GOE 361 AIRFOIL (goe361-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 361 AIRFOIL (goe361-il) Reynolds number: 100,000 Max Cl/Cd: 57.8 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe361-il-100000.txt Download as CSV file: xf-goe361-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.2776 0.09458 0.09002 -0.0230 1.0000 0.0543
-7.000 -0.2816 0.09354 0.08909 -0.0233 1.0000 0.0556
-6.750 -0.2831 0.09319 0.08884 -0.0265 1.0000 0.0565
-6.500 -0.2793 0.09280 0.08851 -0.0318 1.0000 0.0570
-6.250 -0.2756 0.08992 0.08570 -0.0336 1.0000 0.0574
-6.000 -0.2796 0.08476 0.08063 -0.0258 1.0000 0.0585
-5.750 -0.2796 0.08197 0.07788 -0.0227 1.0000 0.0600
-5.500 -0.2791 0.07981 0.07577 -0.0215 1.0000 0.0616
-5.250 -0.2777 0.07781 0.07383 -0.0212 1.0000 0.0635
-5.000 -0.2742 0.07589 0.07195 -0.0221 1.0000 0.0662
-4.750 -0.2324 0.07598 0.07181 -0.0396 1.0000 0.0706
-4.500 -0.2437 0.07156 0.06756 -0.0336 1.0000 0.0715
-4.250 -0.2207 0.06690 0.06295 -0.0341 0.9934 0.0752
-4.000 -0.1371 0.06239 0.05806 -0.0551 0.9842 0.0853
-3.750 -0.1177 0.05774 0.05350 -0.0548 0.9755 0.0885
-3.500 -0.0561 0.05355 0.04905 -0.0671 0.9670 0.1007
-3.250 0.0008 0.05012 0.04534 -0.0767 0.9584 0.1143
-3.000 0.0282 0.04630 0.04163 -0.0781 0.9484 0.1202
-2.750 0.0819 0.04273 0.03786 -0.0858 0.9417 0.1352
-2.500 0.1325 0.03994 0.03479 -0.0928 0.9311 0.1585
-2.250 0.1710 0.03706 0.03191 -0.0961 0.9215 0.1787
-2.000 0.2236 0.03443 0.02907 -0.1023 0.9148 0.2177
-0.750 0.4571 0.02330 0.01558 -0.1166 0.8537 0.1280
-0.500 0.4878 0.02143 0.01345 -0.1159 0.8351 0.1118
-0.250 0.5178 0.02005 0.01184 -0.1153 0.8168 0.1045
0.000 0.5483 0.01942 0.01076 -0.1142 0.7988 0.0989
0.250 0.5770 0.01843 0.00962 -0.1135 0.7814 0.0978
0.500 0.6035 0.01774 0.00881 -0.1125 0.7619 0.1008
0.750 0.6301 0.01718 0.00819 -0.1115 0.7425 0.1047
1.000 0.6568 0.01673 0.00764 -0.1105 0.7239 0.1068
1.250 0.6824 0.01645 0.00724 -0.1093 0.7049 0.1107
1.500 0.7090 0.01625 0.00692 -0.1085 0.6848 0.1179
1.750 0.7363 0.01611 0.00667 -0.1077 0.6656 0.1366
2.000 0.7675 0.01445 0.00644 -0.1080 0.6467 1.0000
2.250 0.7925 0.01474 0.00646 -0.1070 0.6260 1.0000
2.500 0.8178 0.01504 0.00651 -0.1061 0.6067 1.0000
2.750 0.8431 0.01535 0.00660 -0.1052 0.5881 1.0000
3.000 0.8677 0.01568 0.00683 -0.1044 0.5681 1.0000
3.250 0.8926 0.01602 0.00703 -0.1035 0.5494 1.0000
3.500 0.9176 0.01637 0.00723 -0.1028 0.5318 1.0000
3.750 0.9427 0.01677 0.00747 -0.1020 0.5151 1.0000
4.000 0.9674 0.01720 0.00785 -0.1013 0.4979 1.0000
4.250 0.9922 0.01766 0.00823 -0.1006 0.4821 1.0000
4.500 1.0172 0.01816 0.00865 -0.1000 0.4678 1.0000
4.750 1.0426 0.01870 0.00910 -0.0995 0.4554 1.0000
5.000 1.0677 0.01928 0.00971 -0.0990 0.4438 1.0000
5.250 1.0926 0.01991 0.01040 -0.0985 0.4335 1.0000
5.500 1.1187 0.02058 0.01103 -0.0981 0.4255 1.0000
5.750 1.1434 0.02126 0.01185 -0.0977 0.4172 1.0000
6.000 1.1694 0.02198 0.01262 -0.0974 0.4108 1.0000
6.250 1.1930 0.02240 0.01310 -0.0966 0.3994 1.0000
6.500 1.2151 0.02247 0.01310 -0.0954 0.3824 1.0000
6.750 1.2362 0.02260 0.01331 -0.0941 0.3666 1.0000
7.000 1.2576 0.02276 0.01358 -0.0929 0.3520 1.0000
7.250 1.2770 0.02280 0.01378 -0.0913 0.3347 1.0000
7.500 1.2949 0.02272 0.01381 -0.0895 0.3135 1.0000
7.750 1.3104 0.02267 0.01387 -0.0873 0.2845 1.0000
8.000 1.3258 0.02295 0.01421 -0.0851 0.2461 1.0000
8.250 1.3312 0.02463 0.01515 -0.0823 0.1142 1.0000
8.500 1.3319 0.02758 0.01757 -0.0791 0.0664 1.0000
8.750 1.3401 0.02948 0.01953 -0.0766 0.0586 1.0000
9.000 1.3480 0.03116 0.02141 -0.0740 0.0553 1.0000
9.250 1.3530 0.03287 0.02333 -0.0712 0.0530 1.0000
9.500 1.3525 0.03465 0.02528 -0.0677 0.0514 1.0000
9.750 1.3489 0.03663 0.02738 -0.0644 0.0500 1.0000
10.000 1.3423 0.03899 0.02984 -0.0613 0.0486 1.0000
10.250 1.3344 0.04176 0.03266 -0.0587 0.0472 1.0000
10.500 1.3375 0.04391 0.03493 -0.0568 0.0460 1.0000
10.750 1.3465 0.04591 0.03699 -0.0549 0.0452 1.0000
11.000 1.3673 0.04765 0.03874 -0.0532 0.0445 1.0000
11.250 1.4033 0.04967 0.04081 -0.0523 0.0442 1.0000
11.500 1.4391 0.05256 0.04389 -0.0521 0.0440 1.0000
11.750 1.4569 0.05558 0.04717 -0.0511 0.0433 1.0000
12.000 1.4648 0.05870 0.05062 -0.0496 0.0428 1.0000
12.250 1.4680 0.06220 0.05443 -0.0479 0.0431 1.0000
12.500 1.4674 0.06606 0.05862 -0.0464 0.0440 1.0000
12.750 1.4631 0.07023 0.06309 -0.0450 0.0448 1.0000
13.000 1.4579 0.07489 0.06803 -0.0441 0.0457 1.0000
13.250 1.4728 0.08069 0.07405 -0.0438 0.0475 1.0000
13.500 1.4528 0.08337 0.07701 -0.0427 0.0481 1.0000
13.750 1.4284 0.08751 0.08148 -0.0431 0.0488 1.0000
14.000 1.3997 0.09297 0.08724 -0.0449 0.0492 1.0000
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Polar data table (+)
Polar graphs
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