GOE 389 AIRFOIL (goe389-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 389 AIRFOIL (goe389-il) Reynolds number: 50,000 Max Cl/Cd: 37.63 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe389-il-50000-n5.txt Download as CSV file: xf-goe389-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 389 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3437 0.10610 0.09928 -0.0299 1.0000 0.1319
-8.500 -0.3597 0.10495 0.09829 -0.0323 1.0000 0.1365
-8.250 -0.3782 0.10364 0.09717 -0.0337 1.0000 0.1372
-8.000 -0.3579 0.09829 0.09180 -0.0316 1.0000 0.1394
-7.750 -0.3565 0.09532 0.08890 -0.0307 1.0000 0.1408
-7.500 -0.3769 0.08702 0.08067 -0.0388 1.0000 0.0790
-7.250 -0.3765 0.08394 0.07765 -0.0379 1.0000 0.0778
-7.000 -0.3799 0.08071 0.07449 -0.0384 1.0000 0.0773
-6.750 -0.3832 0.07738 0.07120 -0.0391 1.0000 0.0771
-6.500 -0.3854 0.07392 0.06775 -0.0398 1.0000 0.0769
-6.250 -0.3856 0.07034 0.06416 -0.0406 1.0000 0.0764
-6.000 -0.3835 0.06660 0.06036 -0.0414 1.0000 0.0753
-5.750 -0.3786 0.06250 0.05615 -0.0428 1.0000 0.0739
-5.500 -0.3703 0.05810 0.05156 -0.0447 1.0000 0.0727
-5.250 -0.3582 0.05374 0.04692 -0.0466 1.0000 0.0720
-5.000 -0.3327 0.04963 0.04241 -0.0503 0.9966 0.0743
-4.750 -0.2962 0.04498 0.03716 -0.0556 0.9905 0.0763
-4.500 -0.2573 0.04087 0.03240 -0.0602 0.9841 0.0763
-4.250 -0.2161 0.03746 0.02833 -0.0644 0.9764 0.0769
-4.000 -0.1745 0.03468 0.02490 -0.0679 0.9672 0.0780
-3.750 -0.1333 0.03257 0.02227 -0.0712 0.9576 0.0819
-3.500 -0.0915 0.03096 0.02042 -0.0743 0.9486 0.0859
-3.250 -0.0530 0.02944 0.01855 -0.0763 0.9390 0.0880
-3.000 -0.0156 0.02818 0.01695 -0.0780 0.9302 0.0906
-2.750 0.0252 0.02706 0.01551 -0.0802 0.9226 0.0941
-2.500 0.0594 0.02614 0.01458 -0.0813 0.9130 0.0987
-2.250 0.1026 0.02531 0.01353 -0.0839 0.9062 0.1085
-2.000 0.1357 0.02465 0.01292 -0.0850 0.8954 0.1248
-1.750 0.1712 0.02386 0.01220 -0.0863 0.8856 0.1534
-1.500 0.2089 0.02270 0.01166 -0.0883 0.8769 0.2677
-1.250 0.2321 0.02117 0.01155 -0.0873 0.8654 0.5674
-1.000 0.2711 0.02014 0.01110 -0.0877 0.8539 1.0000
-0.750 0.3029 0.02016 0.01076 -0.0881 0.8410 1.0000
-0.500 0.3339 0.02017 0.01048 -0.0884 0.8277 1.0000
-0.250 0.3642 0.02018 0.01022 -0.0884 0.8141 1.0000
0.000 0.3942 0.02019 0.01000 -0.0884 0.8002 1.0000
0.250 0.4238 0.02019 0.00979 -0.0883 0.7858 1.0000
0.500 0.4533 0.02020 0.00961 -0.0881 0.7713 1.0000
0.750 0.4825 0.02023 0.00946 -0.0879 0.7565 1.0000
1.000 0.5112 0.02029 0.00936 -0.0875 0.7411 1.0000
1.250 0.5393 0.02039 0.00931 -0.0871 0.7255 1.0000
1.500 0.5668 0.02054 0.00933 -0.0867 0.7095 1.0000
1.750 0.5936 0.02073 0.00940 -0.0862 0.6932 1.0000
2.000 0.6199 0.02096 0.00953 -0.0856 0.6770 1.0000
2.250 0.6458 0.02122 0.00971 -0.0851 0.6612 1.0000
2.500 0.6715 0.02149 0.00991 -0.0845 0.6457 1.0000
2.750 0.6972 0.02178 0.01013 -0.0840 0.6310 1.0000
3.000 0.7228 0.02208 0.01040 -0.0835 0.6172 1.0000
3.250 0.7487 0.02239 0.01066 -0.0830 0.6042 1.0000
3.500 0.7750 0.02268 0.01090 -0.0825 0.5924 1.0000
3.750 0.8011 0.02301 0.01122 -0.0821 0.5810 1.0000
4.000 0.8262 0.02343 0.01165 -0.0816 0.5695 1.0000
4.250 0.8519 0.02384 0.01206 -0.0812 0.5591 1.0000
4.500 0.8793 0.02418 0.01239 -0.0810 0.5503 1.0000
4.750 0.9034 0.02473 0.01302 -0.0805 0.5398 1.0000
5.000 0.9290 0.02523 0.01357 -0.0801 0.5308 1.0000
5.250 0.9551 0.02573 0.01411 -0.0798 0.5223 1.0000
5.500 0.9790 0.02637 0.01489 -0.0793 0.5132 1.0000
5.750 1.0063 0.02683 0.01538 -0.0790 0.5054 1.0000
6.000 1.0282 0.02757 0.01629 -0.0783 0.4954 1.0000
6.250 1.0524 0.02816 0.01701 -0.0777 0.4861 1.0000
6.500 1.0773 0.02868 0.01761 -0.0771 0.4761 1.0000
6.750 1.0979 0.02938 0.01848 -0.0761 0.4645 1.0000
7.000 1.1196 0.02998 0.01923 -0.0751 0.4529 1.0000
7.250 1.1425 0.03049 0.01984 -0.0742 0.4414 1.0000
7.500 1.1651 0.03096 0.02046 -0.0732 0.4294 1.0000
7.750 1.1831 0.03169 0.02143 -0.0718 0.4170 1.0000
8.000 1.2021 0.03246 0.02244 -0.0705 0.4062 1.0000
8.250 1.2210 0.03304 0.02321 -0.0691 0.3935 1.0000
8.500 1.2345 0.03342 0.02374 -0.0668 0.3748 1.0000
8.750 1.2468 0.03369 0.02415 -0.0643 0.3548 1.0000
9.000 1.2572 0.03432 0.02496 -0.0619 0.3371 1.0000
9.250 1.2655 0.03515 0.02604 -0.0594 0.3193 1.0000
9.500 1.2708 0.03599 0.02702 -0.0566 0.2982 1.0000
9.750 1.2707 0.03704 0.02815 -0.0533 0.2733 1.0000
10.000 1.2696 0.03835 0.02949 -0.0502 0.2480 1.0000
10.250 1.2692 0.04001 0.03118 -0.0477 0.2233 1.0000
10.500 1.2662 0.04211 0.03326 -0.0455 0.1963 1.0000
10.750 1.2577 0.04492 0.03591 -0.0436 0.1668 1.0000
11.000 1.2449 0.04852 0.03929 -0.0424 0.1420 1.0000
11.500 1.2180 0.05707 0.04772 -0.0417 0.1098 1.0000
11.750 1.2083 0.06138 0.05217 -0.0419 0.0941 1.0000
12.000 1.1992 0.06583 0.05678 -0.0424 0.0758 1.0000
12.250 1.1863 0.07087 0.06180 -0.0432 0.0669 1.0000
12.500 1.1733 0.07607 0.06696 -0.0443 0.0615 1.0000
12.750 1.1627 0.08101 0.07194 -0.0452 0.0569 1.0000
13.000 1.1532 0.08586 0.07685 -0.0462 0.0531 1.0000
13.250 1.1438 0.09074 0.08174 -0.0472 0.0501 1.0000
13.500 1.1359 0.09539 0.08637 -0.0481 0.0476 1.0000
13.750 1.1329 0.09941 0.09057 -0.0487 0.0447 1.0000
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Polar data table (+)
Polar graphs
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