GOE 436 AIRFOIL (goe436-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 436 AIRFOIL (goe436-il) Reynolds number: 50,000 Max Cl/Cd: 23.53 at α=12° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe436-il-50000.txt Download as CSV file: xf-goe436-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 436 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3379 0.10675 0.09966 -0.0257 1.0000 0.2365
-8.500 -0.3258 0.10276 0.09569 -0.0245 1.0000 0.2442
-8.250 -0.3433 0.10227 0.09534 -0.0240 1.0000 0.2536
-8.000 -0.3265 0.09815 0.09124 -0.0222 1.0000 0.2663
-7.750 -0.3645 0.09910 0.09243 -0.0208 1.0000 0.2712
-7.500 -0.3455 0.09496 0.08830 -0.0189 1.0000 0.2864
-7.250 -0.3335 0.09145 0.08483 -0.0170 1.0000 0.2981
-7.000 -0.3771 0.09244 0.08608 -0.0133 1.0000 0.3043
-6.750 -0.3640 0.08901 0.08267 -0.0110 1.0000 0.3194
-6.500 -0.3598 0.08631 0.08004 -0.0082 1.0000 0.3334
-6.250 -0.3657 0.08439 0.07820 -0.0048 1.0000 0.3479
-6.000 -0.3741 0.08268 0.07660 -0.0011 1.0000 0.3645
-5.750 -0.3828 0.08106 0.07508 0.0026 1.0000 0.3831
-5.500 -0.3991 0.07987 0.07401 0.0064 1.0000 0.4030
-5.250 -0.3886 0.07719 0.07139 0.0106 1.0000 0.4300
-5.000 -0.4139 0.07663 0.07096 0.0151 1.0000 0.4545
-4.750 -0.4131 0.07472 0.06912 0.0203 1.0000 0.4879
-4.500 -0.3871 0.07181 0.06622 0.0253 1.0000 0.5355
-4.250 -0.1360 0.05951 0.05329 0.0112 1.0000 0.8276
-4.000 0.0600 0.04703 0.04032 -0.0241 1.0000 0.9857
-3.750 -0.0066 0.04977 0.04336 -0.0080 1.0000 0.9485
-3.500 -0.0776 0.05226 0.04613 0.0071 1.0000 0.9074
-3.250 -0.1486 0.05387 0.04801 0.0200 1.0000 0.8591
-3.000 -0.3296 0.04698 0.03978 -0.0210 1.0000 0.2733
-2.750 -0.2914 0.04274 0.03457 -0.0258 1.0000 0.2194
-2.500 -0.2713 0.04064 0.03226 -0.0259 1.0000 0.2131
-2.250 -0.2460 0.03910 0.02994 -0.0266 1.0000 0.2046
-2.000 -0.2273 0.03762 0.02832 -0.0263 1.0000 0.2027
-1.750 -0.2079 0.03641 0.02687 -0.0260 1.0000 0.2003
-1.500 -0.1555 0.03549 0.02547 -0.0313 0.9867 0.2013
-1.250 -0.0966 0.03485 0.02435 -0.0373 0.9703 0.2054
-1.000 -0.0453 0.03402 0.02337 -0.0421 0.9525 0.2097
-0.750 0.0052 0.03362 0.02272 -0.0464 0.9336 0.2207
-0.500 0.0583 0.03301 0.02208 -0.0508 0.9150 0.2329
-0.250 0.1151 0.03249 0.02150 -0.0556 0.8967 0.2539
0.000 0.1694 0.03169 0.02093 -0.0599 0.8790 0.2897
0.250 0.2506 0.02853 0.01994 -0.0676 0.8638 1.0000
0.500 0.2970 0.02872 0.01965 -0.0703 0.8432 1.0000
0.750 0.3396 0.02885 0.01950 -0.0723 0.8221 1.0000
1.000 0.3883 0.02876 0.01920 -0.0752 0.8035 1.0000
1.250 0.4334 0.02865 0.01892 -0.0773 0.7858 1.0000
1.500 0.4744 0.02855 0.01868 -0.0786 0.7686 1.0000
1.750 0.5111 0.02854 0.01854 -0.0793 0.7520 1.0000
2.000 0.5443 0.02863 0.01852 -0.0795 0.7360 1.0000
2.250 0.5743 0.02883 0.01864 -0.0792 0.7205 1.0000
2.500 0.6014 0.02918 0.01891 -0.0787 0.7057 1.0000
2.750 0.6263 0.02968 0.01936 -0.0779 0.6917 1.0000
3.000 0.6517 0.03019 0.01981 -0.0773 0.6788 1.0000
3.250 0.6873 0.03022 0.01977 -0.0776 0.6684 1.0000
3.500 0.7085 0.03101 0.02053 -0.0766 0.6563 1.0000
3.750 0.7217 0.03231 0.02185 -0.0749 0.6442 1.0000
4.000 0.7476 0.03297 0.02249 -0.0744 0.6345 1.0000
4.250 0.7699 0.03383 0.02336 -0.0736 0.6245 1.0000
4.500 0.7753 0.03580 0.02537 -0.0715 0.6138 1.0000
4.750 0.8138 0.03579 0.02536 -0.0721 0.6064 1.0000
5.000 0.8036 0.03881 0.02844 -0.0689 0.5952 1.0000
5.250 0.8377 0.03913 0.02878 -0.0691 0.5880 1.0000
5.500 0.8227 0.04265 0.03236 -0.0660 0.5778 1.0000
5.750 0.8306 0.04475 0.03451 -0.0645 0.5693 1.0000
6.000 0.8291 0.04754 0.03735 -0.0626 0.5606 1.0000
6.250 0.8020 0.05218 0.04198 -0.0595 0.5521 1.0000
6.500 0.8111 0.05437 0.04421 -0.0584 0.5438 1.0000
6.750 0.7799 0.05993 0.04975 -0.0568 0.5361 1.0000
7.000 0.7979 0.06152 0.05140 -0.0561 0.5275 1.0000
7.250 0.7775 0.06628 0.05616 -0.0551 0.5203 1.0000
7.500 0.8206 0.06587 0.05589 -0.0545 0.5100 1.0000
7.750 0.7789 0.07250 0.06246 -0.0539 0.5042 1.0000
8.000 0.8222 0.07218 0.06229 -0.0531 0.4929 1.0000
8.250 0.7817 0.07884 0.06891 -0.0531 0.4881 1.0000
8.500 0.8180 0.07933 0.06953 -0.0523 0.4769 1.0000
8.750 0.7859 0.08550 0.07569 -0.0528 0.4733 1.0000
9.000 0.7744 0.09021 0.08044 -0.0533 0.4705 1.0000
9.250 0.7954 0.09223 0.08256 -0.0528 0.4595 1.0000
9.500 0.7853 0.09726 0.08763 -0.0538 0.4594 1.0000
9.750 0.7939 0.10181 0.09228 -0.0550 0.4617 1.0000
11.500 1.2362 0.06124 0.05346 -0.0242 0.2869 1.0000
12.000 1.3059 0.05551 0.04747 -0.0185 0.2285 1.0000
12.250 1.2496 0.06241 0.05469 -0.0152 0.2301 1.0000
12.500 1.2010 0.07016 0.06256 -0.0148 0.2293 1.0000
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Polar data table (+)
Polar graphs
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