GOE 432 AIRFOIL (goe432-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 432 AIRFOIL (goe432-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.58 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe432-il-1000000-n5.txt Download as CSV file: xf-goe432-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 432 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3659 0.11322 0.11154 -0.0203 1.0000 0.0044
-10.000 -0.3655 0.10965 0.10799 -0.0207 1.0000 0.0042
-8.500 -0.4276 0.02109 0.01817 -0.0997 0.9770 0.0049
-8.250 -0.4064 0.01810 0.01481 -0.1002 0.9739 0.0051
-8.000 -0.3820 0.01644 0.01291 -0.1004 0.9708 0.0052
-7.750 -0.3543 0.01522 0.01147 -0.1009 0.9683 0.0054
-7.500 -0.3255 0.01428 0.01036 -0.1014 0.9663 0.0055
-7.250 -0.2984 0.01305 0.00891 -0.1017 0.9638 0.0058
-7.000 -0.2747 0.01222 0.00794 -0.1010 0.9591 0.0061
-6.750 -0.2474 0.01159 0.00720 -0.1009 0.9553 0.0063
-6.500 -0.2180 0.01105 0.00655 -0.1012 0.9522 0.0066
-6.250 -0.1925 0.01059 0.00600 -0.1007 0.9469 0.0069
-6.000 -0.1653 0.01012 0.00545 -0.1004 0.9399 0.0073
-5.750 -0.1383 0.00971 0.00494 -0.1001 0.9307 0.0076
-5.500 -0.1108 0.00936 0.00449 -0.0998 0.9184 0.0080
-5.250 -0.0839 0.00892 0.00393 -0.0994 0.9028 0.0086
-5.000 -0.0568 0.00862 0.00353 -0.0991 0.8803 0.0095
-4.750 -0.0312 0.00846 0.00318 -0.0983 0.8435 0.0103
-4.250 0.0181 0.00823 0.00259 -0.0965 0.7816 0.0124
-4.000 0.0430 0.00813 0.00237 -0.0957 0.7543 0.0142
-3.750 0.0677 0.00808 0.00217 -0.0949 0.7225 0.0164
-3.500 0.0922 0.00808 0.00206 -0.0940 0.6860 0.0205
-3.250 0.1169 0.00813 0.00196 -0.0932 0.6446 0.0240
-3.000 0.1410 0.00828 0.00191 -0.0923 0.5918 0.0272
-2.750 0.1659 0.00844 0.00187 -0.0916 0.5491 0.0292
-2.500 0.1918 0.00845 0.00178 -0.0910 0.5252 0.0315
-2.250 0.2182 0.00846 0.00172 -0.0906 0.5081 0.0338
-2.000 0.2449 0.00847 0.00168 -0.0903 0.4939 0.0359
-1.750 0.2718 0.00848 0.00163 -0.0899 0.4816 0.0376
-1.500 0.2987 0.00849 0.00158 -0.0896 0.4703 0.0385
-1.250 0.3253 0.00843 0.00145 -0.0892 0.4589 0.0401
-1.000 0.3520 0.00838 0.00135 -0.0888 0.4475 0.0427
-0.750 0.3788 0.00837 0.00130 -0.0885 0.4354 0.0449
-0.500 0.4054 0.00840 0.00126 -0.0881 0.4198 0.0474
-0.250 0.4320 0.00844 0.00123 -0.0877 0.4049 0.0494
0.000 0.4586 0.00849 0.00122 -0.0874 0.3909 0.0508
0.250 0.4852 0.00851 0.00120 -0.0870 0.3786 0.0567
0.500 0.5118 0.00855 0.00120 -0.0866 0.3666 0.0623
0.750 0.5380 0.00856 0.00123 -0.0862 0.3537 0.0876
1.000 0.5639 0.00853 0.00126 -0.0858 0.3409 0.1400
1.250 0.5896 0.00843 0.00134 -0.0854 0.3292 0.2317
1.500 0.6156 0.00839 0.00142 -0.0850 0.3195 0.2969
1.750 0.6411 0.00833 0.00150 -0.0846 0.3084 0.3778
2.000 0.6593 0.00761 0.00167 -0.0829 0.2927 0.7596
2.500 0.7359 0.00785 0.00199 -0.0877 0.2147 1.0000
2.750 0.7588 0.00824 0.00219 -0.0868 0.1797 1.0000
3.000 0.7836 0.00846 0.00232 -0.0861 0.1694 1.0000
3.250 0.8092 0.00860 0.00244 -0.0856 0.1657 1.0000
3.500 0.8347 0.00875 0.00256 -0.0850 0.1625 1.0000
3.750 0.8601 0.00890 0.00269 -0.0845 0.1597 1.0000
4.000 0.8856 0.00906 0.00283 -0.0840 0.1569 1.0000
4.250 0.9111 0.00921 0.00298 -0.0835 0.1545 1.0000
4.500 0.9368 0.00934 0.00311 -0.0830 0.1535 1.0000
4.750 0.9624 0.00947 0.00325 -0.0825 0.1523 1.0000
5.000 0.9880 0.00962 0.00341 -0.0820 0.1508 1.0000
5.250 1.0134 0.00978 0.00358 -0.0815 0.1489 1.0000
5.500 1.0386 0.00995 0.00375 -0.0810 0.1465 1.0000
5.750 1.0637 0.01013 0.00394 -0.0805 0.1444 1.0000
6.000 1.0886 0.01033 0.00415 -0.0799 0.1419 1.0000
6.250 1.1135 0.01052 0.00436 -0.0794 0.1399 1.0000
6.500 1.1388 0.01067 0.00454 -0.0789 0.1388 1.0000
6.750 1.1640 0.01082 0.00473 -0.0784 0.1344 1.0000
7.000 1.1882 0.01107 0.00494 -0.0778 0.1273 1.0000
7.250 1.2124 0.01131 0.00514 -0.0772 0.1162 1.0000
7.500 1.2334 0.01185 0.00549 -0.0761 0.0892 1.0000
7.750 1.2553 0.01229 0.00588 -0.0752 0.0787 1.0000
8.000 1.2785 0.01260 0.00621 -0.0744 0.0726 1.0000
8.250 1.3001 0.01304 0.00662 -0.0734 0.0631 1.0000
8.500 1.3162 0.01398 0.00735 -0.0716 0.0341 1.0000
8.750 1.3327 0.01486 0.00813 -0.0699 0.0158 1.0000
9.000 1.3526 0.01540 0.00867 -0.0686 0.0111 1.0000
9.250 1.3725 0.01592 0.00922 -0.0674 0.0090 1.0000
9.500 1.3928 0.01638 0.00972 -0.0662 0.0079 1.0000
9.750 1.4118 0.01693 0.01030 -0.0649 0.0068 1.0000
10.000 1.4309 0.01744 0.01086 -0.0635 0.0061 1.0000
10.250 1.4496 0.01794 0.01141 -0.0622 0.0056 1.0000
10.500 1.4670 0.01851 0.01202 -0.0606 0.0050 1.0000
10.750 1.4829 0.01916 0.01274 -0.0588 0.0046 1.0000
11.000 1.4978 0.01974 0.01338 -0.0568 0.0043 1.0000
11.250 1.5110 0.02034 0.01404 -0.0546 0.0041 1.0000
11.500 1.5232 0.02098 0.01475 -0.0522 0.0039 1.0000
11.750 1.5349 0.02165 0.01549 -0.0498 0.0037 1.0000
12.000 1.5454 0.02241 0.01632 -0.0474 0.0035 1.0000
12.250 1.5552 0.02323 0.01720 -0.0450 0.0034 1.0000
12.500 1.5618 0.02426 0.01830 -0.0423 0.0031 1.0000
12.750 1.5665 0.02545 0.01960 -0.0396 0.0030 1.0000
13.000 1.5750 0.02642 0.02066 -0.0375 0.0029 1.0000
13.250 1.5819 0.02755 0.02188 -0.0354 0.0028 1.0000
13.500 1.5871 0.02884 0.02326 -0.0333 0.0027 1.0000
13.750 1.5905 0.03034 0.02486 -0.0313 0.0026 1.0000
14.000 1.5916 0.03213 0.02676 -0.0294 0.0025 1.0000
14.250 1.5938 0.03396 0.02868 -0.0280 0.0025 1.0000
14.500 1.5952 0.03599 0.03080 -0.0268 0.0024 1.0000
14.750 1.5944 0.03839 0.03331 -0.0259 0.0023 1.0000
15.000 1.5924 0.04109 0.03611 -0.0254 0.0022 1.0000
15.250 1.5838 0.04480 0.03996 -0.0254 0.0022 1.0000
15.500 1.5792 0.04830 0.04357 -0.0258 0.0021 1.0000
15.750 1.5721 0.05237 0.04777 -0.0267 0.0021 1.0000
16.000 1.5596 0.05754 0.05308 -0.0283 0.0021 1.0000
16.250 1.5480 0.06280 0.05847 -0.0303 0.0021 1.0000
16.500 1.5356 0.06832 0.06412 -0.0324 0.0021 1.0000
16.750 1.5166 0.07504 0.07100 -0.0352 0.0020 1.0000
17.000 1.4945 0.08249 0.07859 -0.0384 0.0020 1.0000
17.250 1.4754 0.08965 0.08588 -0.0416 0.0020 1.0000
17.500 1.4564 0.09699 0.09335 -0.0449 0.0020 1.0000
17.750 1.4338 0.10526 0.10177 -0.0489 0.0020 1.0000
18.000 1.4128 0.11350 0.11013 -0.0530 0.0021 1.0000
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