GOE 308 (MVA H.40) AIRFOIL (goe308-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 308 (MVA H.40) AIRFOIL (goe308-il) Reynolds number: 50,000 Max Cl/Cd: 37.95 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe308-il-50000-n5.txt Download as CSV file: xf-goe308-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 308 (MVA H.40) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3133 0.09921 0.09295 -0.0264 1.0000 0.0944
-7.250 -0.3194 0.09730 0.09115 -0.0251 1.0000 0.0958
-7.000 -0.3250 0.09536 0.08932 -0.0243 1.0000 0.0980
-6.750 -0.3319 0.09378 0.08784 -0.0241 1.0000 0.1000
-6.500 -0.3410 0.09294 0.08708 -0.0254 1.0000 0.1016
-6.250 -0.3459 0.09174 0.08590 -0.0268 1.0000 0.1021
-6.000 -0.3438 0.08732 0.08159 -0.0233 1.0000 0.1037
-5.750 -0.3429 0.08435 0.07869 -0.0207 1.0000 0.1060
-5.500 -0.3428 0.08196 0.07633 -0.0197 1.0000 0.1082
-5.250 -0.3417 0.07960 0.07399 -0.0194 1.0000 0.1100
-5.000 -0.3386 0.07722 0.07160 -0.0196 1.0000 0.1120
-4.750 -0.3049 0.07371 0.06781 -0.0281 0.9920 0.1151
-4.500 -0.2727 0.06879 0.06278 -0.0333 0.9824 0.1174
-4.000 -0.1919 0.05708 0.05033 -0.0457 0.9622 0.0758
-3.750 -0.1565 0.05307 0.04608 -0.0497 0.9519 0.0745
-3.500 -0.1205 0.04937 0.04193 -0.0534 0.9402 0.0763
-3.250 -0.0885 0.04605 0.03829 -0.0556 0.9295 0.0760
-3.000 -0.0525 0.04283 0.03469 -0.0583 0.9206 0.0753
-2.750 -0.0200 0.03996 0.03142 -0.0598 0.9098 0.0751
-2.500 0.0129 0.03740 0.02837 -0.0611 0.8988 0.0777
-2.250 0.0470 0.03576 0.02656 -0.0627 0.8889 0.0813
-2.000 0.0843 0.03349 0.02380 -0.0643 0.8794 0.0819
-1.750 0.1178 0.03161 0.02151 -0.0651 0.8681 0.0828
-1.500 0.1550 0.02985 0.01931 -0.0664 0.8578 0.0846
-1.250 0.1984 0.02809 0.01704 -0.0686 0.8493 0.0877
-1.000 0.2339 0.02696 0.01567 -0.0696 0.8368 0.0925
-0.750 0.2735 0.02608 0.01448 -0.0711 0.8244 0.1037
-0.500 0.3155 0.02509 0.01323 -0.0731 0.8121 0.1164
-0.250 0.3542 0.02411 0.01223 -0.0745 0.7993 0.1351
0.000 0.3876 0.02350 0.01157 -0.0750 0.7849 0.1653
0.250 0.4176 0.02322 0.01132 -0.0752 0.7691 0.2155
0.500 0.4466 0.02273 0.01087 -0.0751 0.7531 0.2489
0.750 0.4745 0.02230 0.01046 -0.0746 0.7368 0.2764
1.000 0.5009 0.02182 0.01012 -0.0740 0.7206 0.3172
1.500 0.6154 0.02039 0.00946 -0.0848 0.6870 1.0000
1.750 0.6416 0.02055 0.00938 -0.0841 0.6712 1.0000
2.000 0.6672 0.02076 0.00938 -0.0833 0.6560 1.0000
2.250 0.6922 0.02101 0.00945 -0.0825 0.6412 1.0000
2.500 0.7166 0.02130 0.00960 -0.0817 0.6271 1.0000
2.750 0.7405 0.02163 0.00981 -0.0808 0.6137 1.0000
3.000 0.7643 0.02198 0.01008 -0.0799 0.6010 1.0000
3.250 0.7883 0.02235 0.01037 -0.0791 0.5892 1.0000
3.500 0.8134 0.02271 0.01063 -0.0784 0.5786 1.0000
3.750 0.8362 0.02313 0.01105 -0.0775 0.5673 1.0000
4.000 0.8582 0.02359 0.01152 -0.0764 0.5565 1.0000
4.250 0.8818 0.02402 0.01192 -0.0756 0.5466 1.0000
4.500 0.9049 0.02446 0.01238 -0.0747 0.5367 1.0000
4.750 0.9256 0.02498 0.01297 -0.0735 0.5263 1.0000
5.000 0.9481 0.02544 0.01344 -0.0724 0.5164 1.0000
5.250 0.9711 0.02583 0.01383 -0.0714 0.5058 1.0000
5.500 0.9899 0.02634 0.01444 -0.0698 0.4937 1.0000
5.750 1.0095 0.02683 0.01501 -0.0683 0.4821 1.0000
6.000 1.0307 0.02730 0.01553 -0.0670 0.4714 1.0000
6.250 1.0530 0.02775 0.01602 -0.0659 0.4611 1.0000
6.500 1.0705 0.02841 0.01688 -0.0642 0.4503 1.0000
6.750 1.0905 0.02902 0.01761 -0.0629 0.4404 1.0000
7.000 1.1130 0.02954 0.01822 -0.0619 0.4309 1.0000
7.250 1.1288 0.03031 0.01922 -0.0601 0.4202 1.0000
7.500 1.1477 0.03101 0.02013 -0.0586 0.4104 1.0000
7.750 1.1693 0.03159 0.02084 -0.0575 0.4007 1.0000
8.000 1.1827 0.03250 0.02202 -0.0554 0.3898 1.0000
8.250 1.1996 0.03331 0.02305 -0.0537 0.3799 1.0000
8.500 1.2134 0.03379 0.02370 -0.0513 0.3662 1.0000
8.750 1.2187 0.03404 0.02407 -0.0476 0.3471 1.0000
9.000 1.2224 0.03415 0.02428 -0.0436 0.3268 1.0000
9.250 1.2231 0.03471 0.02496 -0.0396 0.3077 1.0000
9.500 1.2240 0.03547 0.02589 -0.0358 0.2906 1.0000
9.750 1.2199 0.03630 0.02677 -0.0315 0.2702 1.0000
10.000 1.2167 0.03744 0.02798 -0.0278 0.2492 1.0000
10.250 1.2120 0.03892 0.02943 -0.0246 0.2254 1.0000
10.500 1.2068 0.04083 0.03135 -0.0219 0.1998 1.0000
10.750 1.1964 0.04345 0.03382 -0.0195 0.1702 1.0000
11.000 1.1858 0.04658 0.03688 -0.0179 0.1386 1.0000
11.500 1.1483 0.05563 0.04541 -0.0169 0.0695 1.0000
11.750 1.1328 0.06046 0.05018 -0.0172 0.0608 1.0000
12.000 1.1196 0.06526 0.05500 -0.0178 0.0560 1.0000
12.250 1.1070 0.07019 0.05996 -0.0187 0.0526 1.0000
12.500 1.0969 0.07492 0.06482 -0.0196 0.0502 1.0000
12.750 1.0877 0.07963 0.06966 -0.0206 0.0484 1.0000
13.000 1.0790 0.08435 0.07450 -0.0217 0.0469 1.0000
13.250 1.0700 0.08920 0.07944 -0.0228 0.0454 1.0000
13.500 1.0614 0.09401 0.08432 -0.0240 0.0440 1.0000
13.750 1.0545 0.09856 0.08892 -0.0251 0.0428 1.0000
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Polar data table (+)
Polar graphs
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