GOE 426 AIRFOIL (goe426-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 426 AIRFOIL (goe426-il) Reynolds number: 500,000 Max Cl/Cd: 112.68 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe426-il-500000.txt Download as CSV file: xf-goe426-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 426 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2659 0.10524 0.10293 -0.0455 1.0000 0.0320
-10.250 -0.2851 0.09933 0.09707 -0.0506 1.0000 0.0335
-10.000 -0.2862 0.09405 0.09181 -0.0550 0.9978 0.0336
-9.750 -0.2736 0.09015 0.08792 -0.0560 0.9885 0.0340
-9.500 -0.2535 0.08721 0.08497 -0.0589 0.9824 0.0344
-9.250 -0.2329 0.08415 0.08191 -0.0624 0.9748 0.0348
-9.000 -0.2102 0.08036 0.07809 -0.0678 0.9683 0.0355
-8.750 -0.1877 0.07575 0.07346 -0.0748 0.9583 0.0365
-8.000 -0.2350 0.04751 0.04457 -0.1065 0.8663 0.0402
-7.750 -0.2230 0.04558 0.04257 -0.1061 0.8472 0.0405
-7.500 -0.2120 0.04366 0.04052 -0.1059 0.8281 0.0408
-7.250 -0.1994 0.04191 0.03864 -0.1056 0.8099 0.0413
-7.000 -0.1773 0.02851 0.02528 -0.0974 0.7652 0.0421
-6.750 -0.1676 0.02566 0.02224 -0.0980 0.7539 0.0433
-6.500 -0.1599 0.03615 0.03176 -0.1051 0.7646 0.0468
-6.250 -0.1510 0.03042 0.02583 -0.1055 0.7537 0.0480
-6.000 -0.1298 0.02889 0.02422 -0.1054 0.7424 0.0486
-5.750 -0.1081 0.02758 0.02278 -0.1052 0.7311 0.0494
-5.500 -0.0857 0.02631 0.02137 -0.1049 0.7201 0.0506
-5.250 -0.0626 0.02511 0.01991 -0.1045 0.7098 0.0531
-5.000 -0.0416 0.02309 0.01744 -0.1041 0.6995 0.0571
-4.750 -0.0171 0.02198 0.01631 -0.1040 0.6893 0.0584
-4.500 0.0070 0.01848 0.01214 -0.1028 0.6798 0.0489
-4.250 0.0332 0.01589 0.00901 -0.1018 0.6698 0.0406
-4.000 0.0595 0.01516 0.00813 -0.1014 0.6596 0.0405
-3.750 0.0860 0.01443 0.00730 -0.1011 0.6491 0.0407
-3.500 0.1124 0.01382 0.00665 -0.1009 0.6393 0.0413
-3.250 0.1388 0.01339 0.00613 -0.1006 0.6298 0.0421
-3.000 0.1656 0.01293 0.00563 -0.1004 0.6206 0.0427
-2.750 0.1921 0.01254 0.00516 -0.1001 0.6124 0.0431
-2.500 0.2190 0.01217 0.00476 -0.0998 0.6042 0.0437
-2.000 0.2728 0.01162 0.00410 -0.0994 0.5899 0.0453
-1.750 0.2997 0.01143 0.00384 -0.0991 0.5833 0.0462
-1.500 0.3269 0.01125 0.00361 -0.0990 0.5774 0.0471
-1.250 0.3535 0.01086 0.00322 -0.0988 0.5714 0.0496
-1.000 0.3806 0.01073 0.00304 -0.0986 0.5659 0.0517
-0.750 0.4083 0.01062 0.00289 -0.0986 0.5609 0.0540
-0.500 0.4359 0.01048 0.00273 -0.0985 0.5558 0.0572
-0.250 0.4634 0.01039 0.00260 -0.0984 0.5510 0.0638
0.000 0.4889 0.00973 0.00251 -0.0983 0.5466 0.2532
0.250 0.5126 0.00892 0.00262 -0.0980 0.5424 0.5463
0.500 0.5383 0.00876 0.00271 -0.0976 0.5381 0.6411
0.750 0.5640 0.00871 0.00279 -0.0970 0.5338 0.7028
1.000 0.5892 0.00865 0.00289 -0.0963 0.5298 0.7643
1.500 0.6395 0.00834 0.00300 -0.0945 0.5219 0.9174
1.750 0.6876 0.00843 0.00302 -0.0989 0.5171 1.0000
2.000 0.7148 0.00855 0.00309 -0.0988 0.5132 1.0000
2.250 0.7421 0.00864 0.00316 -0.0987 0.5092 1.0000
2.500 0.7694 0.00874 0.00322 -0.0986 0.5052 1.0000
2.750 0.7965 0.00889 0.00330 -0.0985 0.5011 1.0000
3.000 0.8237 0.00903 0.00341 -0.0984 0.4971 1.0000
3.250 0.8508 0.00911 0.00350 -0.0983 0.4930 1.0000
3.500 0.8780 0.00922 0.00359 -0.0982 0.4889 1.0000
3.750 0.9049 0.00938 0.00369 -0.0980 0.4849 1.0000
4.000 0.9319 0.00953 0.00382 -0.0979 0.4807 1.0000
4.250 0.9588 0.00961 0.00393 -0.0978 0.4761 1.0000
4.500 0.9855 0.00973 0.00404 -0.0976 0.4716 1.0000
4.750 1.0122 0.00992 0.00418 -0.0974 0.4674 1.0000
5.000 1.0388 0.01003 0.00433 -0.0973 0.4630 1.0000
5.250 1.0652 0.01013 0.00446 -0.0971 0.4581 1.0000
5.500 1.0914 0.01028 0.00459 -0.0968 0.4533 1.0000
5.750 1.1176 0.01045 0.00476 -0.0966 0.4485 1.0000
6.000 1.1436 0.01055 0.00492 -0.0963 0.4429 1.0000
6.250 1.1691 0.01071 0.00506 -0.0960 0.4374 1.0000
6.500 1.1946 0.01086 0.00524 -0.0956 0.4316 1.0000
6.750 1.2198 0.01099 0.00539 -0.0952 0.4248 1.0000
7.000 1.2440 0.01115 0.00556 -0.0947 0.4169 1.0000
7.250 1.2685 0.01129 0.00572 -0.0941 0.4086 1.0000
7.500 1.2924 0.01149 0.00593 -0.0936 0.4013 1.0000
7.750 1.3157 0.01168 0.00612 -0.0929 0.3916 1.0000
8.000 1.3386 0.01188 0.00634 -0.0921 0.3808 1.0000
8.250 1.3603 0.01215 0.00659 -0.0912 0.3695 1.0000
8.500 1.3807 0.01246 0.00687 -0.0901 0.3563 1.0000
9.000 1.4194 0.01318 0.00754 -0.0875 0.3292 1.0000
9.250 1.4380 0.01356 0.00791 -0.0861 0.3159 1.0000
9.500 1.4543 0.01400 0.00834 -0.0843 0.3013 1.0000
9.750 1.4668 0.01450 0.00880 -0.0819 0.2855 1.0000
10.000 1.4762 0.01512 0.00936 -0.0791 0.2671 1.0000
10.250 1.4823 0.01593 0.01006 -0.0759 0.2412 1.0000
10.500 1.4792 0.01722 0.01114 -0.0716 0.2038 1.0000
10.750 1.4669 0.01911 0.01276 -0.0667 0.1596 1.0000
11.000 1.4538 0.02127 0.01472 -0.0623 0.1257 1.0000
11.250 1.4433 0.02354 0.01685 -0.0587 0.0998 1.0000
11.500 1.4323 0.02610 0.01927 -0.0557 0.0725 1.0000
11.750 1.4181 0.02919 0.02223 -0.0531 0.0502 1.0000
12.000 1.4093 0.03213 0.02513 -0.0514 0.0374 1.0000
12.250 1.4052 0.03485 0.02785 -0.0501 0.0316 1.0000
12.500 1.4030 0.03749 0.03054 -0.0491 0.0286 1.0000
12.750 1.4029 0.04003 0.03315 -0.0483 0.0269 1.0000
13.000 1.4004 0.04290 0.03608 -0.0477 0.0255 1.0000
13.250 1.3956 0.04613 0.03938 -0.0472 0.0244 1.0000
13.500 1.3958 0.04892 0.04227 -0.0470 0.0236 1.0000
13.750 1.3944 0.05197 0.04541 -0.0468 0.0227 1.0000
14.000 1.3922 0.05520 0.04872 -0.0468 0.0221 1.0000
14.250 1.3884 0.05868 0.05228 -0.0469 0.0214 1.0000
14.500 1.3813 0.06270 0.05637 -0.0472 0.0208 1.0000
14.750 1.3737 0.06686 0.06061 -0.0476 0.0203 1.0000
15.000 1.3730 0.07019 0.06403 -0.0480 0.0200 1.0000
15.250 1.3712 0.07373 0.06767 -0.0484 0.0196 1.0000
15.500 1.3696 0.07733 0.07136 -0.0490 0.0191 1.0000
15.750 1.3675 0.08101 0.07511 -0.0497 0.0187 1.0000
16.000 1.3650 0.08480 0.07898 -0.0504 0.0184 1.0000
16.250 1.3628 0.08862 0.08287 -0.0513 0.0181 1.0000
16.500 1.3610 0.09240 0.08671 -0.0521 0.0178 1.0000
16.750 1.3577 0.09641 0.09077 -0.0531 0.0174 1.0000
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Polar data table (+)
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