GOE 398 AIRFOIL (goe398-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 398 AIRFOIL (goe398-il) Reynolds number: 50,000 Max Cl/Cd: 31.01 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe398-il-50000-n5.txt Download as CSV file: xf-goe398-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 398 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3150 0.10712 0.10032 -0.0401 1.0000 0.0825
-9.250 -0.3281 0.10483 0.09814 -0.0386 1.0000 0.0809
-8.750 -0.3917 0.09843 0.09201 -0.0379 1.0000 0.0760
-8.500 -0.3883 0.09360 0.08719 -0.0429 0.9924 0.0760
-8.250 -0.3867 0.08796 0.08153 -0.0494 0.9827 0.0760
-8.000 -0.3833 0.08132 0.07481 -0.0567 0.9725 0.0760
-7.750 -0.3810 0.07513 0.06849 -0.0621 0.9619 0.0760
-7.500 -0.3778 0.06967 0.06286 -0.0658 0.9520 0.0758
-7.250 -0.3712 0.06375 0.05663 -0.0701 0.9437 0.0758
-7.000 -0.3660 0.05953 0.05218 -0.0714 0.9338 0.0767
-6.750 -0.3418 0.05751 0.05008 -0.0730 0.9282 0.0788
-6.500 -0.3334 0.05447 0.04680 -0.0730 0.9187 0.0802
-6.250 -0.3138 0.05044 0.04233 -0.0752 0.9128 0.0816
-6.000 -0.3047 0.04748 0.03897 -0.0743 0.9034 0.0825
-5.750 -0.2827 0.04428 0.03519 -0.0753 0.8974 0.0849
-5.500 -0.2664 0.04180 0.03211 -0.0746 0.8898 0.0874
-5.250 -0.2427 0.04040 0.03062 -0.0746 0.8830 0.0897
-5.000 -0.2108 0.03868 0.02861 -0.0758 0.8783 0.0925
-4.750 -0.1942 0.03755 0.02719 -0.0743 0.8696 0.0958
-4.500 -0.1641 0.03602 0.02524 -0.0748 0.8634 0.1003
-4.250 -0.1336 0.03498 0.02415 -0.0753 0.8570 0.1045
-4.000 -0.1088 0.03405 0.02300 -0.0747 0.8478 0.1100
-3.750 -0.0687 0.03290 0.02173 -0.0766 0.8425 0.1180
-3.500 -0.0487 0.03232 0.02101 -0.0751 0.8319 0.1255
-3.250 -0.0103 0.03144 0.02011 -0.0766 0.8260 0.1371
-3.000 0.0145 0.03099 0.01961 -0.0760 0.8171 0.1498
-2.750 0.0485 0.03040 0.01898 -0.0768 0.8100 0.1690
-2.250 0.1068 0.02942 0.01801 -0.0770 0.7944 0.2238
-2.000 0.1453 0.02858 0.01735 -0.0786 0.7891 0.2706
-1.750 0.1638 0.02830 0.01729 -0.0771 0.7789 0.3161
-1.500 0.1959 0.02758 0.01697 -0.0775 0.7725 0.4025
-1.250 0.2159 0.02705 0.01699 -0.0757 0.7635 0.5233
-1.000 0.3412 0.02559 0.01647 -0.0923 0.7608 1.0000
-0.750 0.3739 0.02549 0.01604 -0.0928 0.7536 1.0000
-0.500 0.3891 0.02580 0.01614 -0.0905 0.7420 1.0000
-0.250 0.4241 0.02563 0.01570 -0.0912 0.7351 1.0000
0.000 0.4378 0.02600 0.01591 -0.0887 0.7229 1.0000
0.250 0.4746 0.02579 0.01547 -0.0897 0.7166 1.0000
0.500 0.4873 0.02620 0.01576 -0.0870 0.7037 1.0000
0.750 0.5138 0.02627 0.01567 -0.0864 0.6947 1.0000
1.000 0.5379 0.02640 0.01565 -0.0854 0.6846 1.0000
1.250 0.5577 0.02667 0.01581 -0.0838 0.6735 1.0000
1.500 0.5898 0.02656 0.01556 -0.0840 0.6652 1.0000
1.750 0.6054 0.02699 0.01590 -0.0818 0.6531 1.0000
2.000 0.6420 0.02675 0.01551 -0.0826 0.6460 1.0000
2.250 0.6546 0.02729 0.01600 -0.0800 0.6330 1.0000
2.500 0.6783 0.02749 0.01611 -0.0790 0.6230 1.0000
2.750 0.7043 0.02760 0.01613 -0.0783 0.6132 1.0000
3.000 0.7212 0.02805 0.01653 -0.0764 0.6016 1.0000
3.250 0.7547 0.02790 0.01627 -0.0767 0.5935 1.0000
3.500 0.7666 0.02852 0.01688 -0.0742 0.5810 1.0000
3.750 0.7911 0.02871 0.01700 -0.0733 0.5713 1.0000
4.000 0.8138 0.02893 0.01717 -0.0721 0.5608 1.0000
4.250 0.8291 0.02946 0.01768 -0.0701 0.5496 1.0000
4.500 0.8625 0.02927 0.01741 -0.0703 0.5411 1.0000
4.750 0.8721 0.03003 0.01818 -0.0676 0.5292 1.0000
5.000 0.8929 0.03036 0.01847 -0.0663 0.5192 1.0000
5.250 0.9172 0.03056 0.01863 -0.0654 0.5096 1.0000
5.500 0.9309 0.03121 0.01930 -0.0633 0.4990 1.0000
5.750 0.9639 0.03110 0.01910 -0.0635 0.4907 1.0000
6.000 0.9718 0.03200 0.02006 -0.0607 0.4797 1.0000
6.250 0.9966 0.03226 0.02029 -0.0600 0.4707 1.0000
6.500 1.0129 0.03287 0.02092 -0.0583 0.4610 1.0000
6.750 1.0318 0.03343 0.02148 -0.0569 0.4519 1.0000
7.000 1.0519 0.03392 0.02199 -0.0557 0.4427 1.0000
7.250 1.0657 0.03471 0.02280 -0.0537 0.4335 1.0000
7.500 1.0872 0.03522 0.02331 -0.0528 0.4248 1.0000
7.750 1.0983 0.03616 0.02431 -0.0506 0.4161 1.0000
8.000 1.1169 0.03683 0.02502 -0.0493 0.4076 1.0000
8.250 1.1298 0.03780 0.02604 -0.0475 0.3996 1.0000
8.500 1.1402 0.03887 0.02719 -0.0455 0.3915 1.0000
8.750 1.1628 0.03948 0.02783 -0.0448 0.3844 1.0000
9.000 1.1581 0.04129 0.02978 -0.0414 0.3760 1.0000
9.250 1.1912 0.04139 0.02987 -0.0417 0.3696 1.0000
9.500 1.1732 0.04404 0.03271 -0.0376 0.3617 1.0000
9.750 1.1889 0.04504 0.03377 -0.0364 0.3553 1.0000
10.000 1.2022 0.04626 0.03508 -0.0352 0.3496 1.0000
10.250 1.1785 0.04983 0.03884 -0.0318 0.3422 1.0000
10.500 1.2047 0.05015 0.03921 -0.0313 0.3371 1.0000
10.750 1.1757 0.05464 0.04386 -0.0286 0.3303 1.0000
11.000 1.1569 0.05876 0.04811 -0.0269 0.3233 1.0000
11.250 1.1940 0.05795 0.04735 -0.0265 0.3197 1.0000
11.500 1.0788 0.07342 0.06298 -0.0264 0.3070 1.0000
11.750 1.1032 0.07350 0.06315 -0.0255 0.3041 1.0000
12.250 1.0364 0.08984 0.07963 -0.0284 0.2877 1.0000
12.750 0.9849 0.10590 0.09581 -0.0328 0.2728 1.0000
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