GOE 440 AIRFOIL (goe440-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 440 AIRFOIL (goe440-il) Reynolds number: 100,000 Max Cl/Cd: 53.16 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe440-il-100000.txt Download as CSV file: xf-goe440-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 0.2936 0.10260 0.09885 -0.1282 0.8598 0.0340
-7.750 0.3045 0.09990 0.09611 -0.1293 0.8518 0.0353
-7.500 0.3098 0.09802 0.09424 -0.1294 0.8408 0.0365
-7.250 0.3155 0.09635 0.09257 -0.1299 0.8307 0.0377
-7.000 0.3234 0.09497 0.09117 -0.1322 0.8232 0.0387
-6.750 0.3218 0.09467 0.09090 -0.1325 0.8109 0.0390
-6.500 0.3196 0.09439 0.09066 -0.1327 0.7992 0.0393
-6.250 0.3458 0.08650 0.08269 -0.1320 0.7954 0.0417
-6.000 0.3512 0.08422 0.08041 -0.1308 0.7843 0.0439
-5.750 0.3558 0.08237 0.07855 -0.1304 0.7745 0.0461
-5.500 0.3693 0.07995 0.07607 -0.1329 0.7671 0.0491
-5.250 0.3785 0.07904 0.07517 -0.1369 0.7554 0.0509
-5.000 0.4016 0.07805 0.07413 -0.1470 0.7441 0.0518
-4.750 0.4076 0.07224 0.06826 -0.1390 0.7385 0.0558
-4.500 0.4196 0.07010 0.06607 -0.1403 0.7270 0.0601
-4.250 0.4649 0.06825 0.06411 -0.1579 0.7154 0.0651
-4.000 0.4696 0.06378 0.05958 -0.1513 0.7090 0.0688
-3.750 0.4878 0.06145 0.05720 -0.1537 0.6971 0.0754
-3.500 0.5249 0.05789 0.05354 -0.1639 0.6858 0.0816
-3.250 0.5805 0.05382 0.04920 -0.1782 0.6754 0.0947
-3.000 0.5869 0.05137 0.04673 -0.1729 0.6668 0.1007
-2.750 0.6226 0.04823 0.04348 -0.1793 0.6554 0.1155
-2.500 0.6761 0.04471 0.03964 -0.1905 0.6445 0.1547
-2.250 0.6979 0.04276 0.03761 -0.1892 0.6366 0.1879
-1.500 0.9147 0.03073 0.02281 -0.2213 0.6075 0.0654
-1.250 0.9496 0.02897 0.02062 -0.2224 0.5974 0.0521
-1.000 0.9868 0.02744 0.01868 -0.2239 0.5894 0.0514
-0.750 1.0196 0.02624 0.01729 -0.2246 0.5811 0.0533
-0.500 1.0512 0.02548 0.01649 -0.2252 0.5734 0.0592
-0.250 1.0964 0.02375 0.01593 -0.2289 0.5657 0.5132
0.000 1.1129 0.02381 0.01620 -0.2258 0.5586 0.7247
0.250 1.1252 0.02353 0.01600 -0.2223 0.5520 0.8517
0.500 1.1544 0.02375 0.01579 -0.2231 0.5453 1.0000
0.750 1.1822 0.02425 0.01587 -0.2237 0.5381 1.0000
1.000 1.2141 0.02462 0.01583 -0.2249 0.5325 1.0000
1.250 1.2361 0.02528 0.01640 -0.2246 0.5251 1.0000
1.500 1.2675 0.02558 0.01639 -0.2256 0.5197 1.0000
1.750 1.2885 0.02632 0.01712 -0.2251 0.5130 1.0000
2.000 1.3106 0.02593 0.01645 -0.2241 0.4976 1.0000
2.250 1.3301 0.02574 0.01604 -0.2227 0.4823 1.0000
2.500 1.3427 0.02526 0.01515 -0.2199 0.4591 1.0000
2.750 1.3534 0.02552 0.01530 -0.2173 0.4434 1.0000
3.000 1.3516 0.02590 0.01560 -0.2126 0.4206 1.0000
3.250 1.3551 0.02645 0.01603 -0.2090 0.4035 1.0000
3.500 1.3561 0.02717 0.01669 -0.2051 0.3870 1.0000
3.750 1.3549 0.02820 0.01759 -0.2013 0.3660 1.0000
4.000 1.3632 0.02913 0.01844 -0.1990 0.3535 1.0000
4.250 1.3740 0.03007 0.01935 -0.1972 0.3422 1.0000
4.500 1.3844 0.03107 0.02032 -0.1955 0.3307 1.0000
4.750 1.3940 0.03219 0.02139 -0.1937 0.3193 1.0000
5.000 1.4007 0.03355 0.02270 -0.1917 0.3037 1.0000
5.250 1.4199 0.03419 0.02344 -0.1910 0.3085 1.0000
5.500 1.4475 0.03436 0.02382 -0.1911 0.3208 1.0000
5.750 1.4710 0.03479 0.02438 -0.1908 0.3273 1.0000
6.000 1.4911 0.03542 0.02513 -0.1902 0.3296 1.0000
6.250 1.5144 0.03592 0.02578 -0.1898 0.3345 1.0000
6.500 1.5286 0.03690 0.02685 -0.1886 0.3322 1.0000
6.750 1.5374 0.03816 0.02817 -0.1869 0.3268 1.0000
7.000 1.5437 0.03967 0.02975 -0.1851 0.3194 1.0000
7.250 1.5467 0.04145 0.03155 -0.1831 0.3108 1.0000
7.500 1.5432 0.04387 0.03397 -0.1809 0.2963 1.0000
7.750 1.5414 0.04634 0.03644 -0.1789 0.2829 1.0000
8.000 1.5373 0.04914 0.03928 -0.1771 0.2687 1.0000
8.250 1.5326 0.05217 0.04230 -0.1754 0.2550 1.0000
8.500 1.5266 0.05551 0.04563 -0.1738 0.2418 1.0000
8.750 1.5184 0.05924 0.04936 -0.1724 0.2286 1.0000
9.000 1.5080 0.06342 0.05355 -0.1711 0.2153 1.0000
9.250 1.4940 0.06822 0.05835 -0.1701 0.2013 1.0000
9.500 1.4742 0.07396 0.06410 -0.1692 0.1848 1.0000
9.750 1.4502 0.08051 0.07066 -0.1685 0.1668 1.0000
10.000 1.4273 0.08717 0.07735 -0.1682 0.1508 1.0000
10.250 1.4052 0.09390 0.08413 -0.1682 0.1361 1.0000
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Polar data table (+)
Polar graphs
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