GOE 389 AIRFOIL (goe389-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 389 AIRFOIL (goe389-il) Reynolds number: 1,000,000 Max Cl/Cd: 108.06 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe389-il-1000000-n5.txt Download as CSV file: xf-goe389-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 389 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.9235 0.03616 0.03396 -0.0812 1.0000 0.0064
-12.750 -0.9398 0.02981 0.02719 -0.0816 1.0000 0.0065
-12.500 -0.9348 0.02699 0.02413 -0.0806 1.0000 0.0066
-12.250 -0.9112 0.02454 0.02144 -0.0825 0.9979 0.0069
-12.000 -0.8854 0.02269 0.01936 -0.0841 0.9957 0.0071
-11.750 -0.8587 0.02120 0.01769 -0.0854 0.9937 0.0074
-11.500 -0.8331 0.01971 0.01603 -0.0863 0.9903 0.0079
-11.250 -0.8054 0.01848 0.01466 -0.0874 0.9874 0.0085
-11.000 -0.7766 0.01746 0.01352 -0.0884 0.9850 0.0091
-10.750 -0.7503 0.01661 0.01256 -0.0887 0.9797 0.0097
-10.250 -0.6924 0.01525 0.01104 -0.0901 0.9700 0.0116
-10.000 -0.6618 0.01473 0.01046 -0.0910 0.9643 0.0127
-9.750 -0.6316 0.01424 0.00990 -0.0917 0.9562 0.0137
-9.500 -0.5996 0.01414 0.00983 -0.0927 0.9474 0.0148
-9.250 -0.5689 0.01403 0.00967 -0.0933 0.9357 0.0157
-8.750 -0.5138 0.01358 0.00903 -0.0932 0.9092 0.0174
-8.500 -0.4869 0.01340 0.00875 -0.0930 0.8976 0.0178
-8.250 -0.4605 0.01308 0.00834 -0.0928 0.8873 0.0184
-8.000 -0.4335 0.01293 0.00814 -0.0926 0.8766 0.0190
-7.750 -0.4062 0.01284 0.00800 -0.0925 0.8652 0.0195
-7.500 -0.3789 0.01277 0.00788 -0.0923 0.8521 0.0200
-7.250 -0.3518 0.01270 0.00774 -0.0921 0.8363 0.0207
-7.000 -0.3252 0.01253 0.00746 -0.0919 0.8160 0.0213
-6.750 -0.2988 0.01237 0.00716 -0.0916 0.7914 0.0219
-6.500 -0.2723 0.01219 0.00683 -0.0913 0.7710 0.0225
-6.250 -0.2453 0.01202 0.00655 -0.0911 0.7559 0.0230
-6.000 -0.2183 0.01183 0.00625 -0.0909 0.7431 0.0234
-5.750 -0.1910 0.01161 0.00593 -0.0908 0.7324 0.0237
-5.500 -0.1634 0.01144 0.00569 -0.0907 0.7234 0.0240
-5.250 -0.1360 0.01117 0.00532 -0.0906 0.7155 0.0241
-5.000 -0.1084 0.01089 0.00498 -0.0906 0.7093 0.0242
-4.750 -0.0814 0.01035 0.00433 -0.0905 0.7028 0.0246
-4.500 -0.0544 0.00980 0.00368 -0.0904 0.6969 0.0255
-4.250 -0.0266 0.00948 0.00331 -0.0904 0.6911 0.0263
-4.000 0.0012 0.00926 0.00303 -0.0903 0.6851 0.0268
-3.750 0.0293 0.00906 0.00279 -0.0903 0.6789 0.0273
-3.500 0.0573 0.00890 0.00258 -0.0903 0.6708 0.0278
-3.250 0.0854 0.00874 0.00238 -0.0903 0.6629 0.0282
-3.000 0.1134 0.00862 0.00220 -0.0903 0.6539 0.0286
-2.750 0.1415 0.00850 0.00203 -0.0903 0.6423 0.0290
-2.500 0.1694 0.00841 0.00188 -0.0902 0.6262 0.0294
-2.250 0.1969 0.00838 0.00174 -0.0901 0.5998 0.0297
-2.000 0.2228 0.00851 0.00164 -0.0897 0.5480 0.0300
-1.750 0.2492 0.00864 0.00158 -0.0894 0.5082 0.0304
-1.500 0.2763 0.00871 0.00153 -0.0893 0.4833 0.0308
-1.250 0.3039 0.00873 0.00147 -0.0892 0.4676 0.0314
-1.000 0.3317 0.00875 0.00143 -0.0892 0.4556 0.0321
-0.750 0.3595 0.00877 0.00140 -0.0891 0.4442 0.0327
-0.500 0.3875 0.00877 0.00136 -0.0891 0.4347 0.0354
-0.250 0.4154 0.00876 0.00135 -0.0891 0.4268 0.0427
0.000 0.4432 0.00870 0.00136 -0.0891 0.4191 0.0705
0.250 0.4711 0.00870 0.00136 -0.0891 0.4119 0.0836
0.500 0.4989 0.00857 0.00137 -0.0892 0.4057 0.1419
0.750 0.5265 0.00853 0.00141 -0.0892 0.3981 0.1831
1.000 0.5542 0.00844 0.00145 -0.0893 0.3902 0.2427
1.250 0.5818 0.00840 0.00151 -0.0893 0.3838 0.2931
1.500 0.6097 0.00837 0.00156 -0.0894 0.3785 0.3296
1.750 0.6373 0.00830 0.00163 -0.0894 0.3720 0.3905
2.000 0.6639 0.00794 0.00175 -0.0894 0.3668 0.5839
2.250 0.6912 0.00706 0.00188 -0.0892 0.3618 1.0000
2.500 0.7183 0.00719 0.00195 -0.0891 0.3529 1.0000
2.750 0.7455 0.00732 0.00203 -0.0890 0.3417 1.0000
3.000 0.7728 0.00745 0.00211 -0.0889 0.3336 1.0000
3.250 0.8000 0.00758 0.00220 -0.0887 0.3258 1.0000
3.500 0.8271 0.00772 0.00230 -0.0886 0.3160 1.0000
3.750 0.8537 0.00790 0.00241 -0.0885 0.3028 1.0000
4.000 0.8794 0.00819 0.00257 -0.0882 0.2793 1.0000
4.250 0.9043 0.00855 0.00277 -0.0877 0.2500 1.0000
4.500 0.9286 0.00897 0.00302 -0.0873 0.2180 1.0000
4.750 0.9474 0.00998 0.00359 -0.0860 0.1343 1.0000
5.000 0.9716 0.01042 0.00391 -0.0854 0.1124 1.0000
5.250 0.9971 0.01070 0.00415 -0.0851 0.1026 1.0000
5.500 1.0227 0.01098 0.00438 -0.0848 0.0945 1.0000
5.750 1.0451 0.01158 0.00477 -0.0841 0.0589 1.0000
6.000 1.0695 0.01196 0.00511 -0.0836 0.0458 1.0000
6.250 1.0909 0.01265 0.00564 -0.0827 0.0173 1.0000
6.500 1.1156 0.01297 0.00597 -0.0822 0.0133 1.0000
6.750 1.1401 0.01330 0.00631 -0.0818 0.0118 1.0000
7.000 1.1640 0.01367 0.00672 -0.0812 0.0101 1.0000
7.250 1.1883 0.01400 0.00707 -0.0807 0.0094 1.0000
7.500 1.2121 0.01434 0.00744 -0.0802 0.0088 1.0000
7.750 1.2355 0.01472 0.00784 -0.0796 0.0082 1.0000
8.000 1.2582 0.01514 0.00828 -0.0788 0.0076 1.0000
8.250 1.2794 0.01567 0.00886 -0.0779 0.0070 1.0000
8.500 1.3019 0.01606 0.00928 -0.0772 0.0067 1.0000
8.750 1.3237 0.01649 0.00974 -0.0764 0.0063 1.0000
9.000 1.3448 0.01696 0.01024 -0.0755 0.0060 1.0000
9.250 1.3652 0.01746 0.01077 -0.0744 0.0057 1.0000
9.500 1.3847 0.01798 0.01133 -0.0733 0.0054 1.0000
9.750 1.4028 0.01858 0.01197 -0.0720 0.0051 1.0000
10.000 1.4174 0.01937 0.01282 -0.0701 0.0049 1.0000
10.250 1.4317 0.01999 0.01349 -0.0681 0.0048 1.0000
10.500 1.4454 0.02066 0.01422 -0.0661 0.0046 1.0000
10.750 1.4580 0.02140 0.01502 -0.0640 0.0045 1.0000
11.000 1.4699 0.02220 0.01589 -0.0620 0.0044 1.0000
11.250 1.4813 0.02307 0.01683 -0.0600 0.0042 1.0000
11.500 1.4921 0.02400 0.01783 -0.0582 0.0041 1.0000
11.750 1.5027 0.02500 0.01889 -0.0565 0.0039 1.0000
12.000 1.5128 0.02609 0.02003 -0.0548 0.0038 1.0000
12.250 1.5215 0.02733 0.02133 -0.0533 0.0037 1.0000
12.500 1.5296 0.02868 0.02275 -0.0518 0.0036 1.0000
12.750 1.5355 0.03028 0.02442 -0.0503 0.0035 1.0000
13.000 1.5398 0.03212 0.02635 -0.0490 0.0034 1.0000
13.250 1.5410 0.03435 0.02867 -0.0478 0.0033 1.0000
13.500 1.5382 0.03714 0.03157 -0.0467 0.0032 1.0000
13.750 1.5376 0.03985 0.03438 -0.0461 0.0032 1.0000
14.000 1.5379 0.04252 0.03717 -0.0456 0.0032 1.0000
14.250 1.5366 0.04549 0.04024 -0.0453 0.0031 1.0000
14.500 1.5334 0.04873 0.04359 -0.0451 0.0031 1.0000
14.750 1.5293 0.05221 0.04717 -0.0451 0.0031 1.0000
15.000 1.5238 0.05604 0.05111 -0.0455 0.0031 1.0000
15.250 1.5176 0.06010 0.05528 -0.0460 0.0030 1.0000
15.500 1.5101 0.06449 0.05979 -0.0469 0.0030 1.0000
15.750 1.5014 0.06919 0.06460 -0.0479 0.0030 1.0000
16.000 1.4932 0.07390 0.06942 -0.0490 0.0029 1.0000
16.250 1.4841 0.07878 0.07442 -0.0503 0.0029 1.0000
16.500 1.4734 0.08397 0.07971 -0.0517 0.0029 1.0000
16.750 1.4630 0.08917 0.08502 -0.0532 0.0029 1.0000
17.000 1.4517 0.09451 0.09046 -0.0547 0.0028 1.0000
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Polar data table (+)
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