GOE 424 AIRFOIL (goe424-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 424 AIRFOIL (goe424-il) Reynolds number: 200,000 Max Cl/Cd: 59 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe424-il-200000.txt Download as CSV file: xf-goe424-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 424 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2587 0.10301 0.09973 -0.0757 0.9855 0.0766
-11.500 -0.2237 0.10150 0.09819 -0.0771 0.9827 0.0787
-11.250 -0.2222 0.09487 0.09157 -0.0843 0.9772 0.0841
-11.000 -0.0987 0.07837 0.07518 -0.1019 0.9392 0.0995
-10.750 -0.0701 0.07815 0.07493 -0.1000 0.9215 0.1030
-9.750 -0.3012 0.05574 0.05206 -0.1151 0.8967 0.1036
-9.500 -0.3362 0.05350 0.04933 -0.1116 0.8720 0.1091
-9.250 -0.3262 0.04994 0.04578 -0.1110 0.8499 0.1143
-9.000 -0.3150 0.04858 0.04424 -0.1095 0.8249 0.1209
-8.750 -0.2606 0.03638 0.03202 -0.1071 0.7584 0.1350
-8.500 -0.3470 0.03426 0.02762 -0.1002 0.7856 0.0729
-8.250 -0.3309 0.03181 0.02478 -0.0985 0.7652 0.0708
-8.000 -0.3139 0.02981 0.02230 -0.0967 0.7472 0.0692
-7.750 -0.2961 0.02828 0.02018 -0.0948 0.7318 0.0677
-7.500 -0.2730 0.02697 0.01863 -0.0940 0.7175 0.0678
-7.250 -0.2479 0.02583 0.01740 -0.0937 0.7051 0.0691
-7.000 -0.2228 0.02487 0.01625 -0.0933 0.6953 0.0701
-6.750 -0.1975 0.02394 0.01515 -0.0928 0.6858 0.0706
-6.500 -0.1710 0.02311 0.01414 -0.0925 0.6782 0.0713
-6.250 -0.1452 0.02242 0.01335 -0.0922 0.6704 0.0726
-6.000 -0.1187 0.02186 0.01261 -0.0919 0.6641 0.0739
-5.750 -0.0925 0.02132 0.01197 -0.0916 0.6577 0.0748
-5.500 -0.0664 0.02081 0.01138 -0.0913 0.6514 0.0755
-5.250 -0.0405 0.01989 0.01048 -0.0911 0.6463 0.0771
-5.000 -0.0167 0.01936 0.00999 -0.0906 0.6414 0.0791
-4.750 0.0067 0.01895 0.00959 -0.0899 0.6365 0.0811
-4.500 0.0303 0.01859 0.00919 -0.0892 0.6321 0.0829
-4.250 0.0546 0.01832 0.00883 -0.0887 0.6283 0.0847
-4.000 0.0772 0.01801 0.00850 -0.0879 0.6246 0.0869
-3.750 0.0989 0.01766 0.00819 -0.0870 0.6205 0.0906
-3.500 0.1229 0.01747 0.00794 -0.0864 0.6164 0.0949
-3.250 0.1476 0.01727 0.00768 -0.0859 0.6128 0.1001
-3.000 0.1729 0.01711 0.00747 -0.0855 0.6097 0.1112
-2.750 0.1887 0.01619 0.00724 -0.0840 0.6068 0.2519
-2.500 0.2024 0.01541 0.00729 -0.0818 0.6037 0.4473
-2.250 0.2231 0.01524 0.00744 -0.0804 0.6004 0.5274
-2.000 0.2464 0.01521 0.00757 -0.0795 0.5972 0.5844
-1.750 0.2715 0.01526 0.00767 -0.0788 0.5942 0.6256
-1.500 0.2979 0.01540 0.00783 -0.0784 0.5915 0.6609
-1.250 0.3224 0.01553 0.00803 -0.0777 0.5888 0.6885
-1.000 0.3461 0.01563 0.00825 -0.0768 0.5859 0.7160
-0.750 0.3703 0.01576 0.00846 -0.0760 0.5830 0.7446
-0.500 0.3954 0.01589 0.00865 -0.0753 0.5800 0.7707
-0.250 0.4218 0.01604 0.00882 -0.0748 0.5772 0.7944
0.000 0.4486 0.01625 0.00901 -0.0744 0.5748 0.8199
0.250 0.4758 0.01660 0.00934 -0.0740 0.5725 0.8436
0.500 0.4993 0.01685 0.00969 -0.0729 0.5699 0.8658
0.750 0.5245 0.01713 0.01004 -0.0721 0.5669 0.8874
1.000 0.5534 0.01744 0.01036 -0.0721 0.5637 0.9070
1.250 0.5874 0.01775 0.01064 -0.0732 0.5610 0.9225
1.500 0.6235 0.01805 0.01087 -0.0748 0.5585 0.9358
1.750 0.6686 0.01839 0.01110 -0.0784 0.5560 0.9437
2.000 0.7076 0.01878 0.01147 -0.0811 0.5532 0.9532
2.250 0.7512 0.01910 0.01184 -0.0848 0.5499 0.9598
2.500 0.7915 0.01938 0.01212 -0.0878 0.5466 0.9684
2.750 0.8375 0.01959 0.01229 -0.0920 0.5433 0.9747
3.000 0.8811 0.01978 0.01242 -0.0957 0.5406 0.9821
3.250 0.9288 0.01998 0.01253 -0.1001 0.5379 0.9874
3.500 0.9704 0.02031 0.01290 -0.1038 0.5346 0.9943
3.750 1.0111 0.02055 0.01321 -0.1073 0.5306 1.0000
4.000 1.0244 0.02074 0.01342 -0.1052 0.5273 1.0000
4.250 1.0418 0.02083 0.01348 -0.1038 0.5241 1.0000
4.500 1.0640 0.02087 0.01342 -0.1030 0.5211 1.0000
4.750 1.0786 0.02115 0.01370 -0.1010 0.5175 1.0000
5.000 1.0854 0.02142 0.01407 -0.0976 0.5131 1.0000
5.250 1.0997 0.02159 0.01425 -0.0954 0.5093 1.0000
5.500 1.1198 0.02170 0.01432 -0.0943 0.5062 1.0000
5.750 1.1447 0.02180 0.01436 -0.0940 0.5036 1.0000
6.000 1.1625 0.02214 0.01470 -0.0925 0.5005 1.0000
6.250 1.1669 0.02255 0.01523 -0.0886 0.4962 1.0000
6.500 1.1818 0.02277 0.01549 -0.0865 0.4923 1.0000
6.750 1.2043 0.02286 0.01556 -0.0858 0.4891 1.0000
7.000 1.2327 0.02291 0.01556 -0.0861 0.4864 1.0000
7.250 1.2512 0.02325 0.01592 -0.0848 0.4830 1.0000
7.500 1.2550 0.02372 0.01654 -0.0808 0.4782 1.0000
7.750 1.2738 0.02386 0.01670 -0.0795 0.4741 1.0000
8.000 1.3020 0.02377 0.01657 -0.0798 0.4707 1.0000
8.250 1.3378 0.02374 0.01646 -0.0814 0.4676 1.0000
8.500 1.3322 0.02439 0.01732 -0.0760 0.4621 1.0000
8.750 1.3483 0.02458 0.01756 -0.0743 0.4576 1.0000
9.000 1.3767 0.02447 0.01743 -0.0747 0.4540 1.0000
9.250 1.4077 0.02446 0.01737 -0.0755 0.4503 1.0000
9.500 1.3998 0.02511 0.01822 -0.0699 0.4443 1.0000
9.750 1.4170 0.02509 0.01821 -0.0683 0.4395 1.0000
10.000 1.4561 0.02468 0.01771 -0.0703 0.4352 1.0000
10.250 1.4385 0.02547 0.01869 -0.0632 0.4290 1.0000
10.500 1.4513 0.02557 0.01881 -0.0611 0.4233 1.0000
10.750 1.4806 0.02526 0.01843 -0.0615 0.4182 1.0000
11.000 1.4649 0.02631 0.01967 -0.0556 0.4107 1.0000
11.250 1.4849 0.02622 0.01954 -0.0547 0.4047 1.0000
11.500 1.4808 0.02722 0.02065 -0.0510 0.3973 1.0000
11.750 1.4901 0.02773 0.02119 -0.0491 0.3904 1.0000
12.000 1.4960 0.02859 0.02209 -0.0469 0.3834 1.0000
12.250 1.4985 0.02965 0.02322 -0.0446 0.3758 1.0000
12.500 1.5076 0.03051 0.02408 -0.0431 0.3686 1.0000
12.750 1.5074 0.03196 0.02559 -0.0410 0.3605 1.0000
13.000 1.5149 0.03307 0.02670 -0.0396 0.3529 1.0000
13.250 1.5151 0.03469 0.02837 -0.0378 0.3446 1.0000
13.500 1.5177 0.03627 0.02996 -0.0363 0.3365 1.0000
13.750 1.5205 0.03787 0.03156 -0.0350 0.3283 1.0000
14.000 1.5183 0.04001 0.03374 -0.0335 0.3202 1.0000
14.250 1.5235 0.04155 0.03525 -0.0325 0.3123 1.0000
14.500 1.5180 0.04418 0.03796 -0.0313 0.3045 1.0000
14.750 1.5232 0.04583 0.03958 -0.0305 0.2969 1.0000
15.000 1.5183 0.04858 0.04240 -0.0296 0.2897 1.0000
15.250 1.5197 0.05073 0.04455 -0.0289 0.2827 1.0000
15.500 1.5207 0.05298 0.04684 -0.0283 0.2760 1.0000
15.750 1.5156 0.05595 0.04988 -0.0278 0.2694 1.0000
16.000 1.5268 0.05711 0.05097 -0.0273 0.2632 1.0000
16.250 1.5148 0.06098 0.05501 -0.0269 0.2570 1.0000
16.500 1.5223 0.06260 0.05660 -0.0266 0.2510 1.0000
16.750 1.5179 0.06567 0.05976 -0.0264 0.2452 1.0000
17.000 1.5119 0.06898 0.06315 -0.0263 0.2391 1.0000
17.250 1.5204 0.07047 0.06459 -0.0260 0.2329 1.0000
17.500 1.5057 0.07498 0.06926 -0.0262 0.2268 1.0000
17.750 1.5107 0.07696 0.07120 -0.0262 0.2205 1.0000
18.000 1.5006 0.08098 0.07535 -0.0265 0.2147 1.0000
18.250 1.4939 0.08459 0.07903 -0.0268 0.2086 1.0000
18.500 1.4961 0.08699 0.08142 -0.0270 0.2026 1.0000
18.750 1.4826 0.09167 0.08626 -0.0276 0.1969 1.0000
19.000 1.4858 0.09401 0.08856 -0.0280 0.1911 1.0000
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Polar data table (+)
Polar graphs
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