GOE 424 AIRFOIL (goe424-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 424 AIRFOIL (goe424-il) Reynolds number: 50,000 Max Cl/Cd: 16.22 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe424-il-50000-n5.txt Download as CSV file: xf-goe424-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 424 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3790 0.08695 0.08038 -0.0827 0.9737 0.0732
-10.750 -0.3985 0.07966 0.07294 -0.0893 0.9610 0.0728
-10.500 -0.4206 0.07397 0.06703 -0.0932 0.9458 0.0726
-10.250 -0.4409 0.06959 0.06238 -0.0940 0.9285 0.0726
-9.750 -0.4651 0.06174 0.05370 -0.0931 0.8951 0.0734
-9.500 -0.4536 0.05875 0.05056 -0.0931 0.8813 0.0744
-9.250 -0.4413 0.05593 0.04750 -0.0929 0.8682 0.0752
-9.000 -0.4262 0.05298 0.04421 -0.0929 0.8572 0.0759
-8.750 -0.4119 0.05065 0.04161 -0.0922 0.8441 0.0773
-8.500 -0.3979 0.04854 0.03917 -0.0912 0.8309 0.0789
-8.250 -0.3796 0.04635 0.03657 -0.0906 0.8199 0.0805
-8.000 -0.3581 0.04430 0.03407 -0.0902 0.8094 0.0817
-7.750 -0.3381 0.04265 0.03203 -0.0893 0.7975 0.0826
-7.500 -0.3061 0.04076 0.03000 -0.0903 0.7898 0.0848
-7.250 -0.2835 0.03958 0.02871 -0.0897 0.7780 0.0870
-7.000 -0.2497 0.03810 0.02700 -0.0906 0.7712 0.0893
-6.750 -0.2263 0.03719 0.02592 -0.0898 0.7599 0.0908
-6.500 -0.1923 0.03607 0.02452 -0.0905 0.7533 0.0934
-6.250 -0.1695 0.03531 0.02376 -0.0898 0.7430 0.0960
-6.000 -0.1392 0.03437 0.02273 -0.0901 0.7365 0.0993
-5.750 -0.1187 0.03387 0.02214 -0.0889 0.7277 0.1017
-5.500 -0.0941 0.03326 0.02134 -0.0883 0.7211 0.1046
-5.250 -0.0725 0.03266 0.02064 -0.0875 0.7149 0.1085
-5.000 -0.0568 0.03221 0.02017 -0.0859 0.7073 0.1129
-4.750 -0.0339 0.03161 0.01942 -0.0852 0.7020 0.1187
-4.500 -0.0176 0.03122 0.01901 -0.0837 0.6955 0.1242
-4.250 -0.0007 0.03080 0.01861 -0.0823 0.6892 0.1337
-4.000 0.0204 0.02998 0.01804 -0.0817 0.6847 0.1605
-3.750 0.0345 0.02917 0.01773 -0.0802 0.6798 0.2546
-3.500 0.0405 0.02879 0.01814 -0.0769 0.6738 0.4115
-3.250 0.0583 0.02871 0.01832 -0.0748 0.6693 0.4974
-3.000 0.0817 0.02868 0.01836 -0.0732 0.6657 0.5641
-2.750 0.0922 0.02920 0.01900 -0.0701 0.6598 0.6094
-2.500 0.1077 0.02961 0.01945 -0.0675 0.6547 0.6523
-2.250 0.1302 0.02987 0.01969 -0.0658 0.6509 0.6909
-2.000 0.1581 0.03008 0.01985 -0.0648 0.6481 0.7264
-1.750 0.1701 0.03085 0.02066 -0.0620 0.6428 0.7537
-1.500 0.1855 0.03152 0.02133 -0.0596 0.6377 0.7831
-1.250 0.2147 0.03200 0.02174 -0.0588 0.6340 0.8153
-1.000 0.2513 0.03231 0.02191 -0.0595 0.6311 0.8456
-0.750 0.2868 0.03283 0.02228 -0.0608 0.6278 0.8675
-0.500 0.3002 0.03400 0.02347 -0.0597 0.6218 0.8871
-0.250 0.3340 0.03455 0.02387 -0.0615 0.6176 0.9046
0.000 0.3778 0.03479 0.02393 -0.0649 0.6145 0.9207
0.250 0.4266 0.03489 0.02382 -0.0690 0.6120 0.9357
0.500 0.4527 0.03628 0.02520 -0.0710 0.6066 0.9533
0.750 0.4871 0.03734 0.02621 -0.0743 0.6015 0.9697
1.000 0.5343 0.03774 0.02648 -0.0790 0.5979 0.9838
1.250 0.5875 0.03785 0.02644 -0.0845 0.5952 0.9964
1.500 0.6149 0.03792 0.02636 -0.0852 0.5929 1.0000
1.750 0.5015 0.04206 0.03071 -0.0667 0.5816 1.0000
2.000 0.5073 0.04261 0.03114 -0.0639 0.5780 1.0000
2.250 0.5303 0.04278 0.03116 -0.0633 0.5756 1.0000
3.750 0.4918 0.05464 0.04270 -0.0447 0.5389 1.0000
4.250 0.4823 0.05976 0.04778 -0.0413 0.5240 1.0000
4.500 0.5102 0.06009 0.04803 -0.0413 0.5212 1.0000
5.000 0.5090 0.06480 0.05271 -0.0388 0.5066 1.0000
5.250 0.5370 0.06514 0.05299 -0.0388 0.5036 1.0000
5.750 0.5409 0.06958 0.05742 -0.0368 0.4889 1.0000
6.000 0.5694 0.06985 0.05764 -0.0368 0.4859 1.0000
6.250 0.5559 0.07329 0.06111 -0.0354 0.4757 1.0000
6.500 0.5764 0.07412 0.06192 -0.0351 0.4709 1.0000
6.750 0.6062 0.07424 0.06200 -0.0351 0.4681 1.0000
7.000 0.5899 0.07797 0.06578 -0.0339 0.4568 1.0000
7.250 0.6148 0.07842 0.06621 -0.0337 0.4528 1.0000
7.750 0.6268 0.08245 0.07027 -0.0326 0.4381 1.0000
8.000 0.6550 0.08259 0.07040 -0.0325 0.4350 1.0000
8.250 0.6418 0.08630 0.07416 -0.0317 0.4239 1.0000
8.500 0.6657 0.08680 0.07467 -0.0315 0.4201 1.0000
9.000 0.6771 0.09108 0.07901 -0.0308 0.4055 1.0000
9.250 0.7040 0.09126 0.07920 -0.0306 0.4027 1.0000
9.500 0.6886 0.09556 0.08357 -0.0303 0.3916 1.0000
9.750 0.7127 0.09594 0.08397 -0.0301 0.3881 1.0000
10.000 0.7022 0.09990 0.08799 -0.0300 0.3782 1.0000
10.250 0.7209 0.10091 0.08902 -0.0298 0.3740 1.0000
10.500 0.7444 0.10137 0.08952 -0.0296 0.3712 1.0000
10.750 0.7287 0.10612 0.09434 -0.0298 0.3606 1.0000
11.000 0.7515 0.10658 0.09483 -0.0296 0.3573 1.0000
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Polar data table (+)
Polar graphs
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