GOE 113 AIRFOIL (goe113-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 113 AIRFOIL (goe113-il) Reynolds number: 100,000 Max Cl/Cd: 54.65 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe113-il-100000.txt Download as CSV file: xf-goe113-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 113 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3703 0.11314 0.10840 -0.0088 1.0000 0.0468
-9.500 -0.3689 0.10989 0.10517 -0.0099 1.0000 0.0482
-9.250 -0.4769 0.11694 0.11195 0.0006 1.0000 0.0426
-9.000 -0.4717 0.11352 0.10856 -0.0005 1.0000 0.0440
-8.750 -0.4670 0.11017 0.10524 -0.0019 1.0000 0.0454
-8.500 -0.4627 0.10687 0.10197 -0.0035 1.0000 0.0469
-8.250 -0.4591 0.10369 0.09884 -0.0055 1.0000 0.0484
-8.000 -0.4569 0.10082 0.09602 -0.0083 1.0000 0.0497
-7.750 -0.4572 0.09836 0.09364 -0.0124 1.0000 0.0506
-7.500 -0.4514 0.09544 0.09076 -0.0201 1.0000 0.0511
-7.250 -0.4411 0.09220 0.08747 -0.0275 1.0000 0.0515
-7.000 -0.4376 0.08599 0.08138 -0.0229 1.0000 0.0528
-6.750 -0.4302 0.08224 0.07766 -0.0200 1.0000 0.0551
-6.500 -0.4207 0.07865 0.07408 -0.0218 1.0000 0.0576
-6.250 -0.4089 0.07490 0.07032 -0.0254 1.0000 0.0608
-6.000 -0.3843 0.07204 0.06715 -0.0365 1.0000 0.0646
-5.750 -0.3769 0.06652 0.06174 -0.0358 1.0000 0.0661
-5.500 -0.3688 0.06306 0.05837 -0.0335 1.0000 0.0695
-5.250 -0.3406 0.06093 0.05576 -0.0401 1.0000 0.0783
-5.000 -0.3353 0.05568 0.05079 -0.0378 1.0000 0.0820
-4.750 -0.3137 0.05251 0.04730 -0.0406 1.0000 0.0937
-4.500 -0.2945 0.04979 0.04437 -0.0417 1.0000 0.1070
-4.250 -0.2820 0.04625 0.04101 -0.0402 1.0000 0.1162
-4.000 -0.2612 0.04328 0.03780 -0.0415 1.0000 0.1357
-3.750 -0.2455 0.04037 0.03495 -0.0407 1.0000 0.1532
-3.500 -0.2281 0.03786 0.03239 -0.0403 1.0000 0.1815
-2.500 -0.1816 0.02994 0.02499 -0.0297 1.0000 0.4129
-2.250 -0.0832 0.02527 0.01756 -0.0413 1.0000 0.1348
-2.000 -0.0525 0.02271 0.01454 -0.0403 1.0000 0.1006
-1.750 -0.0265 0.02129 0.01282 -0.0397 1.0000 0.0996
-1.500 -0.0008 0.02073 0.01177 -0.0385 1.0000 0.0923
-1.250 0.0246 0.01936 0.01032 -0.0383 1.0000 0.0908
-1.000 0.0496 0.01862 0.00944 -0.0382 1.0000 0.0909
-0.750 0.0752 0.01792 0.00881 -0.0387 0.9994 0.0970
-0.500 0.1264 0.01701 0.00795 -0.0435 0.9893 0.0991
-0.250 0.1772 0.01639 0.00729 -0.0482 0.9773 0.1040
0.000 0.2273 0.01585 0.00671 -0.0528 0.9641 0.1178
0.250 0.2734 0.01311 0.00638 -0.0559 0.9564 1.0000
0.500 0.3247 0.01306 0.00598 -0.0604 0.9413 1.0000
0.750 0.3686 0.01293 0.00569 -0.0633 0.9218 1.0000
1.000 0.4110 0.01274 0.00536 -0.0656 0.9030 1.0000
1.250 0.4460 0.01263 0.00515 -0.0664 0.8814 1.0000
1.500 0.4787 0.01253 0.00496 -0.0665 0.8608 1.0000
1.750 0.5064 0.01256 0.00492 -0.0657 0.8372 1.0000
2.000 0.5331 0.01263 0.00489 -0.0647 0.8146 1.0000
2.250 0.5589 0.01276 0.00493 -0.0636 0.7927 1.0000
2.500 0.5836 0.01294 0.00503 -0.0625 0.7694 1.0000
2.750 0.6082 0.01311 0.00512 -0.0611 0.7459 1.0000
3.000 0.6328 0.01330 0.00527 -0.0599 0.7229 1.0000
3.250 0.6575 0.01352 0.00548 -0.0589 0.7002 1.0000
3.500 0.6827 0.01375 0.00567 -0.0579 0.6799 1.0000
3.750 0.7075 0.01398 0.00592 -0.0570 0.6571 1.0000
4.000 0.7322 0.01420 0.00616 -0.0560 0.6329 1.0000
4.250 0.7566 0.01441 0.00644 -0.0549 0.6057 1.0000
4.500 0.7805 0.01463 0.00666 -0.0536 0.5739 1.0000
4.750 0.8025 0.01480 0.00675 -0.0520 0.5256 1.0000
5.000 0.8236 0.01507 0.00685 -0.0503 0.4614 1.0000
5.250 0.8446 0.01556 0.00708 -0.0489 0.3904 1.0000
5.500 0.8660 0.01628 0.00758 -0.0478 0.3300 1.0000
5.750 0.8871 0.01713 0.00818 -0.0468 0.2825 1.0000
6.000 0.9084 0.01800 0.00889 -0.0460 0.2339 1.0000
6.250 0.9309 0.01882 0.00955 -0.0451 0.1658 1.0000
6.500 0.9461 0.02101 0.01078 -0.0435 0.0594 1.0000
6.750 0.9644 0.02273 0.01258 -0.0419 0.0482 1.0000
7.000 0.9834 0.02423 0.01435 -0.0403 0.0450 1.0000
7.250 1.0022 0.02573 0.01605 -0.0387 0.0430 1.0000
7.500 1.0205 0.02744 0.01789 -0.0370 0.0417 1.0000
7.750 1.0402 0.02938 0.01993 -0.0354 0.0409 1.0000
8.000 1.0623 0.03160 0.02228 -0.0341 0.0404 1.0000
8.250 1.0839 0.03399 0.02482 -0.0330 0.0386 1.0000
8.500 1.1046 0.03702 0.02796 -0.0321 0.0368 1.0000
8.750 1.1252 0.03986 0.03121 -0.0307 0.0374 1.0000
9.000 1.1414 0.04325 0.03530 -0.0286 0.0392 1.0000
9.250 1.1501 0.04747 0.04019 -0.0264 0.0415 1.0000
9.500 1.1545 0.05215 0.04537 -0.0243 0.0436 1.0000
9.750 1.1558 0.05759 0.05114 -0.0226 0.0455 1.0000
10.000 1.1557 0.06105 0.05522 -0.0200 0.0496 1.0000
10.250 1.1298 0.06664 0.06140 -0.0177 0.0522 1.0000
10.500 1.1066 0.07125 0.06627 -0.0159 0.0534 1.0000
10.750 1.0831 0.07615 0.07136 -0.0162 0.0539 1.0000
11.000 1.0582 0.08199 0.07738 -0.0191 0.0538 1.0000
11.250 1.0322 0.08930 0.08476 -0.0246 0.0532 1.0000
11.500 1.0056 0.09861 0.09415 -0.0321 0.0526 1.0000
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Polar data table (+)
Polar graphs
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