GOE 381 AIRFOIL (goe381-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 381 AIRFOIL (goe381-il) Reynolds number: 1,000,000 Max Cl/Cd: 111.87 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe381-il-1000000.txt Download as CSV file: xf-goe381-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 381 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.2495 0.08589 0.08441 -0.0313 0.9482 0.0087
-7.000 -0.2363 0.08262 0.08110 -0.0347 0.9359 0.0087
-6.750 -0.2267 0.07818 0.07662 -0.0373 0.9258 0.0089
-6.500 -0.2128 0.07524 0.07365 -0.0395 0.9161 0.0091
-6.250 -0.1955 0.07222 0.07059 -0.0427 0.9065 0.0093
-6.000 -0.1764 0.06911 0.06743 -0.0463 0.8971 0.0095
-5.750 -0.1549 0.06588 0.06415 -0.0502 0.8871 0.0098
-5.500 -0.1315 0.06256 0.06078 -0.0544 0.8778 0.0103
-5.250 -0.1062 0.05913 0.05726 -0.0586 0.8689 0.0110
-5.000 -0.0441 0.03728 0.03537 -0.0629 0.8312 0.0121
-4.750 -0.0187 0.03307 0.03106 -0.0670 0.8224 0.0122
-4.250 0.0157 0.04322 0.04096 -0.0770 0.8301 0.0129
-4.000 0.0421 0.04113 0.03876 -0.0789 0.8171 0.0136
-3.750 0.0719 0.03860 0.03610 -0.0812 0.8019 0.0149
-3.500 0.1126 0.03583 0.03310 -0.0841 0.7866 0.0165
-3.250 0.1436 0.03263 0.02970 -0.0859 0.7699 0.0165
-2.500 0.2275 0.02483 0.02124 -0.0895 0.6912 0.0191
-2.250 0.2592 0.02413 0.02023 -0.0892 0.6505 0.0223
-1.500 0.3468 0.01651 0.01162 -0.0908 0.5807 0.0249
-1.250 0.3739 0.01643 0.01145 -0.0909 0.5656 0.0287
-1.000 0.4031 0.01629 0.01116 -0.0904 0.5517 0.0311
-0.750 0.4320 0.01471 0.00931 -0.0904 0.5399 0.0312
-0.500 0.4607 0.01174 0.00593 -0.0909 0.5305 0.0344
-0.250 0.4886 0.01138 0.00548 -0.0909 0.5213 0.0365
0.000 0.5171 0.00997 0.00375 -0.0906 0.5128 0.0328
0.250 0.5451 0.00970 0.00340 -0.0906 0.5039 0.0322
0.500 0.5728 0.00929 0.00290 -0.0905 0.4953 0.0323
0.750 0.6005 0.00905 0.00260 -0.0905 0.4857 0.0320
1.000 0.6283 0.00872 0.00222 -0.0904 0.4760 0.0322
1.250 0.6560 0.00844 0.00185 -0.0904 0.4655 0.0337
1.500 0.6837 0.00836 0.00171 -0.0904 0.4531 0.0350
1.750 0.7113 0.00835 0.00164 -0.0904 0.4376 0.0358
2.000 0.7386 0.00840 0.00160 -0.0903 0.4158 0.0364
2.250 0.7655 0.00855 0.00161 -0.0902 0.3859 0.0370
2.500 0.7917 0.00882 0.00169 -0.0900 0.3454 0.0385
2.750 0.8178 0.00910 0.00180 -0.0899 0.3101 0.0396
3.000 0.8442 0.00935 0.00191 -0.0897 0.2854 0.0416
3.250 0.8710 0.00949 0.00207 -0.0897 0.2689 0.0843
3.500 0.8978 0.00967 0.00225 -0.0896 0.2566 0.1042
4.000 0.9510 0.01005 0.00255 -0.0894 0.2312 0.1262
4.250 0.9779 0.01017 0.00270 -0.0894 0.2218 0.1554
4.500 1.0006 0.00895 0.00302 -0.0889 0.2108 1.0000
4.750 1.0270 0.00918 0.00318 -0.0888 0.2001 1.0000
5.000 1.0532 0.00945 0.00336 -0.0886 0.1836 1.0000
5.250 1.0759 0.01020 0.00375 -0.0881 0.1282 1.0000
5.500 1.1002 0.01071 0.00414 -0.0878 0.1083 1.0000
5.750 1.1243 0.01123 0.00450 -0.0874 0.0838 1.0000
6.000 1.1445 0.01234 0.00530 -0.0864 0.0157 1.0000
6.250 1.1698 0.01268 0.00570 -0.0861 0.0141 1.0000
6.500 1.1944 0.01310 0.00618 -0.0856 0.0124 1.0000
6.750 1.2182 0.01364 0.00681 -0.0851 0.0110 1.0000
7.000 1.2403 0.01440 0.00769 -0.0842 0.0101 1.0000
7.250 1.2644 0.01483 0.00816 -0.0837 0.0096 1.0000
7.500 1.2877 0.01533 0.00871 -0.0832 0.0088 1.0000
7.750 1.3100 0.01596 0.00939 -0.0825 0.0082 1.0000
8.000 1.3314 0.01667 0.01018 -0.0816 0.0078 1.0000
8.250 1.3516 0.01745 0.01104 -0.0806 0.0074 1.0000
8.500 1.3696 0.01845 0.01211 -0.0794 0.0070 1.0000
8.750 1.3793 0.02019 0.01398 -0.0769 0.0066 1.0000
9.000 1.3849 0.02214 0.01606 -0.0740 0.0063 1.0000
9.250 1.4028 0.02285 0.01684 -0.0727 0.0061 1.0000
9.500 1.4150 0.02400 0.01808 -0.0707 0.0059 1.0000
9.750 1.4243 0.02512 0.01928 -0.0682 0.0057 1.0000
10.000 1.4322 0.02628 0.02051 -0.0656 0.0055 1.0000
10.250 1.4384 0.02763 0.02195 -0.0631 0.0053 1.0000
10.500 1.4420 0.02934 0.02374 -0.0604 0.0052 1.0000
10.750 1.4458 0.03120 0.02569 -0.0580 0.0052 1.0000
11.000 1.4503 0.03312 0.02769 -0.0559 0.0051 1.0000
11.250 1.4554 0.03509 0.02975 -0.0539 0.0050 1.0000
11.500 1.4610 0.03712 0.03189 -0.0521 0.0050 1.0000
11.750 1.4666 0.03929 0.03415 -0.0503 0.0049 1.0000
12.000 1.4712 0.04140 0.03637 -0.0488 0.0048 1.0000
12.250 1.4752 0.04376 0.03883 -0.0473 0.0047 1.0000
12.500 1.4772 0.04605 0.04121 -0.0462 0.0045 1.0000
12.750 1.4790 0.04835 0.04357 -0.0454 0.0044 1.0000
13.000 1.4787 0.05100 0.04631 -0.0447 0.0043 1.0000
13.250 1.4781 0.05396 0.04936 -0.0438 0.0041 1.0000
13.500 1.4762 0.05746 0.05298 -0.0426 0.0041 1.0000
13.750 1.4711 0.06127 0.05696 -0.0419 0.0041 1.0000
14.000 1.4204 0.07686 0.07329 -0.0382 0.0062 1.0000
14.250 1.4039 0.08151 0.07809 -0.0393 0.0062 1.0000
14.500 1.3871 0.08643 0.08316 -0.0410 0.0062 1.0000
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Polar data table (+)
Polar graphs
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