GOE 440 AIRFOIL (goe440-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 440 AIRFOIL (goe440-il) Reynolds number: 500,000 Max Cl/Cd: 86.65 at α=0.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe440-il-500000-n5.txt Download as CSV file: xf-goe440-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 440 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 0.1882 0.11821 0.11484 -0.1021 0.7004 0.0025
-10.250 0.1978 0.11556 0.11214 -0.1034 0.6923 0.0025
-10.000 0.2076 0.11290 0.10945 -0.1047 0.6837 0.0026
-9.750 0.2174 0.11028 0.10679 -0.1060 0.6758 0.0026
-9.500 0.2271 0.10769 0.10416 -0.1073 0.6677 0.0026
-9.250 0.2370 0.10511 0.10155 -0.1086 0.6601 0.0027
-9.000 0.2470 0.10257 0.09897 -0.1100 0.6522 0.0027
-8.750 0.2570 0.10004 0.09642 -0.1114 0.6452 0.0027
-8.500 0.2670 0.09754 0.09388 -0.1127 0.6379 0.0027
-8.250 0.2771 0.09506 0.09138 -0.1142 0.6307 0.0027
-8.000 0.2871 0.09261 0.08890 -0.1156 0.6229 0.0027
-7.750 0.2972 0.09016 0.08643 -0.1171 0.6150 0.0028
-7.500 0.3072 0.08777 0.08400 -0.1186 0.6071 0.0028
-7.250 0.3174 0.08534 0.08156 -0.1201 0.5989 0.0028
-7.000 0.3275 0.08297 0.07915 -0.1215 0.5911 0.0028
-6.750 0.3378 0.08056 0.07673 -0.1230 0.5828 0.0028
-6.500 0.3480 0.07820 0.07434 -0.1245 0.5749 0.0028
-6.250 0.3580 0.07586 0.07198 -0.1258 0.5660 0.0028
-6.000 0.3670 0.07362 0.06973 -0.1270 0.5570 0.0028
-5.750 0.3738 0.07084 0.06691 -0.1270 0.5473 0.0029
-5.500 0.3840 0.06850 0.06453 -0.1282 0.5365 0.0031
-5.250 0.3965 0.06616 0.06215 -0.1303 0.5261 0.0032
-5.000 0.4104 0.06377 0.05972 -0.1328 0.5155 0.0033
-4.750 0.4387 0.03957 0.03563 -0.1275 0.4813 0.0039
-4.500 0.4491 0.03713 0.03315 -0.1295 0.4736 0.0040
-4.250 0.4621 0.03460 0.03060 -0.1321 0.4665 0.0042
-3.250 0.5890 0.04269 0.03819 -0.1698 0.4523 0.0048
-3.000 0.6433 0.03813 0.03346 -0.1811 0.4455 0.0052
-2.750 0.6973 0.03369 0.02881 -0.1909 0.4396 0.0053
-2.500 0.7487 0.02985 0.02466 -0.1989 0.4331 0.0054
-2.250 0.8055 0.02505 0.01945 -0.2088 0.4272 0.0060
-2.000 0.8507 0.02257 0.01662 -0.2138 0.4213 0.0067
-1.750 0.8937 0.02050 0.01415 -0.2175 0.4160 0.0072
-1.250 0.9797 0.01652 0.00933 -0.2230 0.4076 0.0024
-1.000 1.0157 0.01543 0.00791 -0.2246 0.4031 0.0022
-0.750 1.0496 0.01475 0.00699 -0.2260 0.3987 0.0022
-0.500 1.0826 0.01436 0.00643 -0.2272 0.3947 0.0028
-0.250 1.1131 0.01420 0.00614 -0.2282 0.3909 0.0053
0.000 1.1426 0.01413 0.00588 -0.2288 0.3871 0.0086
0.250 1.1744 0.01387 0.00597 -0.2304 0.3835 0.2183
0.500 1.2021 0.01390 0.00603 -0.2309 0.3798 0.2874
0.750 1.2261 0.01415 0.00621 -0.2307 0.3674 0.3355
1.000 1.2491 0.01445 0.00640 -0.2303 0.3523 0.3586
1.250 1.2723 0.01473 0.00661 -0.2299 0.3410 0.3772
1.500 1.2834 0.01571 0.00718 -0.2276 0.2868 0.3906
1.750 1.2802 0.01729 0.00826 -0.2228 0.2191 0.4008
2.000 1.2535 0.02048 0.01078 -0.2144 0.0963 0.4040
2.250 1.2658 0.02141 0.01168 -0.2125 0.0241 0.4224
2.500 1.2868 0.02178 0.01225 -0.2121 0.0184 0.4871
2.750 1.3072 0.02219 0.01289 -0.2116 0.0135 0.5958
3.000 1.3257 0.02270 0.01357 -0.2107 0.0100 0.6455
3.250 1.3436 0.02323 0.01431 -0.2098 0.0081 0.7057
3.500 1.3552 0.02352 0.01508 -0.2074 0.0097 0.9195
3.750 1.3705 0.02416 0.01573 -0.2060 0.0142 1.0000
4.000 1.3848 0.02505 0.01669 -0.2046 0.0044 1.0000
4.250 1.3907 0.02656 0.01841 -0.2022 0.0089 1.0000
4.500 1.4023 0.02769 0.01960 -0.2006 0.0088 1.0000
4.750 1.4214 0.02827 0.02016 -0.1999 0.0074 1.0000
5.000 1.4323 0.02951 0.02148 -0.1983 0.0067 1.0000
5.250 1.4400 0.03102 0.02309 -0.1964 0.0060 1.0000
5.500 1.4425 0.03301 0.02520 -0.1941 0.0055 1.0000
5.750 1.4360 0.03590 0.02824 -0.1913 0.0052 1.0000
6.000 1.4256 0.03929 0.03179 -0.1884 0.0051 1.0000
6.250 1.4286 0.04158 0.03416 -0.1868 0.0050 1.0000
6.500 1.4500 0.04207 0.03463 -0.1865 0.0047 1.0000
6.750 1.4591 0.04381 0.03644 -0.1854 0.0042 1.0000
7.000 1.4591 0.04659 0.03931 -0.1839 0.0039 1.0000
7.250 1.4564 0.04978 0.04261 -0.1825 0.0037 1.0000
7.500 1.4517 0.05336 0.04630 -0.1812 0.0035 1.0000
7.750 1.4449 0.05731 0.05038 -0.1801 0.0033 1.0000
8.000 1.4356 0.06171 0.05490 -0.1790 0.0032 1.0000
8.250 1.4242 0.06651 0.05983 -0.1781 0.0031 1.0000
8.500 1.4114 0.07166 0.06511 -0.1774 0.0030 1.0000
8.750 1.3967 0.07720 0.07079 -0.1768 0.0030 1.0000
9.000 1.3814 0.08296 0.07667 -0.1765 0.0029 1.0000
9.250 1.3643 0.08911 0.08295 -0.1762 0.0029 1.0000
9.500 1.3481 0.09523 0.08918 -0.1762 0.0028 1.0000
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Polar data table (+)
Polar graphs
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