0000
7.500 1.1427 0.02147 0.01213 -0.0451 0.3216 1.0000
7.750 1.1679 0.02203 0.01280 -0.0449 0.3178 1.0000
8.000 1.1929 0.02263 0.01350 -0.0446 0.3137 1.0000
8.250 1.2172 0.02320 0.01426 -0.0444 0.3070 1.0000
8.500 1.2406 0.02373 0.01487 -0.0441 0.2986 1.0000
8.750 1.2623 0.02423 0.01545 -0.0436 0.2857 1.0000
9.000 1.2821 0.02478 0.01613 -0.0430 0.2688 1.0000
9.250 1.3004 0.02543 0.01691 -0.0425 0.2489 1.0000
9.500 1.3173 0.02623 0.01779 -0.0418 0.2283 1.0000
9.750 1.3334 0.02716 0.01884 -0.0411 0.2069 1.0000
10.000 1.3463 0.02837 0.02013 -0.0403 0.1446 1.0000
10.250 1.3357 0.03174 0.02284 -0.0385 0.0867 1.0000
10.500 1.3265 0.03479 0.02575 -0.0367 0.0627 1.0000
10.750 1.3188 0.03806 0.02903 -0.0360 0.0526 1.0000
11.000 1.3116 0.04158 0.03265 -0.0359 0.0462 1.0000
11.250 1.3036 0.04538 0.03657 -0.0362 0.0421 1.0000
11.500 1.2964 0.04926 0.04061 -0.0367 0.0388 1.0000
11.750 1.2862 0.05363 0.04511 -0.0375 0.0366 1.0000
12.000 1.2730 0.05854 0.05014 -0.0386 0.0353 1.0000
12.250 1.2623 0.06328 0.05503 -0.0397 0.0339 1.0000
12.500 1.2511 0.06820 0.06013 -0.0410 0.0328 1.0000
12.750 1.2394 0.07333 0.06541 -0.0424 0.0319 1.0000
13.000 1.2280 0.07849 0.07071 -0.0439 0.0311 1.0000
13.250 1.2183 0.08357 0.07591 -0.0454 0.0303 1.0000
13.500 1.2101 0.08847 0.08091 -0.0468 0.0295 1.0000
13.750 1.2031 0.09316 0.08568 -0.0481 0.0286 1.0000
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Polar data table (+)
Polar graphs
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