GOE 483 AIRFOIL (goe483-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 483 AIRFOIL (goe483-il) Reynolds number: 200,000 Max Cl/Cd: 85.58 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe483-il-200000-n5.txt Download as CSV file: xf-goe483-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 483 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2652 0.09707 0.09380 -0.0268 1.0000 0.0176
-7.500 -0.2645 0.09507 0.09186 -0.0263 1.0000 0.0180
-7.250 -0.2683 0.09349 0.09037 -0.0250 1.0000 0.0187
-7.000 -0.2553 0.09092 0.08783 -0.0288 0.9911 0.0198
-6.750 -0.2269 0.08731 0.08422 -0.0378 0.9795 0.0203
-6.500 -0.1981 0.08345 0.08034 -0.0464 0.9698 0.0205
-6.250 -0.1696 0.07938 0.07624 -0.0537 0.9601 0.0206
-6.000 -0.1401 0.07511 0.07193 -0.0604 0.9514 0.0207
-5.750 -0.1107 0.07087 0.06764 -0.0667 0.9417 0.0208
-5.500 -0.0826 0.06672 0.06344 -0.0722 0.9306 0.0208
-5.250 -0.0552 0.06273 0.05937 -0.0770 0.9197 0.0208
-5.000 -0.0451 0.05823 0.05487 -0.0766 0.9109 0.0178
-4.750 -0.0162 0.05449 0.05104 -0.0817 0.9004 0.0181
-4.500 0.0125 0.05081 0.04727 -0.0864 0.8902 0.0179
-4.250 0.0425 0.04699 0.04334 -0.0908 0.8810 0.0166
-4.000 0.0752 0.04285 0.03905 -0.0955 0.8722 0.0153
-3.750 0.1093 0.03859 0.03462 -0.1000 0.8633 0.0144
-3.500 0.1452 0.03408 0.02987 -0.1043 0.8558 0.0140
-3.250 0.1815 0.02928 0.02478 -0.1080 0.8477 0.0138
-3.000 0.2222 0.02126 0.01608 -0.1123 0.8411 0.0137
-2.750 0.2539 0.01746 0.01152 -0.1135 0.8333 0.0158
-2.500 0.2831 0.01521 0.00863 -0.1136 0.8256 0.0178
-2.250 0.3113 0.01377 0.00673 -0.1133 0.8175 0.0198
-2.000 0.3385 0.01294 0.00570 -0.1130 0.8086 0.0247
-1.750 0.3659 0.01233 0.00484 -0.1125 0.8000 0.0313
-1.500 0.3927 0.01187 0.00428 -0.1121 0.7900 0.0432
-1.250 0.4194 0.01157 0.00392 -0.1117 0.7795 0.0578
-1.000 0.4461 0.01134 0.00358 -0.1113 0.7689 0.0694
-0.750 0.4727 0.01119 0.00338 -0.1108 0.7580 0.0876
-0.500 0.4993 0.01104 0.00317 -0.1104 0.7462 0.1049
-0.250 0.5258 0.01094 0.00300 -0.1100 0.7342 0.1201
0.000 0.5523 0.01087 0.00288 -0.1096 0.7216 0.1345
0.250 0.5787 0.01084 0.00285 -0.1092 0.7082 0.1553
0.500 0.6051 0.01085 0.00283 -0.1088 0.6938 0.1768
0.750 0.6314 0.01085 0.00277 -0.1083 0.6784 0.1930
1.000 0.6576 0.01086 0.00273 -0.1079 0.6620 0.2100
1.250 0.6835 0.01088 0.00269 -0.1074 0.6445 0.2252
1.500 0.7095 0.01092 0.00268 -0.1069 0.6262 0.2397
1.750 0.7352 0.01098 0.00269 -0.1064 0.6075 0.2553
2.000 0.7608 0.01106 0.00271 -0.1060 0.5898 0.2729
2.250 0.7864 0.01116 0.00276 -0.1055 0.5735 0.2927
2.500 0.8117 0.01125 0.00286 -0.1050 0.5582 0.3208
2.750 0.8394 0.01027 0.00295 -0.1050 0.5441 1.0000
3.000 0.8651 0.01050 0.00309 -0.1046 0.5306 1.0000
3.250 0.8908 0.01073 0.00325 -0.1042 0.5178 1.0000
3.500 0.9163 0.01097 0.00346 -0.1037 0.5048 1.0000
3.750 0.9418 0.01121 0.00366 -0.1033 0.4917 1.0000
4.000 0.9672 0.01146 0.00389 -0.1029 0.4783 1.0000
4.250 0.9926 0.01171 0.00416 -0.1024 0.4653 1.0000
4.500 1.0179 0.01196 0.00443 -0.1020 0.4526 1.0000
4.750 1.0431 0.01221 0.00472 -0.1015 0.4400 1.0000
5.000 1.0681 0.01248 0.00503 -0.1011 0.4275 1.0000
5.250 1.0915 0.01282 0.00535 -0.1003 0.4005 1.0000
5.500 1.1129 0.01331 0.00569 -0.0993 0.3575 1.0000
5.750 1.1319 0.01409 0.00615 -0.0980 0.2950 1.0000
6.000 1.1464 0.01546 0.00692 -0.0963 0.1916 1.0000
6.250 1.1485 0.01856 0.00885 -0.0933 0.0212 1.0000
6.500 1.1684 0.01946 0.00989 -0.0920 0.0152 1.0000
6.750 1.1884 0.02031 0.01100 -0.0907 0.0133 1.0000
7.000 1.2067 0.02131 0.01218 -0.0893 0.0112 1.0000
7.250 1.2196 0.02284 0.01393 -0.0871 0.0096 1.0000
7.500 1.2285 0.02459 0.01585 -0.0845 0.0090 1.0000
7.750 1.2399 0.02599 0.01738 -0.0822 0.0087 1.0000
8.000 1.2497 0.02754 0.01904 -0.0798 0.0084 1.0000
8.250 1.2587 0.02914 0.02073 -0.0772 0.0081 1.0000
8.500 1.2688 0.03052 0.02221 -0.0748 0.0074 1.0000
8.750 1.2786 0.03195 0.02371 -0.0726 0.0067 1.0000
9.000 1.2878 0.03365 0.02555 -0.0705 0.0062 1.0000
9.250 1.2992 0.03579 0.02775 -0.0687 0.0060 1.0000
9.500 1.3178 0.03878 0.03082 -0.0678 0.0058 1.0000
9.750 1.3389 0.04198 0.03420 -0.0672 0.0057 1.0000
10.000 1.3501 0.04454 0.03703 -0.0654 0.0056 1.0000
10.250 1.3594 0.04745 0.04020 -0.0635 0.0056 1.0000
10.500 1.3637 0.05049 0.04352 -0.0613 0.0056 1.0000
10.750 1.3645 0.05370 0.04700 -0.0591 0.0056 1.0000
11.000 1.3638 0.05738 0.05092 -0.0571 0.0057 1.0000
11.500 1.3508 0.06390 0.05795 -0.0533 0.0058 1.0000
11.750 1.3411 0.06716 0.06145 -0.0521 0.0058 1.0000
12.000 1.3297 0.07087 0.06541 -0.0513 0.0058 1.0000
12.250 1.3174 0.07487 0.06966 -0.0512 0.0059 1.0000
12.500 1.3034 0.07946 0.07449 -0.0518 0.0060 1.0000
12.750 1.2877 0.08466 0.07994 -0.0531 0.0061 1.0000
13.000 1.2701 0.09052 0.08604 -0.0554 0.0061 1.0000
13.250 1.2471 0.09787 0.09371 -0.0591 0.0063 1.0000
13.500 1.2285 0.10519 0.10125 -0.0631 0.0064 1.0000
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Polar data table (+)
Polar graphs
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