GOE 379 AIRFOIL (goe379-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 379 AIRFOIL (goe379-il) Reynolds number: 200,000 Max Cl/Cd: 79.12 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe379-il-200000-n5.txt Download as CSV file: xf-goe379-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 379 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2726 0.09589 0.09266 -0.0272 1.0000 0.0164
-7.500 -0.2737 0.09390 0.09073 -0.0265 1.0000 0.0165
-7.250 -0.2804 0.09280 0.08972 -0.0251 1.0000 0.0173
-7.000 -0.2661 0.08977 0.08672 -0.0297 0.9916 0.0177
-6.750 -0.2380 0.08621 0.08315 -0.0392 0.9805 0.0181
-6.500 -0.2126 0.08229 0.07920 -0.0461 0.9712 0.0182
-6.250 -0.1847 0.07813 0.07501 -0.0530 0.9626 0.0183
-6.000 -0.1556 0.07387 0.07071 -0.0593 0.9549 0.0184
-5.750 -0.1286 0.06976 0.06655 -0.0646 0.9450 0.0184
-5.500 -0.0994 0.06557 0.06229 -0.0700 0.9360 0.0185
-5.250 -0.0502 0.04004 0.03693 -0.0699 0.8913 0.0202
-5.000 -0.0344 0.03690 0.03374 -0.0712 0.8800 0.0219
-4.750 -0.0158 0.03352 0.03027 -0.0737 0.8687 0.0228
-4.500 0.0042 0.03005 0.02669 -0.0762 0.8579 0.0230
-4.000 0.0529 0.04183 0.03792 -0.0889 0.8721 0.0163
-3.750 0.0787 0.03848 0.03439 -0.0905 0.8605 0.0150
-3.500 0.1056 0.03517 0.03087 -0.0917 0.8494 0.0142
-3.250 0.1328 0.03184 0.02725 -0.0924 0.8384 0.0135
-3.000 0.1595 0.02853 0.02363 -0.0926 0.8263 0.0132
-2.750 0.1858 0.02523 0.01995 -0.0921 0.8136 0.0130
-2.500 0.2115 0.02231 0.01661 -0.0913 0.8000 0.0144
-2.250 0.2369 0.01887 0.01261 -0.0900 0.7872 0.0156
-2.000 0.2624 0.01581 0.00885 -0.0886 0.7748 0.0163
-1.750 0.2885 0.01407 0.00660 -0.0877 0.7629 0.0176
-1.500 0.3143 0.01309 0.00537 -0.0869 0.7510 0.0217
-1.250 0.3402 0.01247 0.00454 -0.0862 0.7388 0.0274
-1.000 0.3663 0.01224 0.00423 -0.0856 0.7261 0.0406
-0.750 0.3923 0.01217 0.00403 -0.0851 0.7129 0.0543
-0.500 0.4183 0.01216 0.00389 -0.0846 0.6996 0.0668
-0.250 0.4437 0.01195 0.00354 -0.0839 0.6862 0.0722
0.000 0.4689 0.01176 0.00323 -0.0833 0.6723 0.0768
0.250 0.4940 0.01164 0.00303 -0.0826 0.6578 0.0840
0.500 0.5191 0.01154 0.00285 -0.0820 0.6432 0.0916
0.750 0.5441 0.01147 0.00270 -0.0814 0.6290 0.1006
1.000 0.5690 0.01141 0.00259 -0.0807 0.6149 0.1144
1.250 0.5936 0.01134 0.00255 -0.0801 0.6006 0.1477
1.750 0.6961 0.00991 0.00257 -0.0910 0.5673 1.0000
2.000 0.7205 0.01008 0.00262 -0.0903 0.5545 1.0000
2.250 0.7448 0.01027 0.00268 -0.0896 0.5420 1.0000
2.750 0.7929 0.01067 0.00289 -0.0881 0.5145 1.0000
3.000 0.8167 0.01088 0.00302 -0.0873 0.4998 1.0000
3.500 0.8643 0.01130 0.00335 -0.0858 0.4722 1.0000
3.750 0.8881 0.01152 0.00353 -0.0850 0.4586 1.0000
4.000 0.9117 0.01174 0.00373 -0.0843 0.4452 1.0000
4.250 0.9353 0.01197 0.00398 -0.0835 0.4326 1.0000
4.500 0.9587 0.01221 0.00422 -0.0827 0.4200 1.0000
4.750 0.9821 0.01247 0.00448 -0.0819 0.4088 1.0000
5.000 1.0052 0.01274 0.00476 -0.0811 0.3984 1.0000
5.250 1.0285 0.01300 0.00510 -0.0803 0.3877 1.0000
5.500 1.0512 0.01329 0.00544 -0.0794 0.3750 1.0000
5.750 1.0705 0.01374 0.00576 -0.0780 0.3440 1.0000
6.000 1.0894 0.01424 0.00615 -0.0766 0.3118 1.0000
6.250 1.1055 0.01497 0.00661 -0.0747 0.2507 1.0000
6.500 1.1106 0.01679 0.00768 -0.0715 0.1306 1.0000
6.750 1.1108 0.01919 0.00938 -0.0675 0.0177 1.0000
7.000 1.1284 0.01993 0.01033 -0.0658 0.0145 1.0000
7.250 1.1437 0.02085 0.01142 -0.0637 0.0118 1.0000
7.500 1.1538 0.02216 0.01301 -0.0609 0.0102 1.0000
7.750 1.1646 0.02328 0.01431 -0.0583 0.0097 1.0000
8.000 1.1727 0.02447 0.01567 -0.0554 0.0093 1.0000
8.250 1.1778 0.02566 0.01697 -0.0520 0.0087 1.0000
8.500 1.1827 0.02680 0.01821 -0.0488 0.0078 1.0000
8.750 1.1853 0.02820 0.01976 -0.0456 0.0074 1.0000
9.000 1.1858 0.02988 0.02153 -0.0424 0.0069 1.0000
9.250 1.1865 0.03175 0.02347 -0.0396 0.0067 1.0000
9.500 1.1882 0.03378 0.02556 -0.0371 0.0065 1.0000
9.750 1.1925 0.03609 0.02791 -0.0348 0.0064 1.0000
10.000 1.2050 0.03845 0.03031 -0.0330 0.0062 1.0000
10.250 1.2187 0.04046 0.03247 -0.0314 0.0061 1.0000
10.500 1.2341 0.04275 0.03493 -0.0301 0.0061 1.0000
10.750 1.2433 0.04505 0.03750 -0.0283 0.0059 1.0000
11.000 1.2506 0.04749 0.04018 -0.0267 0.0058 1.0000
11.250 1.2519 0.04969 0.04266 -0.0249 0.0053 1.0000
11.500 1.2529 0.05237 0.04558 -0.0234 0.0050 1.0000
11.750 1.2513 0.05519 0.04861 -0.0222 0.0047 1.0000
12.000 1.2474 0.05854 0.05220 -0.0211 0.0046 1.0000
12.250 1.2424 0.06210 0.05601 -0.0203 0.0047 1.0000
12.500 1.2340 0.06608 0.06024 -0.0199 0.0048 1.0000
12.750 1.2237 0.07033 0.06472 -0.0199 0.0047 1.0000
13.000 1.2117 0.07489 0.06950 -0.0205 0.0047 1.0000
13.250 1.1990 0.07980 0.07463 -0.0216 0.0047 1.0000
13.500 1.1853 0.08511 0.08015 -0.0232 0.0048 1.0000
13.750 1.1700 0.09085 0.08609 -0.0254 0.0048 1.0000
14.000 1.1556 0.09682 0.09224 -0.0281 0.0048 1.0000
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Polar data table (+)
Polar graphs
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