GOE 442 AIRFOIL (goe442-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 442 AIRFOIL (goe442-il) Reynolds number: 50,000 Max Cl/Cd: 35.34 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe442-il-50000.txt Download as CSV file: xf-goe442-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 442 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3644 0.10164 0.09498 -0.0185 1.0000 0.1711
-7.500 -0.3840 0.10190 0.09543 -0.0197 1.0000 0.1728
-7.250 -0.3623 0.09619 0.08969 -0.0165 1.0000 0.1844
-7.000 -0.3816 0.09646 0.09014 -0.0195 1.0000 0.1879
-6.750 -0.3666 0.09160 0.08531 -0.0156 1.0000 0.2006
-6.250 -0.3734 0.08786 0.08176 -0.0177 1.0000 0.2178
-6.000 -0.3622 0.08357 0.07753 -0.0135 1.0000 0.2295
-5.750 -0.3596 0.08064 0.07469 -0.0124 1.0000 0.2399
-5.500 -0.3591 0.07817 0.07229 -0.0125 1.0000 0.2520
-5.000 -0.3524 0.07277 0.06703 -0.0103 1.0000 0.2826
-4.750 -0.3479 0.07009 0.06442 -0.0083 1.0000 0.3017
-4.500 -0.3454 0.06763 0.06200 -0.0076 1.0000 0.3256
-4.250 -0.3424 0.06520 0.05964 -0.0053 1.0000 0.3546
-4.000 -0.3397 0.06246 0.05700 -0.0010 1.0000 0.3858
-3.750 -0.3375 0.05983 0.05447 0.0040 1.0000 0.4201
-3.500 -0.3382 0.05739 0.05213 0.0094 1.0000 0.4630
-3.250 -0.3427 0.05541 0.05025 0.0160 1.0000 0.5180
-3.000 -0.3459 0.05266 0.04765 0.0245 1.0000 0.5663
-2.750 -0.3478 0.05007 0.04516 0.0329 1.0000 0.6168
-2.500 -0.1284 0.03735 0.02958 -0.0420 1.0000 0.1905
-2.250 -0.0940 0.03410 0.02559 -0.0438 1.0000 0.1718
-2.000 -0.0674 0.03189 0.02301 -0.0440 1.0000 0.1709
-1.750 -0.0405 0.02990 0.02062 -0.0441 1.0000 0.1684
-1.500 -0.0142 0.02853 0.01873 -0.0439 1.0000 0.1725
-1.250 0.0094 0.02726 0.01732 -0.0435 1.0000 0.1776
-1.000 0.0317 0.02642 0.01625 -0.0429 1.0000 0.1831
-0.750 0.0517 0.02588 0.01559 -0.0422 1.0000 0.1939
-0.500 0.0736 0.02559 0.01503 -0.0418 1.0000 0.2032
-0.250 0.0940 0.02549 0.01489 -0.0416 1.0000 0.2166
0.000 0.1206 0.02561 0.01509 -0.0430 0.9966 0.2411
0.250 0.1884 0.02474 0.01493 -0.0508 0.9776 0.3687
0.500 0.2607 0.02359 0.01448 -0.0586 0.9561 1.0000
0.750 0.3200 0.02425 0.01477 -0.0651 0.9298 1.0000
1.000 0.3732 0.02469 0.01497 -0.0701 0.9043 1.0000
1.250 0.4302 0.02489 0.01499 -0.0753 0.8824 1.0000
1.500 0.4770 0.02501 0.01500 -0.0786 0.8593 1.0000
1.750 0.5333 0.02481 0.01473 -0.0829 0.8408 1.0000
2.000 0.5715 0.02491 0.01477 -0.0842 0.8191 1.0000
2.250 0.6144 0.02481 0.01465 -0.0860 0.8001 1.0000
2.500 0.6571 0.02465 0.01446 -0.0874 0.7825 1.0000
2.750 0.6906 0.02482 0.01461 -0.0876 0.7635 1.0000
3.000 0.7208 0.02512 0.01490 -0.0873 0.7443 1.0000
3.250 0.7526 0.02535 0.01516 -0.0872 0.7264 1.0000
3.500 0.7848 0.02553 0.01532 -0.0868 0.7086 1.0000
3.750 0.8113 0.02576 0.01554 -0.0854 0.6867 1.0000
4.000 0.8427 0.02547 0.01520 -0.0839 0.6627 1.0000
4.250 0.8657 0.02567 0.01537 -0.0818 0.6371 1.0000
4.500 0.8917 0.02585 0.01549 -0.0801 0.6141 1.0000
4.750 0.9157 0.02629 0.01592 -0.0785 0.5921 1.0000
5.000 0.9409 0.02672 0.01635 -0.0770 0.5706 1.0000
5.250 0.9635 0.02730 0.01695 -0.0753 0.5468 1.0000
5.500 0.9858 0.02795 0.01760 -0.0735 0.5221 1.0000
5.750 1.0101 0.02858 0.01819 -0.0719 0.4965 1.0000
6.000 1.0318 0.02934 0.01892 -0.0700 0.4677 1.0000
6.250 1.0523 0.03014 0.01967 -0.0679 0.4376 1.0000
6.500 1.0718 0.03104 0.02055 -0.0659 0.4086 1.0000
6.750 1.0899 0.03229 0.02189 -0.0640 0.3838 1.0000
7.000 1.1125 0.03345 0.02307 -0.0627 0.3649 1.0000
7.250 1.1345 0.03474 0.02438 -0.0615 0.3489 1.0000
7.500 1.1539 0.03619 0.02598 -0.0601 0.3346 1.0000
7.750 1.1699 0.03804 0.02810 -0.0586 0.3225 1.0000
8.000 1.1851 0.04027 0.03066 -0.0572 0.3134 1.0000
8.250 1.2102 0.04168 0.03209 -0.0565 0.3047 1.0000
8.500 1.2139 0.04467 0.03559 -0.0542 0.2962 1.0000
8.750 1.2335 0.04651 0.03756 -0.0531 0.2882 1.0000
9.000 1.2319 0.05022 0.04175 -0.0508 0.2822 1.0000
9.250 1.2518 0.05196 0.04362 -0.0497 0.2737 1.0000
9.500 1.2377 0.05651 0.04864 -0.0470 0.2681 1.0000
9.750 1.2532 0.05828 0.05055 -0.0454 0.2582 1.0000
10.000 1.2214 0.06446 0.05706 -0.0429 0.2561 1.0000
10.250 1.1407 0.07583 0.06844 -0.0419 0.2640 1.0000
10.500 1.1190 0.08223 0.07486 -0.0423 0.2619 1.0000
11.500 1.2252 0.07538 0.06864 -0.0286 0.1802 1.0000
11.750 1.1989 0.08133 0.07466 -0.0286 0.1783 1.0000
12.000 1.1734 0.08840 0.08176 -0.0302 0.1768 1.0000
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Polar data table (+)
Polar graphs
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