GOE 402 AIRFOIL (goe402-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 402 AIRFOIL (goe402-il) Reynolds number: 1,000,000 Max Cl/Cd: 129.24 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe402-il-1000000.txt Download as CSV file: xf-goe402-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 402 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2910 0.09334 0.09184 -0.0196 1.0000 0.0092
-7.750 -0.2898 0.09099 0.08952 -0.0197 1.0000 0.0093
-7.500 -0.2883 0.08821 0.08677 -0.0218 0.9989 0.0094
-7.250 -0.2664 0.08374 0.08230 -0.0286 0.9909 0.0094
-7.000 -0.2492 0.07881 0.07737 -0.0329 0.9815 0.0097
-6.750 -0.2198 0.07479 0.07332 -0.0398 0.9665 0.0099
-6.500 -0.1627 0.06912 0.06757 -0.0543 0.9421 0.0105
-6.250 -0.1218 0.06480 0.06282 -0.0641 0.8360 0.0113
-6.000 -0.1080 0.06207 0.05985 -0.0667 0.7870 0.0124
-5.750 -0.0890 0.05893 0.05657 -0.0706 0.7650 0.0125
-5.500 -0.0691 0.05565 0.05317 -0.0738 0.7480 0.0126
-5.250 -0.0483 0.05238 0.04979 -0.0764 0.7342 0.0126
-5.000 -0.0261 0.04895 0.04624 -0.0789 0.7227 0.0126
-4.750 -0.0087 0.04474 0.04195 -0.0809 0.7128 0.0130
-4.500 0.0126 0.04269 0.03984 -0.0820 0.7039 0.0133
-4.250 0.0365 0.04050 0.03755 -0.0834 0.6951 0.0140
-4.000 0.0727 0.03711 0.03397 -0.0862 0.6870 0.0163
-3.750 0.1002 0.03392 0.03061 -0.0875 0.6786 0.0164
-3.500 0.1277 0.03071 0.02723 -0.0885 0.6699 0.0165
-3.250 0.1494 0.02754 0.02391 -0.0895 0.6614 0.0173
-3.000 0.1748 0.02594 0.02219 -0.0898 0.6518 0.0179
-2.750 0.2073 0.02420 0.02023 -0.0895 0.6430 0.0211
-2.250 0.2587 0.01754 0.01297 -0.0895 0.6249 0.0196
-2.000 0.2863 0.01394 0.00877 -0.0886 0.6161 0.0219
-1.750 0.3117 0.01596 0.01108 -0.0891 0.6026 0.0251
-1.500 0.3388 0.01386 0.00860 -0.0884 0.5914 0.0248
-1.250 0.3663 0.01304 0.00754 -0.0878 0.5789 0.0267
-1.000 0.3926 0.01212 0.00643 -0.0876 0.5661 0.0299
-0.750 0.4190 0.01183 0.00604 -0.0874 0.5511 0.0318
-0.500 0.4460 0.01120 0.00524 -0.0869 0.5385 0.0328
-0.250 0.4731 0.01080 0.00470 -0.0866 0.5269 0.0345
0.000 0.4999 0.01011 0.00386 -0.0861 0.5152 0.0339
0.250 0.5266 0.00963 0.00327 -0.0857 0.5024 0.0335
0.500 0.5533 0.00933 0.00288 -0.0853 0.4883 0.0340
0.750 0.5799 0.00913 0.00259 -0.0850 0.4734 0.0348
1.000 0.6064 0.00897 0.00237 -0.0846 0.4573 0.0356
1.250 0.6328 0.00891 0.00223 -0.0843 0.4383 0.0362
1.500 0.6589 0.00893 0.00215 -0.0839 0.4157 0.0365
1.750 0.6848 0.00896 0.00208 -0.0835 0.3920 0.0368
2.000 0.7102 0.00882 0.00184 -0.0830 0.3739 0.0377
2.250 0.7362 0.00878 0.00173 -0.0827 0.3594 0.0394
2.500 0.7626 0.00882 0.00171 -0.0823 0.3476 0.0414
2.750 0.7892 0.00887 0.00173 -0.0821 0.3387 0.0438
3.000 0.8156 0.00896 0.00179 -0.0818 0.3310 0.0461
3.250 0.8424 0.00901 0.00184 -0.0816 0.3257 0.0480
3.500 0.8686 0.00895 0.00194 -0.0813 0.3201 0.1740
3.750 0.9006 0.00758 0.00222 -0.0828 0.3151 1.0000
4.000 0.9272 0.00769 0.00232 -0.0825 0.3110 1.0000
4.250 0.9534 0.00783 0.00244 -0.0822 0.3063 1.0000
4.500 0.9794 0.00800 0.00257 -0.0819 0.3014 1.0000
4.750 1.0060 0.00810 0.00268 -0.0817 0.2978 1.0000
5.000 1.0322 0.00823 0.00282 -0.0814 0.2937 1.0000
5.250 1.0581 0.00840 0.00297 -0.0810 0.2895 1.0000
5.500 1.0844 0.00853 0.00312 -0.0808 0.2853 1.0000
5.750 1.1105 0.00867 0.00324 -0.0805 0.2778 1.0000
6.000 1.1363 0.00884 0.00341 -0.0802 0.2703 1.0000
6.250 1.1619 0.00903 0.00357 -0.0799 0.2606 1.0000
6.500 1.1877 0.00919 0.00373 -0.0796 0.2522 1.0000
6.750 1.2128 0.00942 0.00392 -0.0792 0.2379 1.0000
7.000 1.2365 0.00978 0.00418 -0.0786 0.2139 1.0000
7.250 1.2554 0.01065 0.00472 -0.0774 0.1562 1.0000
7.500 1.2745 0.01148 0.00534 -0.0762 0.1216 1.0000
7.750 1.2970 0.01195 0.00577 -0.0754 0.1084 1.0000
8.000 1.3184 0.01252 0.00624 -0.0746 0.0875 1.0000
8.250 1.3286 0.01422 0.00749 -0.0721 0.0210 1.0000
8.500 1.3491 0.01484 0.00812 -0.0710 0.0152 1.0000
8.750 1.3689 0.01550 0.00882 -0.0698 0.0128 1.0000
9.000 1.3891 0.01608 0.00948 -0.0687 0.0116 1.0000
9.250 1.4095 0.01661 0.01008 -0.0677 0.0107 1.0000
9.500 1.4284 0.01724 0.01077 -0.0665 0.0098 1.0000
9.750 1.4445 0.01807 0.01167 -0.0648 0.0090 1.0000
10.000 1.4549 0.01929 0.01303 -0.0623 0.0083 1.0000
10.250 1.4709 0.01997 0.01379 -0.0607 0.0081 1.0000
10.500 1.4845 0.02076 0.01466 -0.0588 0.0078 1.0000
10.750 1.4953 0.02153 0.01551 -0.0563 0.0074 1.0000
11.000 1.5018 0.02240 0.01645 -0.0533 0.0071 1.0000
11.250 1.5081 0.02332 0.01745 -0.0504 0.0069 1.0000
11.500 1.5142 0.02431 0.01850 -0.0478 0.0066 1.0000
11.750 1.5174 0.02555 0.01981 -0.0452 0.0063 1.0000
12.000 1.5138 0.02738 0.02174 -0.0424 0.0060 1.0000
12.250 1.5061 0.02983 0.02431 -0.0400 0.0059 1.0000
12.500 1.4903 0.03349 0.02813 -0.0383 0.0057 1.0000
12.750 1.4836 0.03667 0.03144 -0.0376 0.0056 1.0000
13.000 1.4847 0.03923 0.03410 -0.0373 0.0055 1.0000
13.250 1.4819 0.04231 0.03730 -0.0372 0.0054 1.0000
13.500 1.4807 0.04533 0.04042 -0.0373 0.0054 1.0000
13.750 1.4782 0.04861 0.04380 -0.0375 0.0052 1.0000
14.000 1.4738 0.05222 0.04751 -0.0380 0.0051 1.0000
14.250 1.4695 0.05591 0.05131 -0.0386 0.0051 1.0000
14.500 1.4592 0.06045 0.05596 -0.0393 0.0050 1.0000
14.750 1.4554 0.06432 0.05993 -0.0403 0.0049 1.0000
15.000 1.4493 0.06857 0.06429 -0.0414 0.0049 1.0000
15.250 1.4436 0.07293 0.06875 -0.0426 0.0048 1.0000
15.500 1.4374 0.07750 0.07343 -0.0440 0.0047 1.0000
15.750 1.4316 0.08210 0.07813 -0.0455 0.0047 1.0000
16.000 1.4268 0.08669 0.08282 -0.0472 0.0046 1.0000
16.250 1.4199 0.09161 0.08786 -0.0489 0.0046 1.0000
16.500 1.4149 0.09647 0.09281 -0.0509 0.0045 1.0000
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Polar data table (+)
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