GOE 376 AIRFOIL (goe376-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 376 AIRFOIL (goe376-il) Reynolds number: 50,000 Max Cl/Cd: 41.47 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe376-il-50000-n5.txt Download as CSV file: xf-goe376-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 376 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3192 0.11114 0.10430 -0.0245 1.0000 0.0631
-8.250 -0.3245 0.11041 0.10373 -0.0254 1.0000 0.0635
-8.000 -0.3300 0.10980 0.10323 -0.0272 1.0000 0.0639
-7.750 -0.3146 0.10256 0.09600 -0.0241 1.0000 0.0659
-7.500 -0.3088 0.09914 0.09263 -0.0230 1.0000 0.0685
-7.250 -0.3077 0.09675 0.09034 -0.0227 1.0000 0.0710
-7.000 -0.3069 0.09471 0.08840 -0.0234 1.0000 0.0744
-6.750 -0.3068 0.09373 0.08751 -0.0265 1.0000 0.0769
-6.500 -0.3031 0.09375 0.08757 -0.0327 1.0000 0.0780
-6.250 -0.3003 0.08725 0.08122 -0.0253 1.0000 0.0814
-6.000 -0.2968 0.08462 0.07865 -0.0245 1.0000 0.0852
-5.750 -0.2925 0.08273 0.07680 -0.0263 1.0000 0.0901
-5.500 -0.2802 0.08258 0.07659 -0.0337 1.0000 0.0926
-5.250 -0.2827 0.07756 0.07173 -0.0280 1.0000 0.0948
-5.000 -0.2794 0.07481 0.06904 -0.0262 1.0000 0.0986
-4.750 -0.2659 0.07336 0.06747 -0.0302 1.0000 0.1060
-4.250 -0.2558 0.06748 0.06170 -0.0279 1.0000 0.1151
-4.000 -0.2360 0.06459 0.05873 -0.0312 0.9975 0.1250
-3.750 -0.1980 0.06071 0.05472 -0.0374 0.9882 0.1401
-3.500 -0.1598 0.05697 0.05084 -0.0430 0.9781 0.1561
-3.250 -0.1183 0.05376 0.04738 -0.0495 0.9668 0.1826
-3.000 -0.0895 0.05032 0.04392 -0.0519 0.9557 0.2142
-2.000 0.0997 0.03880 0.03063 -0.0713 0.9149 0.1188
-1.750 0.1445 0.03617 0.02759 -0.0744 0.9071 0.1013
-1.500 0.1838 0.03420 0.02516 -0.0761 0.8963 0.0886
-1.250 0.2219 0.03232 0.02288 -0.0778 0.8859 0.0825
-1.000 0.2661 0.03095 0.02091 -0.0798 0.8771 0.0772
-0.750 0.3003 0.02945 0.01921 -0.0808 0.8653 0.0757
-0.500 0.3347 0.02835 0.01780 -0.0816 0.8528 0.0761
-0.250 0.3697 0.02746 0.01657 -0.0823 0.8401 0.0774
0.000 0.4034 0.02648 0.01537 -0.0829 0.8271 0.0773
0.250 0.4377 0.02557 0.01426 -0.0834 0.8139 0.0769
0.500 0.4750 0.02476 0.01320 -0.0844 0.8005 0.0768
0.750 0.5101 0.02407 0.01233 -0.0849 0.7861 0.0769
1.000 0.5426 0.02352 0.01163 -0.0851 0.7711 0.0775
1.250 0.5733 0.02306 0.01106 -0.0850 0.7552 0.0784
1.500 0.6028 0.02266 0.01060 -0.0848 0.7387 0.0819
1.750 0.6318 0.02242 0.01026 -0.0845 0.7215 0.0882
2.000 0.6606 0.02225 0.00999 -0.0841 0.7039 0.0940
2.250 0.6890 0.02209 0.00974 -0.0836 0.6858 0.1009
2.500 0.7163 0.02199 0.00960 -0.0829 0.6672 0.1143
2.750 0.7531 0.02042 0.00964 -0.0847 0.6464 1.0000
3.000 0.7782 0.02067 0.00962 -0.0836 0.6276 1.0000
3.250 0.8033 0.02093 0.00967 -0.0826 0.6098 1.0000
3.500 0.8281 0.02122 0.00978 -0.0817 0.5926 1.0000
3.750 0.8518 0.02156 0.01004 -0.0806 0.5749 1.0000
4.000 0.8757 0.02191 0.01030 -0.0797 0.5578 1.0000
4.250 0.8995 0.02228 0.01059 -0.0787 0.5411 1.0000
4.500 0.9233 0.02267 0.01094 -0.0777 0.5246 1.0000
4.750 0.9468 0.02308 0.01130 -0.0768 0.5083 1.0000
5.000 0.9702 0.02353 0.01170 -0.0758 0.4923 1.0000
5.250 0.9934 0.02400 0.01214 -0.0748 0.4762 1.0000
5.500 1.0163 0.02451 0.01267 -0.0738 0.4603 1.0000
5.750 1.0389 0.02505 0.01320 -0.0727 0.4444 1.0000
6.000 1.0612 0.02563 0.01379 -0.0717 0.4286 1.0000
6.250 1.0831 0.02625 0.01444 -0.0706 0.4131 1.0000
6.500 1.1044 0.02690 0.01518 -0.0695 0.3978 1.0000
6.750 1.1254 0.02759 0.01597 -0.0684 0.3830 1.0000
7.000 1.1458 0.02831 0.01679 -0.0672 0.3685 1.0000
7.250 1.1659 0.02906 0.01769 -0.0660 0.3547 1.0000
7.500 1.1857 0.02986 0.01868 -0.0648 0.3418 1.0000
7.750 1.2055 0.03069 0.01968 -0.0636 0.3297 1.0000
8.000 1.2258 0.03154 0.02068 -0.0625 0.3190 1.0000
8.250 1.2465 0.03236 0.02165 -0.0614 0.3091 1.0000
8.500 1.2636 0.03329 0.02286 -0.0599 0.2972 1.0000
8.750 1.2759 0.03375 0.02334 -0.0575 0.2799 1.0000
9.000 1.2843 0.03442 0.02411 -0.0549 0.2612 1.0000
9.250 1.2959 0.03526 0.02508 -0.0528 0.2475 1.0000
9.500 1.3080 0.03623 0.02626 -0.0508 0.2358 1.0000
9.750 1.3162 0.03728 0.02754 -0.0484 0.2226 1.0000
10.000 1.3189 0.03838 0.02882 -0.0455 0.2065 1.0000
10.250 1.3184 0.03964 0.03024 -0.0424 0.1912 1.0000
10.500 1.3120 0.04129 0.03203 -0.0392 0.1691 1.0000
10.750 1.3034 0.04347 0.03421 -0.0367 0.1411 1.0000
11.000 1.2956 0.04616 0.03688 -0.0350 0.1139 1.0000
11.250 1.2861 0.04946 0.04014 -0.0338 0.0846 1.0000
11.500 1.2718 0.05363 0.04416 -0.0334 0.0675 1.0000
11.750 1.2578 0.05822 0.04870 -0.0337 0.0599 1.0000
12.000 1.2445 0.06308 0.05361 -0.0344 0.0552 1.0000
12.250 1.2319 0.06813 0.05881 -0.0354 0.0515 1.0000
12.500 1.2190 0.07349 0.06429 -0.0369 0.0489 1.0000
12.750 1.2064 0.07898 0.06991 -0.0386 0.0472 1.0000
13.000 1.1933 0.08471 0.07573 -0.0404 0.0458 1.0000
13.250 1.1825 0.09014 0.08125 -0.0422 0.0445 1.0000
13.500 1.1737 0.09537 0.08664 -0.0438 0.0429 1.0000
13.750 1.1663 0.10041 0.09183 -0.0454 0.0416 1.0000
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Polar data table (+)
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