GOE 457 AIRFOIL (goe457-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 457 AIRFOIL (goe457-il) Reynolds number: 50,000 Max Cl/Cd: 40.12 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe457-il-50000-n5.txt Download as CSV file: xf-goe457-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 457 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3496 0.09873 0.09217 -0.0226 1.0000 0.1019
-7.250 -0.3594 0.09727 0.09086 -0.0229 1.0000 0.1044
-7.000 -0.3677 0.09585 0.08955 -0.0262 1.0000 0.1059
-6.750 -0.3693 0.09361 0.08736 -0.0300 1.0000 0.1064
-6.500 -0.3589 0.08859 0.08242 -0.0230 1.0000 0.1096
-6.250 -0.3553 0.08591 0.07979 -0.0221 1.0000 0.1151
-6.000 -0.3552 0.08411 0.07798 -0.0301 1.0000 0.1209
-5.750 -0.3503 0.08010 0.07409 -0.0248 1.0000 0.1243
-5.500 -0.3439 0.07717 0.07118 -0.0244 1.0000 0.1284
-5.000 -0.3085 0.06563 0.05932 -0.0357 1.0000 0.0740
-4.750 -0.2947 0.06181 0.05543 -0.0371 1.0000 0.0717
-4.500 -0.2762 0.05783 0.05131 -0.0397 1.0000 0.0718
-4.250 -0.2553 0.05379 0.04708 -0.0423 1.0000 0.0719
-4.000 -0.2325 0.04966 0.04269 -0.0447 1.0000 0.0702
-3.750 -0.2069 0.04551 0.03820 -0.0472 1.0000 0.0688
-3.500 -0.1819 0.04231 0.03466 -0.0489 1.0000 0.0712
-3.250 -0.1548 0.03914 0.03103 -0.0505 1.0000 0.0733
-3.000 -0.1281 0.03628 0.02769 -0.0515 1.0000 0.0734
-2.750 -0.1014 0.03383 0.02475 -0.0521 1.0000 0.0738
-2.500 -0.0743 0.03195 0.02225 -0.0524 1.0000 0.0761
-2.250 -0.0328 0.03018 0.02027 -0.0559 0.9916 0.0807
-2.000 0.0103 0.02854 0.01819 -0.0589 0.9828 0.0826
-1.750 0.0535 0.02719 0.01642 -0.0618 0.9732 0.0849
-1.500 0.0954 0.02608 0.01496 -0.0643 0.9624 0.0881
-1.250 0.1376 0.02514 0.01380 -0.0668 0.9512 0.0941
-1.000 0.1806 0.02442 0.01286 -0.0695 0.9389 0.1051
-0.750 0.2215 0.02358 0.01198 -0.0717 0.9253 0.1149
-0.500 0.2625 0.02278 0.01116 -0.0738 0.9110 0.1337
-0.250 0.3033 0.02179 0.01062 -0.0761 0.8961 0.2063
0.000 0.3459 0.01926 0.01014 -0.0784 0.8817 1.0000
0.250 0.3847 0.01915 0.00965 -0.0798 0.8627 1.0000
0.500 0.4186 0.01906 0.00930 -0.0804 0.8396 1.0000
0.750 0.4516 0.01895 0.00899 -0.0807 0.8150 1.0000
1.000 0.4871 0.01881 0.00865 -0.0814 0.7906 1.0000
1.250 0.5231 0.01869 0.00833 -0.0821 0.7651 1.0000
1.500 0.5595 0.01861 0.00805 -0.0829 0.7393 1.0000
1.750 0.5955 0.01860 0.00781 -0.0836 0.7141 1.0000
2.000 0.6291 0.01870 0.00768 -0.0840 0.6892 1.0000
2.250 0.6586 0.01895 0.00774 -0.0838 0.6645 1.0000
2.500 0.6883 0.01925 0.00784 -0.0836 0.6426 1.0000
2.750 0.7154 0.01962 0.00808 -0.0832 0.6214 1.0000
3.000 0.7427 0.02002 0.00836 -0.0828 0.6025 1.0000
3.250 0.7699 0.02044 0.00866 -0.0824 0.5852 1.0000
3.500 0.7970 0.02089 0.00902 -0.0821 0.5692 1.0000
3.750 0.8237 0.02137 0.00946 -0.0817 0.5539 1.0000
4.000 0.8502 0.02187 0.00994 -0.0813 0.5393 1.0000
4.250 0.8763 0.02240 0.01047 -0.0810 0.5253 1.0000
4.500 0.9020 0.02295 0.01108 -0.0805 0.5117 1.0000
4.750 0.9275 0.02353 0.01171 -0.0800 0.4988 1.0000
5.000 0.9527 0.02412 0.01237 -0.0795 0.4863 1.0000
5.250 0.9777 0.02471 0.01305 -0.0789 0.4738 1.0000
5.500 1.0013 0.02527 0.01368 -0.0780 0.4597 1.0000
5.750 1.0222 0.02575 0.01424 -0.0767 0.4421 1.0000
6.000 1.0419 0.02616 0.01471 -0.0751 0.4229 1.0000
6.250 1.0614 0.02651 0.01512 -0.0734 0.4037 1.0000
6.500 1.0811 0.02695 0.01563 -0.0719 0.3863 1.0000
6.750 1.1000 0.02745 0.01628 -0.0703 0.3685 1.0000
7.000 1.1182 0.02795 0.01690 -0.0686 0.3498 1.0000
7.250 1.1360 0.02846 0.01754 -0.0669 0.3309 1.0000
7.500 1.1528 0.02904 0.01822 -0.0651 0.3108 1.0000
7.750 1.1687 0.02972 0.01902 -0.0632 0.2892 1.0000
8.000 1.1840 0.03048 0.01982 -0.0613 0.2688 1.0000
8.250 1.1983 0.03142 0.02087 -0.0593 0.2465 1.0000
8.500 1.2116 0.03246 0.02196 -0.0573 0.2270 1.0000
8.750 1.2244 0.03362 0.02311 -0.0553 0.2103 1.0000
9.000 1.2372 0.03487 0.02444 -0.0534 0.1961 1.0000
9.250 1.2509 0.03622 0.02592 -0.0516 0.1845 1.0000
9.500 1.2642 0.03760 0.02745 -0.0499 0.1752 1.0000
9.750 1.2726 0.03890 0.02881 -0.0477 0.1647 1.0000
10.000 1.2760 0.04020 0.03012 -0.0451 0.1541 1.0000
10.500 1.2826 0.04331 0.03359 -0.0404 0.1364 1.0000
10.750 1.2855 0.04506 0.03547 -0.0383 0.1299 1.0000
11.000 1.2875 0.04701 0.03759 -0.0364 0.1240 1.0000
11.250 1.2878 0.04915 0.03995 -0.0347 0.1178 1.0000
11.500 1.2840 0.05161 0.04248 -0.0332 0.1116 1.0000
11.750 1.2778 0.05456 0.04568 -0.0323 0.1041 1.0000
12.000 1.2705 0.05777 0.04894 -0.0318 0.0982 1.0000
12.250 1.2643 0.06141 0.05294 -0.0319 0.0920 1.0000
12.500 1.2559 0.06536 0.05698 -0.0325 0.0866 1.0000
12.750 1.2457 0.07011 0.06202 -0.0340 0.0798 1.0000
13.000 1.2352 0.07498 0.06700 -0.0358 0.0743 1.0000
13.250 1.2253 0.08024 0.07252 -0.0376 0.0690 1.0000
13.500 1.2146 0.08570 0.07818 -0.0397 0.0641 1.0000
13.750 1.2043 0.09102 0.08352 -0.0418 0.0605 1.0000
14.000 1.1920 0.09733 0.09011 -0.0443 0.0566 1.0000
14.250 1.1795 0.10371 0.09668 -0.0470 0.0534 1.0000
14.500 1.1684 0.10985 0.10290 -0.0498 0.0505 1.0000
14.750 1.1593 0.11560 0.10865 -0.0524 0.0481 1.0000
15.000 1.1438 0.12353 0.11681 -0.0563 0.0470 1.0000
15.250 1.1256 0.13255 0.12600 -0.0609 0.0464 1.0000
15.500 1.1044 0.14296 0.13651 -0.0665 0.0465 1.0000
15.750 1.0824 0.15448 0.14804 -0.0728 0.0466 1.0000
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Polar data table (+)
Polar graphs
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