GOE 360 AIRFOIL (goe360-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 360 AIRFOIL (goe360-il) Reynolds number: 500,000 Max Cl/Cd: 105.29 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe360-il-500000.txt Download as CSV file: xf-goe360-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 360 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.1462 0.09019 0.08814 -0.0432 0.9443 0.0189
-9.000 -0.1421 0.08736 0.08527 -0.0432 0.9305 0.0192
-8.750 -0.2393 0.09754 0.09546 -0.0361 0.9786 0.0187
-8.500 -0.2246 0.09402 0.09193 -0.0382 0.9621 0.0189
-8.250 -0.2150 0.09114 0.08902 -0.0396 0.9436 0.0192
-8.000 -0.2090 0.08860 0.08642 -0.0402 0.9272 0.0195
-7.750 -0.2029 0.08600 0.08378 -0.0411 0.9134 0.0199
-7.500 -0.1959 0.08327 0.08101 -0.0426 0.9013 0.0204
-7.250 -0.1878 0.08042 0.07812 -0.0450 0.8903 0.0211
-7.000 -0.1711 0.07692 0.07455 -0.0516 0.8795 0.0220
-6.750 -0.1438 0.07231 0.06984 -0.0642 0.8678 0.0222
-6.500 -0.1258 0.06780 0.06526 -0.0685 0.8578 0.0223
-6.250 -0.1168 0.06469 0.06212 -0.0671 0.8481 0.0225
-6.000 -0.1022 0.06188 0.05928 -0.0677 0.8366 0.0228
-5.750 -0.0838 0.05906 0.05639 -0.0697 0.8243 0.0231
-5.500 -0.0626 0.05614 0.05339 -0.0725 0.8114 0.0237
-5.250 -0.0391 0.05312 0.05027 -0.0756 0.7974 0.0244
-5.000 0.0032 0.04947 0.04634 -0.0827 0.7823 0.0266
-4.750 0.0362 0.04604 0.04262 -0.0863 0.7662 0.0268
-4.500 0.0557 0.04183 0.03828 -0.0879 0.7495 0.0271
-4.250 0.0753 0.03946 0.03581 -0.0885 0.7317 0.0274
-4.000 0.0977 0.03741 0.03363 -0.0893 0.7151 0.0278
-3.750 0.1222 0.03548 0.03154 -0.0902 0.7001 0.0285
-3.500 0.1490 0.03348 0.02936 -0.0912 0.6867 0.0297
-3.250 0.1866 0.03190 0.02737 -0.0921 0.6753 0.0323
-2.750 0.2394 0.02653 0.02154 -0.0935 0.6559 0.0332
-2.500 0.2642 0.02500 0.01991 -0.0940 0.6468 0.0337
-2.250 0.2902 0.02376 0.01854 -0.0944 0.6375 0.0345
-2.000 0.3175 0.02257 0.01720 -0.0946 0.6292 0.0359
-1.750 0.3489 0.02215 0.01646 -0.0942 0.6211 0.0392
-1.500 0.3777 0.02021 0.01415 -0.0943 0.6138 0.0403
-1.250 0.4037 0.01868 0.01258 -0.0947 0.6055 0.0412
-1.000 0.4308 0.01778 0.01161 -0.0949 0.5973 0.0424
-0.750 0.4585 0.01707 0.01075 -0.0949 0.5889 0.0446
-0.500 0.4885 0.01779 0.01122 -0.0944 0.5803 0.0485
-0.250 0.5151 0.01555 0.00885 -0.0948 0.5723 0.0509
0.000 0.5428 0.01490 0.00816 -0.0949 0.5630 0.0533
1.500 0.7107 0.01190 0.00437 -0.0938 0.4978 0.0499
1.750 0.7381 0.01186 0.00426 -0.0936 0.4849 0.0490
2.000 0.7649 0.01134 0.00372 -0.0934 0.4728 0.0466
2.250 0.7917 0.01115 0.00347 -0.0932 0.4614 0.0460
2.500 0.8185 0.01106 0.00333 -0.0930 0.4503 0.0464
2.750 0.8456 0.01102 0.00325 -0.0930 0.4398 0.0473
3.000 0.8725 0.01105 0.00324 -0.0928 0.4301 0.0484
3.250 0.8993 0.01104 0.00318 -0.0928 0.4207 0.0517
3.500 0.9264 0.01109 0.00323 -0.0927 0.4124 0.0553
3.750 0.9531 0.01123 0.00330 -0.0926 0.4047 0.0599
4.000 0.9767 0.00965 0.00355 -0.0921 0.3982 1.0000
4.250 1.0032 0.00987 0.00367 -0.0920 0.3912 1.0000
4.500 1.0297 0.01008 0.00383 -0.0919 0.3849 1.0000
4.750 1.0563 0.01027 0.00399 -0.0918 0.3785 1.0000
5.000 1.0821 0.01055 0.00419 -0.0916 0.3726 1.0000
5.250 1.1090 0.01070 0.00437 -0.0915 0.3675 1.0000
5.500 1.1353 0.01092 0.00458 -0.0914 0.3623 1.0000
5.750 1.1607 0.01123 0.00483 -0.0912 0.3574 1.0000
6.000 1.1874 0.01138 0.00504 -0.0911 0.3528 1.0000
6.250 1.2131 0.01161 0.00526 -0.0909 0.3461 1.0000
6.500 1.2387 0.01185 0.00549 -0.0907 0.3396 1.0000
6.750 1.2645 0.01204 0.00571 -0.0906 0.3331 1.0000
7.000 1.2894 0.01231 0.00596 -0.0903 0.3257 1.0000
7.250 1.3151 0.01249 0.00619 -0.0902 0.3190 1.0000
7.500 1.3393 0.01282 0.00648 -0.0898 0.3122 1.0000
7.750 1.3649 0.01297 0.00669 -0.0896 0.3030 1.0000
8.000 1.3892 0.01325 0.00699 -0.0893 0.2945 1.0000
8.250 1.4132 0.01353 0.00727 -0.0889 0.2849 1.0000
8.500 1.4368 0.01384 0.00757 -0.0885 0.2706 1.0000
8.750 1.4585 0.01429 0.00794 -0.0879 0.2457 1.0000
9.000 1.4643 0.01606 0.00910 -0.0852 0.1578 1.0000
9.250 1.4460 0.01957 0.01181 -0.0794 0.0407 1.0000
9.500 1.4501 0.02092 0.01309 -0.0762 0.0263 1.0000
9.750 1.4613 0.02182 0.01408 -0.0741 0.0240 1.0000
10.000 1.4696 0.02296 0.01530 -0.0719 0.0221 1.0000
10.250 1.4753 0.02436 0.01679 -0.0697 0.0206 1.0000
10.500 1.4845 0.02557 0.01810 -0.0680 0.0198 1.0000
10.750 1.4913 0.02702 0.01965 -0.0664 0.0189 1.0000
11.000 1.4958 0.02873 0.02146 -0.0647 0.0181 1.0000
11.250 1.4979 0.03076 0.02359 -0.0632 0.0175 1.0000
11.500 1.4953 0.03335 0.02628 -0.0617 0.0170 1.0000
11.750 1.4882 0.03660 0.02967 -0.0605 0.0166 1.0000
12.000 1.4767 0.04057 0.03378 -0.0597 0.0163 1.0000
12.250 1.4763 0.04351 0.03683 -0.0594 0.0161 1.0000
12.500 1.4739 0.04677 0.04020 -0.0592 0.0158 1.0000
12.750 1.4697 0.05032 0.04388 -0.0591 0.0156 1.0000
13.000 1.4641 0.05407 0.04774 -0.0591 0.0154 1.0000
13.250 1.4579 0.05795 0.05173 -0.0592 0.0151 1.0000
13.500 1.4517 0.06192 0.05581 -0.0595 0.0148 1.0000
13.750 1.4456 0.06594 0.05992 -0.0598 0.0145 1.0000
14.000 1.4393 0.07002 0.06409 -0.0601 0.0143 1.0000
14.250 1.4337 0.07408 0.06824 -0.0606 0.0140 1.0000
14.500 1.4278 0.07820 0.07243 -0.0611 0.0137 1.0000
14.750 1.4224 0.08223 0.07653 -0.0615 0.0135 1.0000
15.000 1.4176 0.08617 0.08053 -0.0619 0.0133 1.0000
15.250 1.4139 0.08981 0.08422 -0.0621 0.0131 1.0000
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Polar data table (+)
Polar graphs
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