GOE 180 (MVA H.26) AIRFOIL (goe180-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 180 (MVA H.26) AIRFOIL (goe180-il) Reynolds number: 500,000 Max Cl/Cd: 107.43 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe180-il-500000.txt Download as CSV file: xf-goe180-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 180 (MVA H.26) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3642 0.09335 0.09111 -0.0298 1.0000 0.0218
-8.250 -0.3675 0.09039 0.08818 -0.0300 1.0000 0.0218
-8.000 -0.3755 0.08660 0.08444 -0.0286 1.0000 0.0221
-7.750 -0.3748 0.08465 0.08252 -0.0267 1.0000 0.0224
-7.500 -0.3727 0.08272 0.08063 -0.0254 1.0000 0.0227
-7.250 -0.3751 0.08067 0.07863 -0.0245 1.0000 0.0230
-7.000 -0.3698 0.07788 0.07585 -0.0262 0.9990 0.0234
-6.750 -0.3424 0.07293 0.07088 -0.0345 0.9957 0.0245
-6.250 -0.2135 0.03917 0.03706 -0.0664 0.9750 0.0283
-6.000 -0.2377 0.05006 0.04768 -0.0699 0.9814 0.0283
-5.750 -0.2104 0.04799 0.04557 -0.0725 0.9768 0.0293
-5.500 -0.1754 0.04401 0.04147 -0.0781 0.9735 0.0313
-5.250 -0.1360 0.03304 0.02989 -0.0871 0.9662 0.0354
-5.000 -0.1055 0.03158 0.02842 -0.0892 0.9620 0.0364
-4.750 -0.0743 0.02996 0.02672 -0.0912 0.9567 0.0384
-4.500 -0.0409 0.02502 0.02122 -0.0940 0.9490 0.0450
-4.250 -0.0092 0.02383 0.02001 -0.0956 0.9417 0.0466
-4.000 0.0259 0.02193 0.01760 -0.0973 0.9331 0.0547
-3.750 0.0556 0.02028 0.01598 -0.0985 0.9226 0.0568
-3.500 0.0889 0.01496 0.00975 -0.0986 0.9125 0.0414
-3.250 0.1185 0.01310 0.00756 -0.0987 0.9006 0.0395
-3.000 0.1467 0.01217 0.00641 -0.0984 0.8871 0.0395
-2.750 0.1739 0.01149 0.00559 -0.0980 0.8721 0.0401
-2.500 0.2006 0.01085 0.00480 -0.0974 0.8546 0.0401
-2.250 0.2271 0.01035 0.00418 -0.0968 0.8334 0.0405
-2.000 0.2534 0.00996 0.00366 -0.0962 0.8078 0.0409
-1.750 0.2792 0.00967 0.00321 -0.0954 0.7747 0.0413
-1.500 0.3045 0.00953 0.00287 -0.0946 0.7353 0.0421
-1.250 0.3299 0.00948 0.00261 -0.0939 0.6953 0.0430
-1.000 0.3556 0.00939 0.00233 -0.0933 0.6613 0.0437
-0.750 0.3818 0.00930 0.00207 -0.0928 0.6324 0.0454
-0.500 0.4084 0.00929 0.00194 -0.0924 0.6084 0.0479
-0.250 0.4352 0.00931 0.00186 -0.0921 0.5882 0.0511
0.000 0.4622 0.00931 0.00182 -0.0918 0.5719 0.0614
0.250 0.4894 0.00918 0.00183 -0.0917 0.5589 0.1255
0.500 0.5163 0.00885 0.00190 -0.0918 0.5475 0.2848
0.750 0.5403 0.00723 0.00203 -0.0910 0.5368 1.0000
1.000 0.5674 0.00737 0.00205 -0.0908 0.5257 1.0000
1.250 0.5949 0.00748 0.00208 -0.0906 0.5160 1.0000
1.500 0.6220 0.00763 0.00213 -0.0904 0.5070 1.0000
1.750 0.6495 0.00774 0.00217 -0.0902 0.4983 1.0000
2.000 0.6767 0.00788 0.00223 -0.0900 0.4903 1.0000
2.250 0.7042 0.00799 0.00231 -0.0899 0.4828 1.0000
2.500 0.7315 0.00814 0.00239 -0.0897 0.4764 1.0000
2.750 0.7590 0.00824 0.00247 -0.0896 0.4689 1.0000
3.000 0.7860 0.00840 0.00256 -0.0894 0.4621 1.0000
3.250 0.8136 0.00849 0.00267 -0.0893 0.4550 1.0000
3.750 0.8680 0.00875 0.00289 -0.0890 0.4403 1.0000
4.000 0.8947 0.00892 0.00301 -0.0887 0.4323 1.0000
4.250 0.9221 0.00902 0.00313 -0.0886 0.4233 1.0000
4.500 0.9489 0.00917 0.00327 -0.0884 0.4143 1.0000
4.750 0.9756 0.00932 0.00340 -0.0882 0.4039 1.0000
5.000 1.0025 0.00946 0.00356 -0.0880 0.3924 1.0000
5.250 1.0290 0.00962 0.00372 -0.0877 0.3788 1.0000
5.500 1.0550 0.00982 0.00388 -0.0874 0.3612 1.0000
5.750 1.0806 0.01007 0.00408 -0.0870 0.3373 1.0000
6.000 1.1046 0.01049 0.00433 -0.0865 0.3013 1.0000
6.250 1.1275 0.01103 0.00469 -0.0858 0.2684 1.0000
6.500 1.1507 0.01155 0.00508 -0.0851 0.2459 1.0000
7.000 1.1985 0.01240 0.00584 -0.0840 0.2160 1.0000
7.250 1.2228 0.01277 0.00619 -0.0835 0.2028 1.0000
7.500 1.2470 0.01314 0.00654 -0.0830 0.1883 1.0000
7.750 1.2708 0.01354 0.00691 -0.0824 0.1716 1.0000
8.000 1.2934 0.01406 0.00731 -0.0817 0.1466 1.0000
8.250 1.3141 0.01474 0.00785 -0.0808 0.1240 1.0000
8.500 1.3333 0.01556 0.00854 -0.0796 0.0974 1.0000
8.750 1.3408 0.01751 0.01002 -0.0768 0.0336 1.0000
9.000 1.3586 0.01840 0.01095 -0.0752 0.0271 1.0000
9.250 1.3740 0.01948 0.01207 -0.0734 0.0234 1.0000
9.500 1.3929 0.02014 0.01282 -0.0721 0.0218 1.0000
9.750 1.4096 0.02095 0.01369 -0.0705 0.0202 1.0000
10.000 1.4225 0.02200 0.01483 -0.0684 0.0189 1.0000
10.250 1.4282 0.02346 0.01640 -0.0652 0.0179 1.0000
10.500 1.4387 0.02434 0.01737 -0.0627 0.0174 1.0000
10.750 1.4470 0.02538 0.01852 -0.0600 0.0168 1.0000
11.000 1.4541 0.02654 0.01977 -0.0574 0.0161 1.0000
11.250 1.4602 0.02781 0.02113 -0.0549 0.0155 1.0000
11.500 1.4649 0.02927 0.02267 -0.0526 0.0150 1.0000
11.750 1.4652 0.03117 0.02466 -0.0502 0.0145 1.0000
12.000 1.4590 0.03381 0.02740 -0.0478 0.0141 1.0000
12.250 1.4499 0.03696 0.03068 -0.0456 0.0138 1.0000
12.500 1.4542 0.03902 0.03286 -0.0446 0.0136 1.0000
12.750 1.4564 0.04140 0.03536 -0.0437 0.0133 1.0000
13.000 1.4572 0.04403 0.03811 -0.0431 0.0131 1.0000
13.250 1.4570 0.04689 0.04109 -0.0426 0.0128 1.0000
13.500 1.4562 0.04990 0.04422 -0.0423 0.0126 1.0000
13.750 1.4548 0.05306 0.04750 -0.0421 0.0124 1.0000
14.000 1.4531 0.05632 0.05087 -0.0421 0.0122 1.0000
14.250 1.4507 0.05970 0.05435 -0.0422 0.0120 1.0000
14.500 1.4479 0.06318 0.05795 -0.0425 0.0118 1.0000
14.750 1.4449 0.06680 0.06167 -0.0429 0.0116 1.0000
15.000 1.4414 0.07051 0.06548 -0.0435 0.0114 1.0000
15.250 1.4376 0.07432 0.06938 -0.0442 0.0112 1.0000
15.500 1.4334 0.07820 0.07334 -0.0448 0.0110 1.0000
15.750 1.4286 0.08211 0.07733 -0.0453 0.0108 1.0000
16.000 1.4217 0.08606 0.08137 -0.0451 0.0106 1.0000
16.250 1.4111 0.09086 0.08633 -0.0454 0.0104 1.0000
16.500 1.4027 0.09599 0.09161 -0.0475 0.0103 1.0000
16.750 1.3938 0.10121 0.09699 -0.0496 0.0103 1.0000
17.000 1.3839 0.10674 0.10268 -0.0520 0.0102 1.0000
17.250 1.3736 0.11249 0.10860 -0.0546 0.0102 1.0000
17.500 1.3624 0.11858 0.11484 -0.0575 0.0101 1.0000
17.750 1.3506 0.12494 0.12136 -0.0608 0.0101 1.0000
18.000 1.3383 0.13159 0.12818 -0.0643 0.0101 1.0000
18.250 1.3255 0.13856 0.13530 -0.0683 0.0101 1.0000
18.500 1.3124 0.14590 0.14279 -0.0727 0.0101 1.0000
18.750 1.2985 0.15370 0.15075 -0.0775 0.0101 1.0000
19.000 1.2840 0.16197 0.15917 -0.0829 0.0101 1.0000
19.250 1.2689 0.17071 0.16805 -0.0886 0.0102 1.0000
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Polar data table (+)
Polar graphs
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