GOE 402 AIRFOIL (goe402-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 402 AIRFOIL (goe402-il) Reynolds number: 100,000 Max Cl/Cd: 59.94 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe402-il-100000-n5.txt Download as CSV file: xf-goe402-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 402 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.2574 0.09841 0.09396 -0.0251 1.0000 0.0298
-7.250 -0.2607 0.09702 0.09269 -0.0247 1.0000 0.0300
-7.000 -0.2605 0.09550 0.09127 -0.0257 1.0000 0.0302
-6.750 -0.2597 0.09395 0.08982 -0.0268 1.0000 0.0304
-6.500 -0.2478 0.09178 0.08770 -0.0311 0.9965 0.0306
-6.250 -0.2107 0.08769 0.08355 -0.0413 0.9842 0.0307
-6.000 -0.1759 0.08340 0.07919 -0.0497 0.9713 0.0309
-5.750 -0.1436 0.07905 0.07476 -0.0563 0.9582 0.0309
-5.500 -0.1291 0.07256 0.06835 -0.0572 0.9469 0.0315
-5.250 -0.1083 0.06782 0.06361 -0.0591 0.9346 0.0323
-5.000 -0.0820 0.06373 0.05946 -0.0628 0.9200 0.0334
-4.750 -0.0508 0.05990 0.05555 -0.0678 0.9051 0.0346
-4.500 -0.0166 0.05618 0.05172 -0.0733 0.8903 0.0362
-4.250 0.0373 0.05335 0.04855 -0.0830 0.8752 0.0424
-4.000 0.0833 0.05036 0.04517 -0.0894 0.8609 0.0430
-3.750 0.1048 0.04537 0.04017 -0.0911 0.8468 0.0440
-3.500 0.1291 0.04215 0.03685 -0.0925 0.8315 0.0460
-3.250 0.1601 0.03941 0.03387 -0.0947 0.8156 0.0491
-3.000 0.1947 0.03672 0.03082 -0.0974 0.7994 0.0578
-2.750 0.2288 0.03478 0.02842 -0.0992 0.7830 0.0689
-2.500 0.2580 0.03159 0.02493 -0.0995 0.7682 0.0531
-2.250 0.2868 0.02904 0.02206 -0.1001 0.7547 0.0502
-2.000 0.3171 0.02695 0.01955 -0.1004 0.7427 0.0514
-1.750 0.3470 0.02486 0.01702 -0.1005 0.7321 0.0491
-1.500 0.3764 0.02338 0.01508 -0.1004 0.7215 0.0521
-1.250 0.4050 0.02209 0.01332 -0.1000 0.7102 0.0534
-1.000 0.4329 0.02093 0.01179 -0.0996 0.6992 0.0536
-0.750 0.4608 0.02025 0.01070 -0.0991 0.6886 0.0554
-0.500 0.4869 0.01917 0.00953 -0.0989 0.6775 0.0591
-0.250 0.5138 0.01849 0.00861 -0.0983 0.6658 0.0588
0.000 0.5404 0.01792 0.00787 -0.0977 0.6543 0.0588
0.250 0.5667 0.01744 0.00726 -0.0971 0.6429 0.0592
0.500 0.5928 0.01703 0.00674 -0.0965 0.6315 0.0601
0.750 0.6186 0.01667 0.00633 -0.0959 0.6191 0.0614
1.000 0.6437 0.01641 0.00599 -0.0951 0.6062 0.0634
1.250 0.6696 0.01630 0.00575 -0.0945 0.5931 0.0680
1.500 0.6956 0.01612 0.00551 -0.0941 0.5801 0.0746
1.750 0.7217 0.01609 0.00535 -0.0935 0.5672 0.0778
2.250 0.7735 0.01612 0.00521 -0.0925 0.5402 0.0920
2.750 0.8283 0.01482 0.00534 -0.0924 0.5122 1.0000
3.000 0.8533 0.01507 0.00544 -0.0917 0.4989 1.0000
3.250 0.8782 0.01534 0.00558 -0.0911 0.4860 1.0000
3.500 0.9031 0.01562 0.00576 -0.0905 0.4731 1.0000
3.750 0.9279 0.01591 0.00600 -0.0899 0.4609 1.0000
4.000 0.9526 0.01622 0.00624 -0.0894 0.4492 1.0000
4.250 0.9772 0.01655 0.00648 -0.0888 0.4385 1.0000
4.500 1.0016 0.01688 0.00679 -0.0882 0.4278 1.0000
4.750 1.0261 0.01722 0.00712 -0.0876 0.4175 1.0000
5.000 1.0503 0.01758 0.00744 -0.0870 0.4080 1.0000
5.250 1.0744 0.01795 0.00779 -0.0864 0.3990 1.0000
5.500 1.0986 0.01833 0.00823 -0.0859 0.3903 1.0000
5.750 1.1227 0.01873 0.00863 -0.0853 0.3835 1.0000
6.000 1.1470 0.01914 0.00913 -0.0848 0.3766 1.0000
6.250 1.1711 0.01958 0.00963 -0.0843 0.3706 1.0000
6.500 1.1951 0.02002 0.01017 -0.0837 0.3644 1.0000
6.750 1.2188 0.02048 0.01073 -0.0832 0.3581 1.0000
7.000 1.2427 0.02097 0.01128 -0.0826 0.3528 1.0000
7.250 1.2660 0.02145 0.01199 -0.0820 0.3463 1.0000
7.500 1.2892 0.02194 0.01256 -0.0813 0.3400 1.0000
7.750 1.3118 0.02245 0.01329 -0.0806 0.3331 1.0000
8.000 1.3346 0.02298 0.01398 -0.0799 0.3272 1.0000
8.250 1.3558 0.02350 0.01470 -0.0790 0.3185 1.0000
8.500 1.3724 0.02387 0.01525 -0.0773 0.3003 1.0000
8.750 1.3864 0.02426 0.01574 -0.0754 0.2757 1.0000
9.000 1.4012 0.02478 0.01638 -0.0736 0.2512 1.0000
9.250 1.4127 0.02554 0.01714 -0.0715 0.2051 1.0000
9.500 1.4077 0.02768 0.01862 -0.0679 0.1340 1.0000
9.750 1.4042 0.02993 0.02066 -0.0644 0.0969 1.0000
10.000 1.3904 0.03268 0.02304 -0.0601 0.0475 1.0000
10.250 1.3813 0.03517 0.02552 -0.0567 0.0339 1.0000
10.500 1.3749 0.03765 0.02810 -0.0542 0.0285 1.0000
10.750 1.3690 0.04033 0.03093 -0.0523 0.0259 1.0000
11.000 1.3608 0.04352 0.03426 -0.0511 0.0241 1.0000
11.250 1.3527 0.04702 0.03792 -0.0505 0.0230 1.0000
11.500 1.3455 0.05066 0.04184 -0.0503 0.0220 1.0000
11.750 1.3370 0.05470 0.04608 -0.0506 0.0211 1.0000
12.000 1.3274 0.05908 0.05066 -0.0512 0.0203 1.0000
12.250 1.3175 0.06372 0.05549 -0.0521 0.0195 1.0000
12.500 1.3071 0.06862 0.06057 -0.0533 0.0190 1.0000
12.750 1.2966 0.07369 0.06581 -0.0547 0.0185 1.0000
13.000 1.2861 0.07888 0.07117 -0.0561 0.0180 1.0000
13.250 1.2768 0.08398 0.07643 -0.0576 0.0177 1.0000
13.500 1.2690 0.08894 0.08153 -0.0590 0.0173 1.0000
13.750 1.2631 0.09358 0.08630 -0.0602 0.0169 1.0000
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Polar data table (+)
Polar graphs
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