GOE 362 AIRFOIL (goe362-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 362 AIRFOIL (goe362-il) Reynolds number: 100,000 Max Cl/Cd: 58.38 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe362-il-100000.txt Download as CSV file: xf-goe362-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 362 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3122 0.09521 0.09047 -0.0232 1.0000 0.0650
-7.250 -0.3182 0.09437 0.08974 -0.0243 1.0000 0.0661
-7.000 -0.3186 0.09376 0.08924 -0.0299 1.0000 0.0668
-6.750 -0.3118 0.09234 0.08785 -0.0365 1.0000 0.0671
-6.500 -0.3099 0.08583 0.08144 -0.0269 1.0000 0.0686
-6.250 -0.3044 0.08278 0.07843 -0.0235 1.0000 0.0719
-6.000 -0.3014 0.08053 0.07625 -0.0237 1.0000 0.0751
-5.750 -0.2972 0.07853 0.07431 -0.0261 1.0000 0.0781
-5.500 -0.2761 0.07745 0.07314 -0.0400 1.0000 0.0806
-5.250 -0.2826 0.07315 0.06898 -0.0329 1.0000 0.0817
-5.000 -0.2825 0.07046 0.06636 -0.0292 1.0000 0.0833
-4.750 -0.2781 0.06813 0.06408 -0.0280 1.0000 0.0859
-4.500 -0.2681 0.06571 0.06165 -0.0296 1.0000 0.0899
-4.250 -0.2365 0.06226 0.05801 -0.0399 1.0000 0.0953
-4.000 -0.2356 0.05957 0.05542 -0.0365 1.0000 0.0970
-3.750 -0.2264 0.05725 0.05312 -0.0359 1.0000 0.1005
-3.500 -0.1696 0.05238 0.04800 -0.0477 0.9942 0.1109
-3.250 -0.1176 0.04824 0.04365 -0.0563 0.9865 0.1247
-3.000 -0.0734 0.04463 0.03992 -0.0621 0.9787 0.1402
-2.750 -0.0254 0.04110 0.03624 -0.0682 0.9715 0.1562
-2.500 0.0235 0.03820 0.03305 -0.0745 0.9624 0.1823
-2.250 0.0999 0.02950 0.02287 -0.0838 0.9589 0.0953
-2.000 0.1446 0.02610 0.01909 -0.0871 0.9513 0.0887
-1.750 0.1929 0.02347 0.01576 -0.0904 0.9438 0.0911
-1.500 0.2359 0.02157 0.01343 -0.0929 0.9345 0.0982
-1.250 0.2853 0.02010 0.01174 -0.0965 0.9275 0.1148
-1.000 0.3262 0.01901 0.01047 -0.0984 0.9165 0.1368
-0.750 0.3675 0.01793 0.00953 -0.1005 0.9062 0.1711
-0.500 0.4123 0.01693 0.00867 -0.1030 0.8977 0.2281
-0.250 0.4475 0.01608 0.00806 -0.1038 0.8846 0.2958
0.000 0.4905 0.01380 0.00734 -0.1058 0.8726 1.0000
0.250 0.5238 0.01370 0.00693 -0.1059 0.8577 1.0000
0.500 0.5549 0.01362 0.00663 -0.1055 0.8419 1.0000
0.750 0.5843 0.01357 0.00639 -0.1049 0.8255 1.0000
1.000 0.6107 0.01362 0.00628 -0.1038 0.8065 1.0000
1.250 0.6370 0.01368 0.00620 -0.1027 0.7871 1.0000
1.500 0.6636 0.01376 0.00612 -0.1015 0.7682 1.0000
1.750 0.6891 0.01390 0.00613 -0.1004 0.7480 1.0000
2.000 0.7145 0.01407 0.00617 -0.0993 0.7275 1.0000
2.250 0.7405 0.01425 0.00619 -0.0983 0.7086 1.0000
2.500 0.7656 0.01451 0.00637 -0.0973 0.6883 1.0000
2.750 0.7911 0.01478 0.00653 -0.0964 0.6694 1.0000
3.000 0.8168 0.01507 0.00671 -0.0955 0.6518 1.0000
3.250 0.8426 0.01539 0.00692 -0.0947 0.6352 1.0000
3.500 0.8679 0.01574 0.00724 -0.0940 0.6185 1.0000
3.750 0.8932 0.01611 0.00758 -0.0932 0.6024 1.0000
4.000 0.9185 0.01649 0.00793 -0.0925 0.5871 1.0000
4.250 0.9439 0.01686 0.00829 -0.0919 0.5723 1.0000
4.500 0.9692 0.01725 0.00871 -0.0912 0.5580 1.0000
4.750 0.9945 0.01763 0.00910 -0.0905 0.5440 1.0000
5.000 1.0198 0.01803 0.00951 -0.0898 0.5304 1.0000
5.250 1.0447 0.01841 0.00992 -0.0890 0.5160 1.0000
5.500 1.0688 0.01875 0.01033 -0.0881 0.4991 1.0000
5.750 1.0923 0.01900 0.01058 -0.0870 0.4799 1.0000
6.000 1.1160 0.01925 0.01076 -0.0859 0.4607 1.0000
6.250 1.1389 0.01963 0.01119 -0.0848 0.4420 1.0000
6.500 1.1618 0.02004 0.01171 -0.0838 0.4239 1.0000
6.750 1.1846 0.02043 0.01216 -0.0827 0.4053 1.0000
7.000 1.2069 0.02081 0.01256 -0.0816 0.3861 1.0000
7.250 1.2273 0.02112 0.01306 -0.0802 0.3632 1.0000
7.500 1.2472 0.02140 0.01349 -0.0786 0.3382 1.0000
7.750 1.2645 0.02166 0.01384 -0.0767 0.3037 1.0000
8.000 1.2778 0.02233 0.01440 -0.0744 0.2514 1.0000
8.250 1.2867 0.02396 0.01563 -0.0717 0.1965 1.0000
8.500 1.2977 0.02573 0.01714 -0.0694 0.1642 1.0000
8.750 1.3100 0.02739 0.01867 -0.0674 0.1423 1.0000
9.000 1.3221 0.02896 0.02020 -0.0655 0.1242 1.0000
9.250 1.3334 0.03070 0.02187 -0.0635 0.1091 1.0000
9.500 1.3448 0.03277 0.02384 -0.0617 0.0953 1.0000
9.750 1.3583 0.03542 0.02637 -0.0601 0.0818 1.0000
10.000 1.3684 0.03744 0.02857 -0.0580 0.0711 1.0000
10.250 1.3842 0.04041 0.03177 -0.0564 0.0633 1.0000
10.500 1.4024 0.04381 0.03509 -0.0558 0.0566 1.0000
10.750 1.4094 0.04605 0.03781 -0.0533 0.0528 1.0000
11.000 1.4201 0.04901 0.04105 -0.0515 0.0499 1.0000
11.250 1.4300 0.05225 0.04446 -0.0501 0.0477 1.0000
11.500 1.4363 0.05772 0.05014 -0.0491 0.0458 1.0000
11.750 1.4253 0.06028 0.05311 -0.0455 0.0452 1.0000
12.000 1.4105 0.06315 0.05633 -0.0422 0.0446 1.0000
12.250 1.3944 0.06657 0.06008 -0.0399 0.0442 1.0000
12.500 1.3764 0.07050 0.06431 -0.0386 0.0439 1.0000
12.750 1.3572 0.07507 0.06917 -0.0383 0.0438 1.0000
13.000 1.3369 0.08020 0.07455 -0.0390 0.0439 1.0000
13.250 1.3158 0.08597 0.08055 -0.0407 0.0441 1.0000
13.500 1.2935 0.09239 0.08719 -0.0433 0.0443 1.0000
13.750 1.2707 0.09949 0.09448 -0.0468 0.0447 1.0000
14.000 1.2491 0.10714 0.10227 -0.0509 0.0452 1.0000
14.250 1.2284 0.11532 0.11057 -0.0554 0.0457 1.0000
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Polar data table (+)
Polar graphs
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