GOE 458 AIRFOIL (goe458-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 458 AIRFOIL (goe458-il) Reynolds number: 100,000 Max Cl/Cd: 65.09 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe458-il-100000.txt Download as CSV file: xf-goe458-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 458 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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3365 0.09777 0.09352 -0.0269 1.0000 0.0700
-7.000 -0.3541 0.09740 0.09326 -0.0242 1.0000 0.0707
-6.750 -0.3685 0.09689 0.09286 -0.0243 1.0000 0.0714
-6.500 -0.3775 0.09609 0.09213 -0.0271 1.0000 0.0719
-6.250 -0.3798 0.09351 0.08962 -0.0292 1.0000 0.0725
-6.000 -0.3786 0.08904 0.08519 -0.0205 1.0000 0.0746
-5.750 -0.3789 0.08679 0.08298 -0.0187 1.0000 0.0768
-5.500 -0.3791 0.08458 0.08081 -0.0187 1.0000 0.0796
-5.000 -0.3645 0.07885 0.07509 -0.0293 1.0000 0.0860
-4.750 -0.3584 0.07578 0.07202 -0.0257 0.9983 0.0888
-4.500 -0.3039 0.07020 0.06625 -0.0420 0.9904 0.0991
-4.250 -0.2799 0.06650 0.06256 -0.0424 0.9845 0.1043
-4.000 -0.2380 0.06176 0.05769 -0.0516 0.9768 0.1150
-3.750 -0.1968 0.05768 0.05350 -0.0584 0.9705 0.1302
-3.500 -0.1591 0.05386 0.04955 -0.0643 0.9623 0.1438
-3.250 -0.1118 0.04963 0.04512 -0.0718 0.9567 0.1575
-3.000 -0.0705 0.04581 0.04102 -0.0778 0.9483 0.1692
-2.750 0.0097 0.03137 0.02484 -0.0907 0.9481 0.0654
-2.500 0.0582 0.02739 0.01966 -0.0940 0.9443 0.0581
-2.250 0.0957 0.02531 0.01702 -0.0955 0.9373 0.0584
-2.000 0.1363 0.02361 0.01511 -0.0979 0.9315 0.0664
-1.750 0.1724 0.02247 0.01373 -0.0990 0.9238 0.0718
-1.500 0.2130 0.02137 0.01274 -0.1011 0.9176 0.0936
-1.250 0.2470 0.02112 0.01281 -0.1023 0.9085 0.2418
-1.000 0.2882 0.02128 0.01300 -0.1052 0.9025 0.3209
-0.750 0.3178 0.02105 0.01270 -0.1056 0.8924 0.3444
-0.500 0.3638 0.02044 0.01212 -0.1089 0.8886 0.3754
-0.250 0.3930 0.02010 0.01191 -0.1093 0.8787 0.4241
0.000 0.4499 0.01838 0.01130 -0.1145 0.8764 1.0000
0.250 0.4792 0.01859 0.01126 -0.1147 0.8666 1.0000
0.500 0.5222 0.01848 0.01094 -0.1173 0.8620 1.0000
0.750 0.5478 0.01875 0.01108 -0.1170 0.8517 1.0000
1.000 0.5899 0.01858 0.01079 -0.1193 0.8476 1.0000
1.250 0.6131 0.01891 0.01105 -0.1186 0.8370 1.0000
1.500 0.6407 0.01914 0.01123 -0.1185 0.8284 1.0000
1.750 0.6755 0.01911 0.01117 -0.1195 0.8223 1.0000
2.000 0.7000 0.01941 0.01145 -0.1190 0.8126 1.0000
2.250 0.7402 0.01899 0.01101 -0.1203 0.8069 1.0000
2.500 0.7667 0.01894 0.01097 -0.1196 0.7950 1.0000
2.750 0.7963 0.01863 0.01071 -0.1189 0.7827 1.0000
3.000 0.8258 0.01831 0.01040 -0.1182 0.7701 1.0000
3.250 0.8540 0.01814 0.01027 -0.1175 0.7583 1.0000
3.500 0.8828 0.01808 0.01026 -0.1172 0.7486 1.0000
3.750 0.9128 0.01797 0.01028 -0.1169 0.7392 1.0000
4.000 0.9373 0.01811 0.01053 -0.1160 0.7276 1.0000
4.250 0.9628 0.01819 0.01074 -0.1151 0.7160 1.0000
4.500 0.9903 0.01799 0.01064 -0.1142 0.7016 1.0000
4.750 1.0184 0.01697 0.00954 -0.1118 0.6697 1.0000
5.000 1.0395 0.01665 0.00931 -0.1092 0.6371 1.0000
5.250 1.0579 0.01637 0.00888 -0.1059 0.5886 1.0000
5.500 1.0721 0.01647 0.00890 -0.1023 0.5309 1.0000
5.750 1.0813 0.01697 0.00902 -0.0981 0.4289 1.0000
6.000 1.0773 0.01902 0.00979 -0.0927 0.2579 1.0000
6.250 1.0773 0.02138 0.01112 -0.0887 0.1004 1.0000
6.500 1.0819 0.02345 0.01270 -0.0851 0.0538 1.0000
6.750 1.0965 0.02462 0.01403 -0.0826 0.0486 1.0000
7.000 1.1091 0.02592 0.01557 -0.0800 0.0457 1.0000
7.250 1.1174 0.02747 0.01728 -0.0769 0.0438 1.0000
7.500 1.1213 0.02917 0.01910 -0.0732 0.0419 1.0000
7.750 1.1304 0.03059 0.02065 -0.0703 0.0398 1.0000
8.000 1.1416 0.03229 0.02243 -0.0677 0.0389 1.0000
8.250 1.1651 0.03440 0.02454 -0.0666 0.0390 1.0000
8.500 1.2133 0.03757 0.02774 -0.0688 0.0401 1.0000
8.750 1.2732 0.04309 0.03330 -0.0727 0.0426 1.0000
9.000 1.2909 0.04367 0.03455 -0.0694 0.0461 1.0000
9.250 1.3150 0.04789 0.03934 -0.0679 0.0507 1.0000
9.500 1.3450 0.05480 0.04645 -0.0684 0.0538 1.0000
9.750 1.3400 0.05508 0.04772 -0.0621 0.0594 1.0000
10.000 1.3474 0.05989 0.05320 -0.0587 0.0692 1.0000
10.250 1.3470 0.06817 0.06222 -0.0554 0.0877 1.0000
10.500 1.3190 0.07360 0.06833 -0.0505 0.0991 1.0000
10.750 1.2176 0.06647 0.06144 -0.0388 0.0818 1.0000
11.000 1.1873 0.07095 0.06617 -0.0359 0.0827 1.0000
11.250 1.1566 0.07580 0.07123 -0.0343 0.0828 1.0000
11.500 1.1247 0.08120 0.07682 -0.0339 0.0826 1.0000
11.750 1.0927 0.08707 0.08285 -0.0346 0.0821 1.0000
12.000 1.0614 0.09323 0.08915 -0.0364 0.0813 1.0000
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Polar data table (+)
Polar graphs
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