GOE 448 AIRFOIL (goe448-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 448 AIRFOIL (goe448-il) Reynolds number: 200,000 Max Cl/Cd: 162.03 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe448-il-200000.txt Download as CSV file: xf-goe448-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 448 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 0.2707 0.09312 0.08885 -0.1459 0.8316 0.0485
-8.750 0.2787 0.09126 0.08696 -0.1474 0.8270 0.0502
-8.500 0.2770 0.09131 0.08705 -0.1509 0.8199 0.0509
-8.250 0.2869 0.08806 0.08377 -0.1518 0.8160 0.0512
-8.000 0.3047 0.08431 0.07994 -0.1508 0.8133 0.0521
-7.750 0.3142 0.08240 0.07807 -0.1509 0.8075 0.0531
-7.500 0.3239 0.08042 0.07608 -0.1516 0.8028 0.0543
-7.250 0.3340 0.07837 0.07399 -0.1529 0.7990 0.0560
-7.000 0.3361 0.07779 0.07342 -0.1551 0.7933 0.0576
-6.750 0.3497 0.07742 0.07304 -0.1670 0.7867 0.0582
-6.500 0.3590 0.07319 0.06878 -0.1613 0.7840 0.0586
-6.250 0.3744 0.07037 0.06591 -0.1602 0.7815 0.0595
-6.000 0.3835 0.06877 0.06435 -0.1602 0.7759 0.0604
-5.750 0.3977 0.06685 0.06241 -0.1618 0.7713 0.0618
-5.500 0.4175 0.06461 0.06011 -0.1653 0.7678 0.0638
-5.250 0.4656 0.06221 0.05752 -0.1836 0.7635 0.0664
-5.000 0.4676 0.05995 0.05534 -0.1795 0.7583 0.0669
-4.750 0.4798 0.05775 0.05313 -0.1779 0.7546 0.0675
-4.500 0.5005 0.05556 0.05088 -0.1789 0.7516 0.0687
-4.250 0.5292 0.05325 0.04846 -0.1825 0.7491 0.0706
-4.000 0.5449 0.05188 0.04713 -0.1841 0.7430 0.0729
-3.750 0.5954 0.04850 0.04352 -0.1960 0.7390 0.0764
-3.500 0.6144 0.04652 0.04151 -0.1957 0.7361 0.0774
-3.250 0.6432 0.04456 0.03946 -0.1978 0.7338 0.0793
-3.000 0.6971 0.04223 0.03680 -0.2084 0.7287 0.0866
-2.750 0.7080 0.04046 0.03512 -0.2065 0.7243 0.0878
-2.500 0.7299 0.03913 0.03377 -0.2065 0.7212 0.0900
-2.250 0.7820 0.03654 0.03083 -0.2141 0.7188 0.0999
-2.000 0.8039 0.03534 0.02964 -0.2141 0.7157 0.1021
-1.750 0.8194 0.03479 0.02912 -0.2129 0.7101 0.1067
-1.500 0.8524 0.03331 0.02749 -0.2154 0.7066 0.1170
-1.250 0.8897 0.03193 0.02591 -0.2185 0.7040 0.1304
-0.750 0.9414 0.03032 0.02417 -0.2195 0.6966 0.1499
-0.500 0.9671 0.02960 0.02337 -0.2200 0.6923 0.1647
-0.250 1.0000 0.02863 0.02225 -0.2217 0.6892 0.1801
0.250 1.0200 0.01286 0.00592 -0.2113 0.6738 0.1426
0.500 1.0570 0.01132 0.00420 -0.2137 0.6713 0.1351
0.750 1.0994 0.01006 0.00242 -0.2164 0.6691 0.1295
1.000 1.1057 0.01053 0.00290 -0.2129 0.6622 0.1286
1.250 1.1348 0.01013 0.00235 -0.2133 0.6581 0.1280
1.500 1.1702 0.00951 0.00156 -0.2148 0.6551 0.1284
1.750 1.1995 0.00922 0.00123 -0.2154 0.6516 0.1309
2.000 1.2094 0.00959 0.00167 -0.2126 0.6457 0.1319
2.250 1.2365 0.00941 0.00144 -0.2127 0.6420 0.1328
2.500 1.2701 0.00908 0.00105 -0.2139 0.6392 0.1343
2.750 1.2996 0.00896 0.00090 -0.2145 0.6359 0.1364
3.000 1.3056 0.00946 0.00152 -0.2110 0.6298 0.1377
3.250 1.3318 0.00939 0.00143 -0.2109 0.6258 0.1411
3.500 1.3667 0.00910 0.00113 -0.2125 0.6229 0.1468
3.750 1.3879 0.00927 0.00137 -0.2117 0.6188 0.1526
4.000 1.3960 0.00974 0.00192 -0.2085 0.6130 0.1580
4.250 1.4234 0.00967 0.00189 -0.2087 0.6093 0.1734
4.500 1.4616 0.00926 0.00165 -0.2109 0.6064 0.2880
4.750 1.4683 0.00919 0.00249 -0.2075 0.6011 1.0000
5.000 1.4805 0.00956 0.00285 -0.2051 0.5956 1.0000
5.250 1.5133 0.00951 0.00269 -0.2062 0.5920 1.0000
5.500 1.5458 0.00954 0.00263 -0.2073 0.5882 1.0000
5.750 1.5331 0.01032 0.00355 -0.2005 0.5810 1.0000
6.000 1.5626 0.01029 0.00344 -0.2011 0.5766 1.0000
6.250 1.6059 0.01014 0.00316 -0.2041 0.5729 1.0000
6.500 1.5793 0.01116 0.00437 -0.1950 0.5651 1.0000
6.750 1.6092 0.01110 0.00426 -0.1957 0.5604 1.0000
7.000 1.6364 0.01123 0.00434 -0.1959 0.5559 1.0000
7.250 1.6195 0.01224 0.00548 -0.1889 0.5481 1.0000
7.500 1.6531 0.01209 0.00528 -0.1901 0.5436 1.0000
7.750 1.6493 0.01300 0.00628 -0.1855 0.5369 1.0000
8.000 1.6573 0.01351 0.00681 -0.1827 0.5300 1.0000
8.250 1.6754 0.01367 0.00693 -0.1815 0.5232 1.0000
8.500 1.6658 0.01485 0.00820 -0.1763 0.5146 1.0000
8.750 1.6786 0.01525 0.00858 -0.1744 0.5069 1.0000
9.000 1.6711 0.01663 0.01004 -0.1698 0.4982 1.0000
9.250 1.6799 0.01742 0.01083 -0.1675 0.4906 1.0000
9.500 1.6742 0.01902 0.01249 -0.1635 0.4818 1.0000
9.750 1.6750 0.02045 0.01395 -0.1605 0.4735 1.0000
10.000 1.6764 0.02196 0.01549 -0.1576 0.4655 1.0000
10.250 1.6759 0.02375 0.01735 -0.1546 0.4576 1.0000
10.500 1.6772 0.02542 0.01904 -0.1519 0.4491 1.0000
10.750 1.6719 0.02788 0.02157 -0.1487 0.4409 1.0000
11.000 1.6781 0.02929 0.02296 -0.1467 0.4322 1.0000
11.250 1.6629 0.03288 0.02667 -0.1428 0.4230 1.0000
11.500 1.6700 0.03435 0.02809 -0.1409 0.4138 1.0000
11.750 1.6549 0.03827 0.03213 -0.1374 0.4048 1.0000
12.000 1.6546 0.04066 0.03455 -0.1351 0.3960 1.0000
12.250 1.6482 0.04380 0.03773 -0.1325 0.3863 1.0000
12.500 1.6375 0.04756 0.04157 -0.1297 0.3769 1.0000
12.750 1.6349 0.05028 0.04426 -0.1274 0.3664 1.0000
13.000 1.6212 0.05445 0.04852 -0.1247 0.3562 1.0000
13.250 1.6094 0.05842 0.05254 -0.1222 0.3454 1.0000
13.500 1.6025 0.06173 0.05584 -0.1201 0.3347 1.0000
13.750 1.5891 0.06586 0.06005 -0.1177 0.3243 1.0000
14.000 1.5767 0.06988 0.06414 -0.1156 0.3136 1.0000
14.250 1.5661 0.07356 0.06785 -0.1137 0.3029 1.0000
14.500 1.5512 0.07766 0.07198 -0.1117 0.2905 1.0000
14.750 1.5337 0.08207 0.07647 -0.1098 0.2773 1.0000
15.000 1.5153 0.08637 0.08082 -0.1079 0.2623 1.0000
15.250 1.4955 0.09063 0.08510 -0.1062 0.2454 1.0000
15.500 1.4720 0.09500 0.08946 -0.1044 0.2235 1.0000
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Polar data table (+)
Polar graphs
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