GOE 361 AIRFOIL (goe361-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 361 AIRFOIL (goe361-il) Reynolds number: 500,000 Max Cl/Cd: 103.78 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe361-il-500000.txt Download as CSV file: xf-goe361-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 361 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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.2942 0.08862 0.08661 -0.0201 1.0000 0.0169
-7.000 -0.3010 0.08719 0.08523 -0.0173 1.0000 0.0171
-6.750 -0.2750 0.08313 0.08116 -0.0230 0.9969 0.0175
-5.250 -0.0729 0.05489 0.05272 -0.0741 0.9608 0.0217
-5.000 -0.0409 0.05165 0.04944 -0.0787 0.9546 0.0224
-4.750 -0.0040 0.04807 0.04579 -0.0850 0.9451 0.0235
-4.500 0.0463 0.04376 0.04130 -0.0945 0.9331 0.0263
-4.250 0.0967 0.03955 0.03681 -0.1023 0.9187 0.0269
-4.000 0.1232 0.03410 0.03117 -0.1061 0.9014 0.0276
-3.750 0.1463 0.03218 0.02915 -0.1069 0.8817 0.0283
-3.500 0.1708 0.03036 0.02718 -0.1076 0.8602 0.0291
-3.250 0.1972 0.02836 0.02496 -0.1084 0.8367 0.0305
-3.000 0.2311 0.02673 0.02296 -0.1089 0.8111 0.0343
-2.750 0.2588 0.02250 0.01825 -0.1102 0.7863 0.0356
-2.500 0.2819 0.02111 0.01671 -0.1101 0.7605 0.0367
-2.250 0.3065 0.02009 0.01550 -0.1100 0.7376 0.0381
-2.000 0.3326 0.01899 0.01416 -0.1098 0.7168 0.0404
-1.750 0.3620 0.01934 0.01414 -0.1089 0.6976 0.0449
-1.500 0.3864 0.01646 0.01104 -0.1094 0.6816 0.0481
-1.250 0.4123 0.01583 0.01026 -0.1092 0.6658 0.0509
-1.000 0.4409 0.01695 0.01109 -0.1083 0.6503 0.0572
-0.750 0.4654 0.01442 0.00846 -0.1086 0.6366 0.0628
0.500 0.6017 0.01100 0.00396 -0.1057 0.5647 0.0454
0.750 0.6278 0.01032 0.00321 -0.1052 0.5488 0.0431
1.000 0.6539 0.01002 0.00281 -0.1047 0.5315 0.0422
1.250 0.6799 0.00984 0.00254 -0.1041 0.5133 0.0421
1.500 0.7060 0.00975 0.00237 -0.1037 0.4947 0.0428
1.750 0.7320 0.00972 0.00226 -0.1032 0.4766 0.0436
2.000 0.7580 0.00975 0.00221 -0.1027 0.4600 0.0443
2.250 0.7840 0.00981 0.00218 -0.1023 0.4444 0.0461
2.500 0.8101 0.00989 0.00218 -0.1019 0.4297 0.0487
2.750 0.8362 0.00999 0.00224 -0.1015 0.4154 0.0525
3.000 0.8617 0.00976 0.00245 -0.1012 0.4018 0.2918
3.250 0.8935 0.00869 0.00267 -0.1024 0.3870 1.0000
3.500 0.9194 0.00890 0.00279 -0.1020 0.3730 1.0000
3.750 0.9451 0.00913 0.00294 -0.1015 0.3588 1.0000
4.000 0.9708 0.00936 0.00310 -0.1011 0.3448 1.0000
4.250 0.9963 0.00960 0.00328 -0.1007 0.3318 1.0000
4.500 1.0216 0.00986 0.00347 -0.1002 0.3194 1.0000
4.750 1.0468 0.01013 0.00367 -0.0997 0.3044 1.0000
5.000 1.0718 0.01040 0.00388 -0.0992 0.2918 1.0000
5.500 1.1219 0.01093 0.00432 -0.0983 0.2700 1.0000
5.750 1.1470 0.01118 0.00457 -0.0978 0.2588 1.0000
6.000 1.1718 0.01146 0.00482 -0.0973 0.2465 1.0000
6.250 1.1959 0.01180 0.00509 -0.0968 0.2283 1.0000
6.500 1.2151 0.01273 0.00554 -0.0956 0.1503 1.0000
6.750 1.2225 0.01514 0.00725 -0.0928 0.0296 1.0000
7.000 1.2449 0.01571 0.00794 -0.0918 0.0258 1.0000
7.250 1.2665 0.01633 0.00865 -0.0908 0.0233 1.0000
7.500 1.2855 0.01724 0.00964 -0.0894 0.0207 1.0000
7.750 1.3026 0.01829 0.01083 -0.0877 0.0193 1.0000
8.000 1.3219 0.01902 0.01165 -0.0864 0.0186 1.0000
8.250 1.3394 0.01989 0.01262 -0.0848 0.0176 1.0000
8.500 1.3551 0.02085 0.01366 -0.0831 0.0168 1.0000
8.750 1.3699 0.02181 0.01470 -0.0812 0.0160 1.0000
9.000 1.3814 0.02295 0.01589 -0.0790 0.0151 1.0000
9.250 1.3821 0.02478 0.01781 -0.0753 0.0144 1.0000
9.750 1.3822 0.02804 0.02126 -0.0676 0.0138 1.0000
10.000 1.3907 0.02914 0.02245 -0.0652 0.0135 1.0000
10.250 1.3963 0.03062 0.02402 -0.0628 0.0133 1.0000
10.500 1.4020 0.03226 0.02575 -0.0605 0.0130 1.0000
10.750 1.4084 0.03400 0.02757 -0.0585 0.0128 1.0000
11.000 1.4159 0.03588 0.02955 -0.0567 0.0125 1.0000
11.250 1.4244 0.03782 0.03159 -0.0550 0.0123 1.0000
11.500 1.4328 0.03975 0.03361 -0.0536 0.0119 1.0000
11.750 1.4400 0.04167 0.03564 -0.0522 0.0115 1.0000
12.000 1.4462 0.04358 0.03762 -0.0511 0.0112 1.0000
12.250 1.4515 0.04565 0.03976 -0.0501 0.0108 1.0000
12.500 1.4598 0.04812 0.04235 -0.0490 0.0107 1.0000
12.750 1.4666 0.05078 0.04512 -0.0480 0.0106 1.0000
13.000 1.4722 0.05375 0.04825 -0.0470 0.0105 1.0000
13.250 1.3366 0.05977 0.05512 -0.0431 0.0113 1.0000
13.500 1.3273 0.06595 0.06157 -0.0430 0.0117 1.0000
13.750 1.3116 0.07267 0.06855 -0.0435 0.0122 1.0000
14.000 1.2928 0.07924 0.07534 -0.0447 0.0125 1.0000
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Polar data table (+)
Polar graphs
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