GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il) Reynolds number: 100,000 Max Cl/Cd: 55.76 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe315-il-100000-n5.txt Download as CSV file: xf-goe315-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 315 (HANSA-BRANDENBURG III.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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3449 0.09287 0.08797 -0.0215 1.0000 0.0471
-7.750 -0.3492 0.09086 0.08605 -0.0236 1.0000 0.0483
-7.500 -0.3497 0.08856 0.08381 -0.0287 1.0000 0.0489
-7.250 -0.3446 0.08581 0.08105 -0.0336 1.0000 0.0492
-7.000 -0.3371 0.08290 0.07810 -0.0371 1.0000 0.0494
-6.750 -0.3330 0.07781 0.07318 -0.0333 1.0000 0.0504
-6.500 -0.3267 0.07482 0.07027 -0.0306 1.0000 0.0518
-6.250 -0.3199 0.07211 0.06760 -0.0304 1.0000 0.0538
-6.000 -0.3129 0.06938 0.06490 -0.0313 1.0000 0.0559
-5.750 -0.2995 0.06638 0.06187 -0.0343 0.9970 0.0587
-5.500 -0.2510 0.06223 0.05721 -0.0471 0.9760 0.0616
-5.250 -0.2306 0.05705 0.05216 -0.0484 0.9624 0.0632
-5.000 -0.2037 0.05368 0.04878 -0.0509 0.9465 0.0668
-4.750 -0.1570 0.05167 0.04609 -0.0584 0.9260 0.0752
-4.500 -0.1330 0.04665 0.04120 -0.0604 0.9105 0.0771
-4.250 -0.1032 0.04356 0.03801 -0.0627 0.8935 0.0803
-4.000 -0.0628 0.04253 0.03626 -0.0661 0.8751 0.0898
-3.750 -0.0399 0.03835 0.03221 -0.0672 0.8588 0.0928
-3.500 -0.0098 0.03691 0.03034 -0.0684 0.8421 0.1053
-3.000 0.0520 0.03055 0.02311 -0.0683 0.8127 0.0591
-2.750 0.0780 0.02855 0.02085 -0.0681 0.7986 0.0565
-2.500 0.1053 0.02698 0.01895 -0.0679 0.7853 0.0564
-2.250 0.1327 0.02562 0.01725 -0.0675 0.7727 0.0568
-2.000 0.1599 0.02424 0.01555 -0.0670 0.7601 0.0554
-1.750 0.1871 0.02300 0.01400 -0.0665 0.7476 0.0540
-1.500 0.2144 0.02192 0.01262 -0.0659 0.7360 0.0531
-1.250 0.2418 0.02099 0.01141 -0.0653 0.7252 0.0526
-1.000 0.2687 0.02018 0.01040 -0.0648 0.7133 0.0526
-0.750 0.2953 0.01957 0.00967 -0.0643 0.7021 0.0540
-0.500 0.3220 0.01904 0.00901 -0.0638 0.6916 0.0560
-0.250 0.3486 0.01848 0.00835 -0.0632 0.6808 0.0569
0.000 0.3750 0.01796 0.00776 -0.0626 0.6697 0.0572
0.250 0.4008 0.01749 0.00723 -0.0619 0.6582 0.0578
0.500 0.4258 0.01706 0.00675 -0.0610 0.6446 0.0586
0.750 0.4504 0.01671 0.00633 -0.0600 0.6300 0.0597
1.000 0.4755 0.01645 0.00597 -0.0591 0.6161 0.0611
1.250 0.5012 0.01619 0.00568 -0.0586 0.6033 0.0654
1.500 0.5275 0.01609 0.00552 -0.0581 0.5921 0.0704
1.750 0.5541 0.01603 0.00534 -0.0576 0.5820 0.0746
2.000 0.5806 0.01596 0.00522 -0.0571 0.5719 0.0831
2.250 0.6072 0.01582 0.00520 -0.0567 0.5613 0.1297
2.750 0.6773 0.01427 0.00525 -0.0595 0.5400 1.0000
3.000 0.7023 0.01447 0.00539 -0.0588 0.5286 1.0000
3.250 0.7272 0.01469 0.00553 -0.0581 0.5176 1.0000
3.500 0.7521 0.01493 0.00566 -0.0574 0.5068 1.0000
3.750 0.7768 0.01515 0.00589 -0.0568 0.4947 1.0000
4.000 0.8016 0.01539 0.00612 -0.0561 0.4828 1.0000
4.250 0.8260 0.01563 0.00635 -0.0554 0.4695 1.0000
4.500 0.8499 0.01586 0.00656 -0.0545 0.4529 1.0000
4.750 0.8734 0.01608 0.00676 -0.0537 0.4337 1.0000
5.000 0.8966 0.01632 0.00697 -0.0528 0.4134 1.0000
5.250 0.9199 0.01660 0.00723 -0.0519 0.3933 1.0000
5.500 0.9427 0.01692 0.00749 -0.0510 0.3724 1.0000
5.750 0.9647 0.01730 0.00780 -0.0500 0.3503 1.0000
6.000 0.9867 0.01773 0.00816 -0.0491 0.3297 1.0000
6.250 1.0087 0.01819 0.00858 -0.0482 0.3129 1.0000
6.500 1.0306 0.01867 0.00905 -0.0473 0.2984 1.0000
6.750 1.0525 0.01916 0.00958 -0.0464 0.2858 1.0000
7.000 1.0739 0.01967 0.01011 -0.0454 0.2733 1.0000
7.250 1.0945 0.02023 0.01067 -0.0444 0.2572 1.0000
7.500 1.1149 0.02080 0.01127 -0.0434 0.2426 1.0000
7.750 1.1350 0.02139 0.01193 -0.0424 0.2277 1.0000
8.000 1.1545 0.02201 0.01261 -0.0413 0.2095 1.0000
8.250 1.1725 0.02274 0.01334 -0.0400 0.1848 1.0000
8.500 1.1883 0.02365 0.01417 -0.0386 0.1364 1.0000
8.750 1.1923 0.02565 0.01564 -0.0362 0.0858 1.0000
9.000 1.2026 0.02707 0.01705 -0.0342 0.0718 1.0000
9.250 1.2136 0.02834 0.01839 -0.0323 0.0634 1.0000
9.750 1.2307 0.03092 0.02115 -0.0281 0.0556 1.0000
10.000 1.2356 0.03225 0.02260 -0.0256 0.0534 1.0000
10.250 1.2384 0.03377 0.02425 -0.0232 0.0515 1.0000
10.500 1.2382 0.03560 0.02616 -0.0212 0.0499 1.0000
10.750 1.2376 0.03762 0.02829 -0.0195 0.0484 1.0000
11.000 1.2375 0.03979 0.03060 -0.0183 0.0472 1.0000
11.250 1.2369 0.04217 0.03312 -0.0175 0.0461 1.0000
11.500 1.2358 0.04477 0.03584 -0.0170 0.0451 1.0000
11.750 1.2345 0.04749 0.03867 -0.0166 0.0441 1.0000
12.000 1.2330 0.05034 0.04160 -0.0164 0.0431 1.0000
12.250 1.2314 0.05324 0.04456 -0.0162 0.0420 1.0000
12.500 1.2335 0.05579 0.04717 -0.0157 0.0409 1.0000
12.750 1.2374 0.05825 0.04978 -0.0154 0.0399 1.0000
13.000 1.2426 0.06060 0.05226 -0.0149 0.0389 1.0000
13.250 1.2479 0.06301 0.05479 -0.0145 0.0377 1.0000
13.500 1.2526 0.06553 0.05738 -0.0142 0.0364 1.0000
13.750 1.2604 0.06771 0.05955 -0.0136 0.0351 1.0000
14.000 1.2731 0.06973 0.06162 -0.0124 0.0339 1.0000
14.250 1.2715 0.07329 0.06544 -0.0129 0.0333 1.0000
14.500 1.2682 0.07713 0.06953 -0.0137 0.0326 1.0000
14.750 1.2634 0.08126 0.07390 -0.0149 0.0319 1.0000
15.000 1.2575 0.08564 0.07849 -0.0163 0.0312 1.0000
15.250 1.2507 0.09021 0.08326 -0.0179 0.0305 1.0000
15.500 1.2435 0.09502 0.08825 -0.0198 0.0300 1.0000
15.750 1.2347 0.10021 0.09362 -0.0222 0.0294 1.0000
16.000 1.2247 0.10579 0.09938 -0.0248 0.0291 1.0000
16.250 1.2131 0.11187 0.10565 -0.0280 0.0288 1.0000
16.500 1.1994 0.11866 0.11264 -0.0319 0.0287 1.0000
16.750 1.1827 0.12639 0.12057 -0.0366 0.0286 1.0000
17.000 1.1597 0.13608 0.13049 -0.0430 0.0288 1.0000
17.250 1.1192 0.15154 0.14625 -0.0537 0.0295 1.0000
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