GOE 420 AIRFOIL (goe420-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 420 AIRFOIL (goe420-il) Reynolds number: 100,000 Max Cl/Cd: 32.68 at α=11.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe420-il-100000.txt Download as CSV file: xf-goe420-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 420 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2676 0.12366 0.11884 -0.0561 0.9770 0.1698
-10.000 -0.5954 0.06687 0.06138 -0.0900 0.9591 0.0938
-9.750 -0.6038 0.06216 0.05643 -0.0921 0.9514 0.0934
-9.500 -0.6184 0.05878 0.05285 -0.0908 0.9420 0.0930
-9.250 -0.6196 0.05464 0.04834 -0.0918 0.9349 0.0928
-9.000 -0.6248 0.05176 0.04515 -0.0900 0.9263 0.0926
-8.750 -0.6191 0.04873 0.04173 -0.0897 0.9191 0.0926
-8.500 -0.5986 0.04576 0.03827 -0.0912 0.9150 0.0931
-8.250 -0.6043 0.04440 0.03666 -0.0872 0.9061 0.0934
-8.000 -0.5852 0.04238 0.03426 -0.0872 0.9004 0.0943
-7.750 -0.5484 0.04088 0.03280 -0.0896 0.8968 0.0968
-7.500 -0.5443 0.04023 0.03208 -0.0865 0.8890 0.0982
-7.250 -0.5238 0.03917 0.03084 -0.0860 0.8830 0.1005
-7.000 -0.4905 0.03779 0.02912 -0.0874 0.8788 0.1034
-6.750 -0.4693 0.03686 0.02820 -0.0868 0.8730 0.1058
-6.500 -0.4558 0.03633 0.02770 -0.0849 0.8652 0.1084
-6.250 -0.4188 0.03533 0.02651 -0.0865 0.8601 0.1140
-6.000 -0.3723 0.03430 0.02560 -0.0897 0.8565 0.1224
-5.750 -0.3751 0.03415 0.02529 -0.0849 0.8447 0.1268
-5.500 -0.3360 0.03312 0.02434 -0.0868 0.8400 0.1395
-5.250 -0.2920 0.03183 0.02331 -0.0895 0.8370 0.1624
-5.000 -0.3037 0.03191 0.02346 -0.0837 0.8251 0.1733
-4.750 -0.2697 0.03100 0.02284 -0.0848 0.8205 0.2190
-4.500 -0.2252 0.03080 0.02277 -0.0874 0.8175 0.2655
-4.250 -0.2345 0.03143 0.02344 -0.0818 0.8052 0.2777
-4.000 -0.1958 0.03140 0.02333 -0.0833 0.8008 0.3086
-3.750 -0.1496 0.03135 0.02337 -0.0857 0.7980 0.3364
-3.500 -0.1590 0.03207 0.02402 -0.0803 0.7851 0.3479
-3.250 -0.1181 0.03193 0.02396 -0.0818 0.7810 0.3719
-3.000 -0.1074 0.03241 0.02440 -0.0792 0.7714 0.3886
-2.750 -0.0784 0.03245 0.02449 -0.0789 0.7648 0.4096
-2.500 -0.0360 0.03214 0.02422 -0.0805 0.7614 0.4319
-2.250 -0.0322 0.03276 0.02485 -0.0770 0.7501 0.4432
-2.000 0.0038 0.03235 0.02443 -0.0777 0.7449 0.4591
-1.750 0.0506 0.03162 0.02364 -0.0800 0.7421 0.4764
-1.500 0.0523 0.03228 0.02427 -0.0763 0.7293 0.4858
-1.250 0.0931 0.03162 0.02361 -0.0776 0.7253 0.5005
-1.000 0.1416 0.03076 0.02270 -0.0800 0.7233 0.5171
-0.750 0.1372 0.03172 0.02369 -0.0756 0.7093 0.5256
-0.500 0.1812 0.03091 0.02287 -0.0773 0.7064 0.5412
-0.250 0.2320 0.02993 0.02188 -0.0799 0.7047 0.5601
0.000 0.2257 0.03095 0.02293 -0.0751 0.6902 0.5713
0.250 0.2719 0.03003 0.02204 -0.0769 0.6879 0.5930
0.500 0.3226 0.02910 0.02112 -0.0795 0.6861 0.6158
0.750 0.3729 0.02817 0.02021 -0.0821 0.6844 0.6383
1.000 0.3566 0.02946 0.02161 -0.0758 0.6694 0.6499
1.250 0.4080 0.02845 0.02062 -0.0786 0.6675 0.6793
1.500 0.4580 0.02731 0.01956 -0.0809 0.6657 0.7124
1.750 0.4383 0.02870 0.02110 -0.0741 0.6510 0.7360
2.000 0.4862 0.02764 0.02025 -0.0758 0.6489 0.7867
2.250 0.5386 0.02665 0.01947 -0.0780 0.6471 0.8700
2.500 0.5941 0.02784 0.02079 -0.0850 0.6351 0.9842
2.750 0.6501 0.02712 0.01983 -0.0899 0.6316 1.0000
3.000 0.7017 0.02638 0.01889 -0.0933 0.6289 1.0000
3.250 0.6628 0.02875 0.02125 -0.0842 0.6156 1.0000
3.500 0.7109 0.02811 0.02047 -0.0869 0.6124 1.0000
3.750 0.7661 0.02731 0.01953 -0.0906 0.6098 1.0000
4.000 0.7157 0.03028 0.02255 -0.0800 0.5962 1.0000
4.250 0.7699 0.02946 0.02162 -0.0834 0.5934 1.0000
4.500 0.8302 0.02843 0.02046 -0.0876 0.5909 1.0000
4.750 0.7629 0.03214 0.02426 -0.0751 0.5769 1.0000
5.000 0.8283 0.03076 0.02278 -0.0797 0.5746 1.0000
5.250 0.8962 0.02944 0.02134 -0.0849 0.5722 1.0000
5.500 0.8114 0.03405 0.02606 -0.0706 0.5578 1.0000
5.750 0.8782 0.03240 0.02434 -0.0750 0.5559 1.0000
6.000 0.9544 0.03082 0.02266 -0.0812 0.5537 1.0000
6.250 0.8497 0.03678 0.02875 -0.0656 0.5385 1.0000
6.500 0.9185 0.03469 0.02661 -0.0695 0.5372 1.0000
6.750 1.0008 0.03264 0.02447 -0.0760 0.5354 1.0000
7.000 0.8326 0.04399 0.03599 -0.0575 0.5134 1.0000
7.250 0.9024 0.04084 0.03281 -0.0599 0.5140 1.0000
7.500 0.9957 0.03697 0.02888 -0.0653 0.5148 1.0000
7.750 0.9237 0.04321 0.03520 -0.0569 0.5003 1.0000
8.000 0.9991 0.03994 0.03190 -0.0600 0.5000 1.0000
8.250 1.0866 0.03689 0.02880 -0.0656 0.4990 1.0000
8.500 0.9669 0.04620 0.03824 -0.0534 0.4817 1.0000
8.750 1.0391 0.04294 0.03496 -0.0559 0.4813 1.0000
9.000 1.1375 0.03890 0.03087 -0.0618 0.4807 1.0000
9.250 1.0125 0.04906 0.04117 -0.0502 0.4630 1.0000
9.500 1.0931 0.04493 0.03702 -0.0529 0.4630 1.0000
9.750 1.1955 0.04066 0.03272 -0.0589 0.4623 1.0000
10.000 1.0496 0.05289 0.04509 -0.0469 0.4438 1.0000
10.250 1.1327 0.04820 0.04040 -0.0493 0.4437 1.0000
11.250 1.1482 0.05379 0.04613 -0.0420 0.4091 1.0000
11.500 1.3398 0.04100 0.03308 -0.0511 0.4055 1.0000
11.750 0.8347 0.09869 0.09120 -0.0430 0.3573 1.0000
12.000 0.8951 0.09348 0.08600 -0.0410 0.3552 1.0000
12.250 0.9628 0.08680 0.07936 -0.0388 0.3544 1.0000
12.500 1.0285 0.07993 0.07252 -0.0366 0.3542 1.0000
12.750 1.1065 0.07174 0.06436 -0.0346 0.3548 1.0000
13.000 1.2463 0.05791 0.05051 -0.0343 0.3569 1.0000
13.250 1.3818 0.04814 0.04056 -0.0378 0.3523 1.0000
13.500 1.2062 0.06646 0.05920 -0.0319 0.3388 1.0000
13.750 1.4097 0.04895 0.04140 -0.0354 0.3362 1.0000
14.000 1.1544 0.07780 0.07067 -0.0312 0.3183 1.0000
14.250 1.2498 0.06795 0.06083 -0.0294 0.3168 1.0000
14.500 1.2245 0.07322 0.06619 -0.0291 0.3062 1.0000
14.750 1.3696 0.05876 0.05152 -0.0282 0.3011 1.0000
15.000 1.3321 0.06460 0.05751 -0.0270 0.2909 1.0000
15.250 1.3264 0.06733 0.06028 -0.0262 0.2804 1.0000
15.500 1.3803 0.06326 0.05602 -0.0253 0.2685 1.0000
15.750 1.3982 0.06337 0.05601 -0.0245 0.2556 1.0000
16.000 1.3725 0.06848 0.06123 -0.0239 0.2438 1.0000
16.250 1.3722 0.07092 0.06363 -0.0234 0.2317 1.0000
16.500 1.3852 0.07191 0.06447 -0.0227 0.2200 1.0000
16.750 1.3999 0.07277 0.06518 -0.0221 0.2094 1.0000
17.000 1.3794 0.07801 0.07058 -0.0223 0.2014 1.0000
17.250 1.4128 0.07679 0.06910 -0.0214 0.1930 1.0000
17.500 1.3827 0.08338 0.07599 -0.0222 0.1874 1.0000
17.750 1.3994 0.08423 0.07675 -0.0218 0.1815 1.0000
18.000 1.4054 0.08658 0.07913 -0.0218 0.1768 1.0000
18.250 1.3791 0.09315 0.08597 -0.0231 0.1731 1.0000
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