GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il) Reynolds number: 50,000 Max Cl/Cd: 42.83 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe346-il-50000-n5.txt Download as CSV file: xf-goe346-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 346 (FRIEDRICHSHAFEN-STAAKEN) 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4308 0.12021 0.11296 -0.0138 1.0000 0.0632
-9.000 -0.4322 0.11894 0.11177 -0.0169 1.0000 0.0637
-8.750 -0.4336 0.11753 0.11045 -0.0203 1.0000 0.0639
-8.500 -0.4104 0.10840 0.10126 -0.0152 1.0000 0.0677
-8.250 -0.4049 0.10532 0.09823 -0.0159 1.0000 0.0710
-8.000 -0.4029 0.10294 0.09592 -0.0175 1.0000 0.0741
-7.750 -0.4019 0.10153 0.09460 -0.0222 1.0000 0.0765
-7.500 -0.3962 0.10051 0.09361 -0.0300 1.0000 0.0774
-7.250 -0.3885 0.09439 0.08754 -0.0260 1.0000 0.0791
-7.000 -0.3804 0.09041 0.08360 -0.0245 1.0000 0.0821
-6.750 -0.3726 0.08732 0.08054 -0.0256 1.0000 0.0855
-6.500 -0.3638 0.08475 0.07798 -0.0291 1.0000 0.0901
-6.250 -0.3503 0.08310 0.07627 -0.0367 1.0000 0.0928
-6.000 -0.3475 0.07822 0.07153 -0.0313 1.0000 0.0969
-5.750 -0.3362 0.07568 0.06896 -0.0335 1.0000 0.1047
-5.500 -0.3239 0.07258 0.06583 -0.0361 1.0000 0.1087
-5.250 -0.3159 0.06935 0.06265 -0.0346 1.0000 0.1136
-5.000 -0.2966 0.06699 0.06012 -0.0392 1.0000 0.1221
-4.750 -0.2894 0.06354 0.05673 -0.0370 1.0000 0.1270
-4.500 -0.2716 0.06087 0.05393 -0.0394 1.0000 0.1373
-4.000 -0.2438 0.05539 0.04838 -0.0399 1.0000 0.1670
-3.750 -0.2304 0.05275 0.04573 -0.0395 1.0000 0.1854
-3.500 -0.2151 0.05023 0.04317 -0.0399 1.0000 0.2125
-3.250 -0.2025 0.04773 0.04068 -0.0390 1.0000 0.2448
-3.000 -0.1901 0.04531 0.03829 -0.0380 1.0000 0.2881
-2.500 -0.1510 0.04058 0.03347 -0.0383 1.0000 0.3411
-2.000 -0.0385 0.03708 0.02808 -0.0495 1.0000 0.1171
-1.750 -0.0094 0.03525 0.02590 -0.0500 1.0000 0.0993
-1.500 0.0331 0.03355 0.02373 -0.0528 0.9949 0.0885
-1.250 0.0740 0.03187 0.02171 -0.0557 0.9887 0.0838
-1.000 0.1160 0.03063 0.01998 -0.0583 0.9824 0.0796
-0.750 0.1557 0.02941 0.01857 -0.0611 0.9761 0.0814
-0.500 0.1929 0.02846 0.01741 -0.0632 0.9685 0.0834
-0.250 0.2328 0.02757 0.01626 -0.0656 0.9617 0.0824
0.000 0.2700 0.02682 0.01530 -0.0673 0.9535 0.0813
0.250 0.3071 0.02618 0.01449 -0.0689 0.9456 0.0809
0.500 0.3463 0.02561 0.01375 -0.0709 0.9378 0.0810
0.750 0.3822 0.02513 0.01320 -0.0723 0.9287 0.0817
1.000 0.4235 0.02463 0.01266 -0.0748 0.9212 0.0832
1.250 0.4588 0.02429 0.01233 -0.0762 0.9098 0.0879
1.500 0.4972 0.02388 0.01193 -0.0779 0.8970 0.0954
1.750 0.5351 0.02343 0.01151 -0.0794 0.8821 0.1017
2.000 0.5713 0.02302 0.01113 -0.0802 0.8661 0.1088
2.250 0.6058 0.02261 0.01082 -0.0807 0.8498 0.1231
2.500 0.6351 0.02048 0.01057 -0.0801 0.8334 1.0000
2.750 0.6624 0.02047 0.01038 -0.0790 0.8124 1.0000
3.000 0.6916 0.02033 0.01014 -0.0781 0.7914 1.0000
3.250 0.7186 0.02025 0.01000 -0.0769 0.7684 1.0000
3.500 0.7466 0.02013 0.00987 -0.0758 0.7450 1.0000
3.750 0.7722 0.02015 0.00988 -0.0744 0.7185 1.0000
4.000 0.7980 0.02018 0.00992 -0.0731 0.6903 1.0000
4.250 0.8233 0.02027 0.01003 -0.0718 0.6587 1.0000
4.500 0.8482 0.02039 0.01013 -0.0703 0.6238 1.0000
4.750 0.8721 0.02062 0.01032 -0.0688 0.5842 1.0000
5.000 0.8957 0.02095 0.01054 -0.0672 0.5422 1.0000
5.250 0.9186 0.02145 0.01094 -0.0657 0.4997 1.0000
5.500 0.9407 0.02210 0.01146 -0.0643 0.4586 1.0000
5.750 0.9623 0.02285 0.01211 -0.0630 0.4194 1.0000
6.000 0.9828 0.02368 0.01279 -0.0617 0.3819 1.0000
6.250 1.0023 0.02457 0.01358 -0.0603 0.3456 1.0000
6.500 1.0211 0.02552 0.01438 -0.0590 0.3119 1.0000
6.750 1.0401 0.02645 0.01529 -0.0577 0.2804 1.0000
7.000 1.0589 0.02739 0.01626 -0.0565 0.2504 1.0000
7.250 1.0755 0.02839 0.01729 -0.0552 0.2127 1.0000
7.500 1.0919 0.02954 0.01843 -0.0538 0.1754 1.0000
7.750 1.1070 0.03103 0.01986 -0.0523 0.1364 1.0000
8.000 1.1216 0.03281 0.02152 -0.0507 0.1071 1.0000
8.250 1.1358 0.03464 0.02328 -0.0491 0.0904 1.0000
8.500 1.1496 0.03656 0.02519 -0.0474 0.0804 1.0000
8.750 1.1646 0.03849 0.02730 -0.0458 0.0735 1.0000
9.000 1.1790 0.04054 0.02950 -0.0442 0.0671 1.0000
9.250 1.1936 0.04257 0.03172 -0.0427 0.0617 1.0000
9.500 1.2078 0.04496 0.03411 -0.0412 0.0584 1.0000
9.750 1.2226 0.04745 0.03705 -0.0397 0.0545 1.0000
10.000 1.2333 0.04989 0.03975 -0.0381 0.0510 1.0000
10.250 1.2440 0.05264 0.04269 -0.0367 0.0488 1.0000
10.500 1.2528 0.05605 0.04632 -0.0351 0.0473 1.0000
10.750 1.2522 0.05953 0.05032 -0.0329 0.0460 1.0000
11.000 1.2449 0.06301 0.05420 -0.0305 0.0449 1.0000
11.250 1.2343 0.06675 0.05829 -0.0285 0.0440 1.0000
11.500 1.2206 0.07087 0.06272 -0.0273 0.0434 1.0000
11.750 1.2042 0.07553 0.06768 -0.0270 0.0431 1.0000
12.000 1.1846 0.08096 0.07337 -0.0279 0.0430 1.0000
12.250 1.1621 0.08741 0.08007 -0.0303 0.0433 1.0000
12.500 1.1370 0.09513 0.08801 -0.0343 0.0440 1.0000
12.750 1.1113 0.10415 0.09719 -0.0399 0.0449 1.0000
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Polar data table (+)
Polar graphs
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