GOE 137 (MVA H.15) AIRFOIL (goe137-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 137 (MVA H.15) AIRFOIL (goe137-il) Reynolds number: 100,000 Max Cl/Cd: 59.46 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe137-il-100000-n5.txt Download as CSV file: xf-goe137-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 137 (MVA H.15) 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3323 0.09912 0.09444 -0.0250 1.0000 0.0453
-8.000 -0.3366 0.09726 0.09269 -0.0288 1.0000 0.0470
-7.750 -0.3379 0.09478 0.09030 -0.0321 1.0000 0.0474
-7.500 -0.3348 0.09168 0.08725 -0.0353 1.0000 0.0476
-7.250 -0.3318 0.08846 0.08409 -0.0376 1.0000 0.0477
-7.000 -0.3289 0.08519 0.08086 -0.0394 1.0000 0.0477
-6.750 -0.3262 0.08192 0.07763 -0.0406 1.0000 0.0478
-6.500 -0.3237 0.07871 0.07444 -0.0411 1.0000 0.0478
-6.250 -0.3244 0.07503 0.07089 -0.0329 0.9987 0.0426
-6.000 -0.2927 0.06902 0.06479 -0.0421 0.9892 0.0414
-5.750 -0.2583 0.06316 0.05881 -0.0513 0.9799 0.0420
-5.500 -0.2208 0.05598 0.05142 -0.0611 0.9705 0.0388
-5.250 -0.1801 0.04843 0.04353 -0.0704 0.9620 0.0373
-5.000 -0.1461 0.04489 0.03977 -0.0748 0.9528 0.0408
-4.750 -0.1107 0.03956 0.03404 -0.0796 0.9419 0.0419
-4.500 -0.0750 0.03436 0.02831 -0.0835 0.9317 0.0430
-4.250 -0.0382 0.02996 0.02316 -0.0865 0.9223 0.0464
-4.000 -0.0065 0.02692 0.01947 -0.0877 0.9097 0.0473
-3.750 0.0233 0.02452 0.01668 -0.0886 0.8969 0.0501
-3.500 0.0533 0.02304 0.01491 -0.0892 0.8836 0.0526
-3.250 0.0835 0.02148 0.01296 -0.0894 0.8702 0.0536
-3.000 0.1130 0.02022 0.01139 -0.0894 0.8564 0.0549
-2.750 0.1420 0.01922 0.01013 -0.0892 0.8424 0.0567
-2.500 0.1706 0.01851 0.00916 -0.0890 0.8283 0.0602
-2.250 0.1986 0.01779 0.00825 -0.0886 0.8143 0.0615
-2.000 0.2261 0.01709 0.00743 -0.0882 0.8006 0.0625
-1.750 0.2532 0.01650 0.00676 -0.0877 0.7872 0.0642
-1.500 0.2804 0.01609 0.00625 -0.0873 0.7742 0.0666
-1.250 0.3076 0.01577 0.00581 -0.0868 0.7616 0.0702
-1.000 0.3348 0.01551 0.00544 -0.0864 0.7492 0.0756
-0.750 0.3620 0.01527 0.00521 -0.0860 0.7367 0.0895
-0.500 0.3891 0.01504 0.00506 -0.0857 0.7249 0.1379
-0.250 0.4163 0.01471 0.00497 -0.0856 0.7137 0.2327
0.000 0.4453 0.01275 0.00486 -0.0853 0.7035 1.0000
0.250 0.4724 0.01290 0.00478 -0.0850 0.6919 1.0000
0.500 0.4994 0.01305 0.00473 -0.0847 0.6809 1.0000
0.750 0.5265 0.01321 0.00471 -0.0843 0.6705 1.0000
1.000 0.5535 0.01338 0.00470 -0.0840 0.6601 1.0000
1.250 0.5803 0.01355 0.00475 -0.0837 0.6483 1.0000
1.500 0.6070 0.01373 0.00480 -0.0834 0.6366 1.0000
1.750 0.6337 0.01390 0.00486 -0.0831 0.6251 1.0000
2.000 0.6603 0.01408 0.00492 -0.0827 0.6134 1.0000
2.250 0.6868 0.01426 0.00502 -0.0824 0.6011 1.0000
2.500 0.7132 0.01445 0.00514 -0.0820 0.5882 1.0000
2.750 0.7396 0.01464 0.00529 -0.0817 0.5757 1.0000
3.000 0.7659 0.01484 0.00544 -0.0814 0.5631 1.0000
3.250 0.7922 0.01504 0.00560 -0.0810 0.5509 1.0000
3.500 0.8185 0.01526 0.00579 -0.0807 0.5399 1.0000
3.750 0.8446 0.01549 0.00602 -0.0804 0.5282 1.0000
4.000 0.8706 0.01572 0.00625 -0.0800 0.5157 1.0000
4.250 0.8965 0.01596 0.00652 -0.0797 0.5034 1.0000
4.500 0.9223 0.01622 0.00678 -0.0793 0.4915 1.0000
4.750 0.9477 0.01648 0.00705 -0.0789 0.4785 1.0000
5.000 0.9730 0.01676 0.00736 -0.0784 0.4655 1.0000
5.250 0.9982 0.01707 0.00768 -0.0779 0.4537 1.0000
5.500 1.0233 0.01739 0.00807 -0.0775 0.4414 1.0000
5.750 1.0482 0.01772 0.00848 -0.0771 0.4294 1.0000
6.000 1.0730 0.01808 0.00894 -0.0766 0.4178 1.0000
6.250 1.0975 0.01846 0.00939 -0.0761 0.4062 1.0000
6.500 1.1214 0.01886 0.00986 -0.0755 0.3933 1.0000
6.750 1.1445 0.01927 0.01035 -0.0748 0.3758 1.0000
7.000 1.1654 0.01974 0.01082 -0.0737 0.3501 1.0000
7.250 1.1855 0.02028 0.01134 -0.0727 0.3211 1.0000
7.500 1.2054 0.02089 0.01194 -0.0716 0.2920 1.0000
7.750 1.2232 0.02167 0.01261 -0.0704 0.2513 1.0000
8.000 1.2382 0.02272 0.01343 -0.0689 0.2086 1.0000
8.250 1.2522 0.02392 0.01449 -0.0673 0.1795 1.0000
8.500 1.2677 0.02500 0.01557 -0.0659 0.1593 1.0000
8.750 1.2816 0.02622 0.01675 -0.0642 0.1107 1.0000
9.250 1.2806 0.03093 0.02064 -0.0583 0.0290 1.0000
9.500 1.2845 0.03258 0.02234 -0.0555 0.0258 1.0000
9.750 1.2894 0.03418 0.02413 -0.0531 0.0242 1.0000
10.000 1.2926 0.03599 0.02613 -0.0508 0.0228 1.0000
10.250 1.2936 0.03807 0.02840 -0.0488 0.0214 1.0000
10.500 1.2923 0.04048 0.03099 -0.0471 0.0202 1.0000
10.750 1.2886 0.04329 0.03402 -0.0458 0.0194 1.0000
11.000 1.2833 0.04645 0.03738 -0.0448 0.0188 1.0000
11.250 1.2769 0.04995 0.04107 -0.0443 0.0184 1.0000
11.500 1.2697 0.05370 0.04501 -0.0441 0.0181 1.0000
11.750 1.2642 0.05738 0.04883 -0.0441 0.0179 1.0000
12.000 1.2604 0.06093 0.05255 -0.0441 0.0177 1.0000
12.250 1.2569 0.06449 0.05627 -0.0441 0.0175 1.0000
12.500 1.2540 0.06798 0.05991 -0.0441 0.0173 1.0000
12.750 1.2522 0.07136 0.06344 -0.0440 0.0171 1.0000
13.000 1.2510 0.07468 0.06691 -0.0439 0.0167 1.0000
13.250 1.2502 0.07803 0.07040 -0.0439 0.0163 1.0000
13.500 1.2494 0.08144 0.07397 -0.0439 0.0158 1.0000
13.750 1.2484 0.08495 0.07763 -0.0441 0.0153 1.0000
14.000 1.2473 0.08857 0.08141 -0.0444 0.0149 1.0000
14.250 1.2460 0.09232 0.08532 -0.0448 0.0146 1.0000
14.500 1.2439 0.09629 0.08947 -0.0453 0.0145 1.0000
14.750 1.2403 0.10063 0.09401 -0.0463 0.0144 1.0000
15.000 1.2352 0.10539 0.09896 -0.0477 0.0143 1.0000
15.250 1.2285 0.11061 0.10439 -0.0496 0.0142 1.0000
15.500 1.2204 0.11627 0.11025 -0.0520 0.0142 1.0000
15.750 1.2110 0.12240 0.11664 -0.0550 0.0142 1.0000
16.000 1.2004 0.12903 0.12348 -0.0585 0.0142 1.0000
16.250 1.1886 0.13628 0.13093 -0.0627 0.0142 1.0000
16.500 1.1759 0.14415 0.13893 -0.0675 0.0143 1.0000
16.750 1.1620 0.15277 0.14774 -0.0729 0.0144 1.0000
17.000 1.1469 0.16235 0.15749 -0.0791 0.0146 1.0000
17.250 1.1303 0.17324 0.16852 -0.0861 0.0149 1.0000
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Polar data table (+)
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