GOE 437 AIRFOIL (goe437-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 437 AIRFOIL (goe437-il) Reynolds number: 500,000 Max Cl/Cd: 106.84 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe437-il-500000.txt Download as CSV file: xf-goe437-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 437 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3269 0.09178 0.08969 -0.0267 1.0000 0.0148
-7.500 -0.3344 0.09010 0.08806 -0.0248 1.0000 0.0149
-7.250 -0.3441 0.08853 0.08654 -0.0225 1.0000 0.0149
-7.000 -0.3461 0.08614 0.08419 -0.0225 0.9998 0.0149
-6.750 -0.3171 0.08088 0.07892 -0.0311 0.9963 0.0150
-6.500 -0.2878 0.07567 0.07368 -0.0394 0.9926 0.0150
-6.250 -0.2674 0.06800 0.06601 -0.0478 0.9876 0.0157
-6.000 -0.2387 0.06401 0.06199 -0.0534 0.9845 0.0162
-5.750 -0.2079 0.06001 0.05795 -0.0596 0.9804 0.0169
-5.500 -0.1748 0.05553 0.05342 -0.0668 0.9749 0.0178
-5.250 -0.1335 0.05023 0.04802 -0.0759 0.9714 0.0199
-5.000 -0.0803 0.04491 0.04251 -0.0857 0.9683 0.0222
-4.750 -0.0449 0.03970 0.03710 -0.0909 0.9611 0.0223
-4.500 -0.0142 0.03212 0.02928 -0.0973 0.9560 0.0242
-4.250 0.0126 0.03011 0.02716 -0.0986 0.9462 0.0258
-4.000 0.0502 0.02863 0.02541 -0.0998 0.9371 0.0321
-3.750 0.0708 0.01516 0.01059 -0.1006 0.9238 0.0182
-3.500 0.0980 0.01269 0.00760 -0.1000 0.9095 0.0182
-3.250 0.1255 0.01156 0.00620 -0.0995 0.8926 0.0197
-3.000 0.1529 0.01073 0.00513 -0.0990 0.8757 0.0212
-2.750 0.1795 0.00986 0.00404 -0.0985 0.8594 0.0240
-2.500 0.2059 0.00940 0.00347 -0.0980 0.8427 0.0276
-2.250 0.2325 0.00913 0.00306 -0.0974 0.8266 0.0317
-2.000 0.2583 0.00868 0.00252 -0.0968 0.8114 0.0410
-1.750 0.2844 0.00839 0.00214 -0.0963 0.7968 0.0522
-1.500 0.3106 0.00822 0.00188 -0.0958 0.7832 0.0636
-1.250 0.3370 0.00813 0.00178 -0.0954 0.7701 0.0827
-1.000 0.3635 0.00810 0.00174 -0.0949 0.7567 0.1116
-0.750 0.3897 0.00804 0.00167 -0.0945 0.7434 0.1307
-0.500 0.4161 0.00802 0.00159 -0.0941 0.7302 0.1450
-0.250 0.4424 0.00800 0.00154 -0.0937 0.7167 0.1577
0.000 0.4686 0.00797 0.00150 -0.0933 0.7019 0.1745
0.250 0.4945 0.00790 0.00147 -0.0929 0.6856 0.2085
0.500 0.5139 0.00683 0.00156 -0.0917 0.6684 0.6509
0.750 0.5620 0.00620 0.00152 -0.0959 0.6465 1.0000
1.000 0.5869 0.00633 0.00151 -0.0952 0.6229 1.0000
1.250 0.6116 0.00648 0.00151 -0.0945 0.5979 1.0000
1.500 0.6363 0.00667 0.00155 -0.0938 0.5758 1.0000
1.750 0.6611 0.00686 0.00161 -0.0931 0.5574 1.0000
2.000 0.6863 0.00705 0.00169 -0.0925 0.5426 1.0000
2.250 0.7117 0.00723 0.00179 -0.0920 0.5297 1.0000
2.500 0.7372 0.00740 0.00191 -0.0915 0.5177 1.0000
2.750 0.7627 0.00758 0.00203 -0.0910 0.5060 1.0000
3.000 0.7882 0.00776 0.00215 -0.0906 0.4947 1.0000
3.250 0.8137 0.00793 0.00228 -0.0901 0.4836 1.0000
3.500 0.8395 0.00808 0.00242 -0.0897 0.4720 1.0000
3.750 0.8652 0.00824 0.00258 -0.0893 0.4600 1.0000
4.000 0.8907 0.00841 0.00273 -0.0888 0.4475 1.0000
4.250 0.9156 0.00860 0.00287 -0.0883 0.4297 1.0000
4.500 0.9402 0.00880 0.00300 -0.0877 0.4056 1.0000
4.750 0.9646 0.00905 0.00320 -0.0871 0.3865 1.0000
5.000 0.9884 0.00935 0.00340 -0.0864 0.3600 1.0000
5.250 1.0114 0.00973 0.00365 -0.0856 0.3298 1.0000
5.500 1.0344 0.01012 0.00393 -0.0848 0.2967 1.0000
5.750 1.0457 0.01176 0.00470 -0.0825 0.1453 1.0000
6.000 1.0546 0.01382 0.00609 -0.0796 0.0234 1.0000
6.250 1.0770 0.01434 0.00675 -0.0786 0.0204 1.0000
6.500 1.0984 0.01495 0.00747 -0.0774 0.0182 1.0000
6.750 1.1179 0.01576 0.00837 -0.0760 0.0164 1.0000
7.000 1.1293 0.01731 0.01010 -0.0732 0.0143 1.0000
7.250 1.1474 0.01811 0.01098 -0.0716 0.0137 1.0000
7.500 1.1641 0.01901 0.01196 -0.0698 0.0132 1.0000
7.750 1.1789 0.02005 0.01312 -0.0677 0.0126 1.0000
8.000 1.1918 0.02127 0.01443 -0.0653 0.0121 1.0000
8.250 1.2040 0.02265 0.01590 -0.0628 0.0117 1.0000
8.500 1.2168 0.02424 0.01757 -0.0604 0.0117 1.0000
8.750 1.2321 0.02591 0.01933 -0.0586 0.0115 1.0000
9.000 1.2486 0.02730 0.02080 -0.0570 0.0109 1.0000
9.250 1.2634 0.02855 0.02210 -0.0554 0.0101 1.0000
9.500 1.2825 0.03061 0.02428 -0.0543 0.0100 1.0000
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Polar data table (+)
Polar graphs
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