GOE 401 AIRFOIL (goe401-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 401 AIRFOIL (goe401-il) Reynolds number: 1,000,000 Max Cl/Cd: 118.98 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe401-il-1000000-n5.txt Download as CSV file: xf-goe401-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 401 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3584 0.09569 0.09404 -0.0195 1.0000 0.0104
-8.750 -0.3555 0.09294 0.09130 -0.0201 1.0000 0.0108
-8.500 -0.3583 0.08597 0.08434 -0.0251 0.9986 0.0120
-8.250 -0.3430 0.08356 0.08194 -0.0279 0.9931 0.0122
-8.000 -0.3364 0.08103 0.07942 -0.0295 0.9811 0.0123
-7.750 -0.3067 0.07718 0.07554 -0.0369 0.9481 0.0125
-7.500 -0.2396 0.07080 0.06906 -0.0551 0.9278 0.0132
-7.250 -0.1936 0.06072 0.05866 -0.0749 0.8783 0.0150
-7.000 -0.1796 0.05886 0.05662 -0.0762 0.8405 0.0152
-6.750 -0.1673 0.05670 0.05432 -0.0773 0.8114 0.0153
-6.500 -0.1525 0.05470 0.05222 -0.0784 0.7900 0.0155
-6.250 -0.1366 0.05241 0.04983 -0.0798 0.7726 0.0158
-6.000 -0.1197 0.04976 0.04708 -0.0815 0.7571 0.0161
-5.750 -0.1015 0.04699 0.04420 -0.0832 0.7429 0.0166
-5.500 -0.0824 0.04296 0.04003 -0.0856 0.7302 0.0175
-5.250 -0.0641 0.03502 0.03177 -0.0890 0.7195 0.0186
-5.000 -0.0423 0.03337 0.03000 -0.0893 0.7065 0.0188
-4.750 -0.0197 0.03184 0.02835 -0.0895 0.6949 0.0191
-4.500 0.0033 0.03053 0.02694 -0.0895 0.6819 0.0193
-4.250 0.0259 0.02832 0.02456 -0.0895 0.6692 0.0197
-4.000 0.0485 0.02580 0.02183 -0.0893 0.6549 0.0200
-3.750 0.0612 0.01536 0.01045 -0.0876 0.6474 0.0211
-3.500 0.0838 0.01362 0.00831 -0.0867 0.6323 0.0215
-3.250 0.1081 0.01273 0.00716 -0.0859 0.6147 0.0218
-3.000 0.1328 0.01216 0.00636 -0.0852 0.5936 0.0221
-2.750 0.1579 0.01180 0.00580 -0.0845 0.5685 0.0223
-2.500 0.1830 0.01151 0.00533 -0.0839 0.5425 0.0224
-2.250 0.2081 0.01134 0.00497 -0.0832 0.5123 0.0226
-2.000 0.2332 0.01115 0.00460 -0.0825 0.4848 0.0227
-1.750 0.2580 0.01059 0.00386 -0.0819 0.4653 0.0229
-1.500 0.2833 0.01022 0.00337 -0.0813 0.4503 0.0231
-1.250 0.3089 0.00996 0.00303 -0.0807 0.4375 0.0233
-1.000 0.3350 0.00976 0.00276 -0.0802 0.4279 0.0235
-0.750 0.3610 0.00959 0.00255 -0.0797 0.4192 0.0237
-0.500 0.3872 0.00946 0.00237 -0.0792 0.4114 0.0240
-0.250 0.4134 0.00938 0.00226 -0.0788 0.4044 0.0245
0.000 0.4397 0.00925 0.00211 -0.0783 0.3983 0.0247
0.250 0.4658 0.00916 0.00198 -0.0778 0.3920 0.0251
0.500 0.4922 0.00906 0.00187 -0.0774 0.3872 0.0254
0.750 0.5185 0.00899 0.00178 -0.0769 0.3814 0.0259
1.000 0.5447 0.00896 0.00172 -0.0765 0.3759 0.0265
1.250 0.5712 0.00891 0.00167 -0.0761 0.3716 0.0269
1.500 0.5977 0.00889 0.00164 -0.0757 0.3658 0.0274
1.750 0.6240 0.00890 0.00163 -0.0752 0.3603 0.0278
2.000 0.6505 0.00890 0.00162 -0.0749 0.3558 0.0280
2.250 0.6769 0.00889 0.00162 -0.0745 0.3503 0.0284
2.500 0.7030 0.00892 0.00161 -0.0740 0.3443 0.0293
2.750 0.7296 0.00892 0.00163 -0.0736 0.3400 0.0310
3.000 0.7559 0.00896 0.00166 -0.0732 0.3344 0.0328
3.250 0.7820 0.00903 0.00171 -0.0728 0.3261 0.0349
3.500 0.8074 0.00908 0.00179 -0.0723 0.3145 0.0663
3.750 0.8331 0.00913 0.00189 -0.0718 0.3036 0.1032
4.000 0.8587 0.00919 0.00202 -0.0714 0.2960 0.1435
4.250 0.8845 0.00927 0.00214 -0.0709 0.2878 0.1707
4.500 0.9089 0.00921 0.00229 -0.0703 0.2793 0.3097
5.000 1.0021 0.00844 0.00280 -0.0796 0.2487 1.0000
5.250 1.0263 0.00864 0.00296 -0.0788 0.2393 1.0000
5.500 1.0506 0.00883 0.00312 -0.0781 0.2300 1.0000
5.750 1.0738 0.00911 0.00332 -0.0772 0.2143 1.0000
6.000 1.0971 0.00938 0.00353 -0.0764 0.2008 1.0000
6.250 1.1198 0.00971 0.00377 -0.0754 0.1842 1.0000
6.500 1.1415 0.01012 0.00406 -0.0743 0.1623 1.0000
6.750 1.1621 0.01062 0.00442 -0.0731 0.1357 1.0000
7.000 1.1745 0.01184 0.00524 -0.0706 0.0659 1.0000
7.250 1.1962 0.01224 0.00559 -0.0695 0.0570 1.0000
7.500 1.2185 0.01257 0.00592 -0.0685 0.0506 1.0000
7.750 1.2409 0.01288 0.00624 -0.0676 0.0466 1.0000
8.000 1.2626 0.01326 0.00660 -0.0666 0.0419 1.0000
8.250 1.2847 0.01357 0.00692 -0.0656 0.0379 1.0000
8.500 1.3051 0.01403 0.00732 -0.0644 0.0295 1.0000
8.750 1.3233 0.01465 0.00786 -0.0629 0.0178 1.0000
9.000 1.3433 0.01510 0.00831 -0.0616 0.0148 1.0000
9.250 1.3633 0.01554 0.00877 -0.0604 0.0132 1.0000
9.500 1.3824 0.01603 0.00929 -0.0590 0.0117 1.0000
9.750 1.4021 0.01645 0.00975 -0.0577 0.0110 1.0000
10.000 1.4211 0.01690 0.01023 -0.0564 0.0102 1.0000
10.250 1.4390 0.01740 0.01076 -0.0549 0.0095 1.0000
10.500 1.4558 0.01795 0.01135 -0.0532 0.0090 1.0000
10.750 1.4712 0.01855 0.01200 -0.0514 0.0084 1.0000
11.000 1.4873 0.01907 0.01258 -0.0496 0.0081 1.0000
11.250 1.5004 0.01960 0.01316 -0.0473 0.0078 1.0000
11.500 1.5121 0.02017 0.01379 -0.0449 0.0075 1.0000
11.750 1.5232 0.02081 0.01447 -0.0424 0.0071 1.0000
12.000 1.5333 0.02154 0.01525 -0.0400 0.0068 1.0000
12.250 1.5429 0.02233 0.01609 -0.0377 0.0065 1.0000
12.500 1.5502 0.02331 0.01714 -0.0353 0.0062 1.0000
12.750 1.5563 0.02443 0.01834 -0.0331 0.0060 1.0000
13.000 1.5638 0.02555 0.01953 -0.0312 0.0059 1.0000
13.250 1.5707 0.02680 0.02087 -0.0296 0.0058 1.0000
13.500 1.5769 0.02821 0.02236 -0.0282 0.0056 1.0000
13.750 1.5816 0.02984 0.02408 -0.0269 0.0055 1.0000
14.000 1.5858 0.03165 0.02598 -0.0260 0.0053 1.0000
14.250 1.5879 0.03377 0.02820 -0.0252 0.0052 1.0000
14.500 1.5886 0.03619 0.03071 -0.0246 0.0052 1.0000
14.750 1.5893 0.03871 0.03332 -0.0244 0.0051 1.0000
15.000 1.5885 0.04152 0.03623 -0.0243 0.0049 1.0000
15.250 1.5859 0.04467 0.03947 -0.0245 0.0048 1.0000
15.500 1.5798 0.04837 0.04328 -0.0250 0.0048 1.0000
15.750 1.5734 0.05226 0.04728 -0.0257 0.0047 1.0000
16.000 1.5642 0.05666 0.05179 -0.0267 0.0047 1.0000
16.250 1.5523 0.06158 0.05682 -0.0280 0.0046 1.0000
16.500 1.5408 0.06657 0.06191 -0.0294 0.0044 1.0000
16.750 1.5274 0.07190 0.06736 -0.0310 0.0045 1.0000
17.000 1.5151 0.07710 0.07267 -0.0325 0.0045 1.0000
17.250 1.4991 0.08293 0.07861 -0.0344 0.0043 1.0000
17.500 1.4850 0.08847 0.08426 -0.0361 0.0043 1.0000
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