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GOE 81 AIRFOIL (goe81-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 81 AIRFOIL (goe81-il)
Reynolds number: 100,000
Max Cl/Cd: 61.71 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe81-il-100000.txt
Download as CSV file: xf-goe81-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 81 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2886   0.10672   0.10230  -0.0246   1.0000   0.0480
  -7.500  -0.3059   0.10706   0.10275  -0.0220   1.0000   0.0481
  -7.250  -0.3202   0.10730   0.10310  -0.0211   1.0000   0.0483
  -7.000  -0.3308   0.10744   0.10331  -0.0216   1.0000   0.0484
  -6.750  -0.3345   0.10726   0.10317  -0.0242   0.9997   0.0486
  -6.500  -0.3225   0.10006   0.09603  -0.0215   0.9968   0.0493
  -6.250  -0.3033   0.09489   0.09083  -0.0219   0.9929   0.0507
  -6.000  -0.2766   0.09074   0.08667  -0.0273   0.9864   0.0527
  -5.750  -0.2463   0.08692   0.08280  -0.0345   0.9790   0.0556
  -5.500  -0.1718   0.08566   0.08124  -0.0602   0.9673   0.0597
  -5.250  -0.1662   0.07920   0.07490  -0.0565   0.9626   0.0607
  -5.000  -0.1419   0.07480   0.07049  -0.0585   0.9585   0.0629
  -4.750  -0.1178   0.07173   0.06738  -0.0622   0.9498   0.0657
  -4.250  -0.0260   0.06470   0.06004  -0.0814   0.9349   0.0738
  -4.000   0.0063   0.06054   0.05588  -0.0845   0.9304   0.0782
  -3.750   0.0732   0.05926   0.05412  -0.0975   0.9200   0.0866
  -3.500   0.1009   0.05356   0.04857  -0.0995   0.9160   0.0895
  -3.250   0.1519   0.05234   0.04701  -0.1065   0.9071   0.1001
  -3.000   0.1865   0.04767   0.04237  -0.1103   0.9025   0.1040
  -2.750   0.2390   0.04495   0.03942  -0.1172   0.8992   0.1176
  -2.500   0.2599   0.04302   0.03750  -0.1173   0.8893   0.1262
  -2.250   0.3037   0.04038   0.03471  -0.1218   0.8850   0.1396
  -2.000   0.3327   0.03872   0.03294  -0.1234   0.8760   0.1533
  -1.750   0.3759   0.03714   0.03112  -0.1271   0.8703   0.1794
  -1.500   0.4015   0.03514   0.02912  -0.1277   0.8619   0.1975
  -1.250   0.4343   0.03325   0.02717  -0.1293   0.8551   0.2292
  -1.000   0.4595   0.03158   0.02550  -0.1296   0.8466   0.2755
  -0.750   0.4855   0.02948   0.02344  -0.1298   0.8392   0.3484
  -0.500   0.5091   0.02773   0.02174  -0.1292   0.8303   0.3994
  -0.250   0.5432   0.02627   0.02017  -0.1300   0.8229   0.4411
   0.000   0.5737   0.02519   0.01898  -0.1303   0.8129   0.4568
   0.500   0.6760   0.02515   0.01723  -0.1334   0.7952   0.1421
   0.750   0.7098   0.02394   0.01568  -0.1330   0.7871   0.1205
   1.000   0.7394   0.02338   0.01484  -0.1321   0.7767   0.1146
   1.250   0.7665   0.02255   0.01396  -0.1313   0.7653   0.1109
   1.500   0.7961   0.02174   0.01302  -0.1305   0.7554   0.1066
   1.750   0.8249   0.02109   0.01224  -0.1296   0.7446   0.1045
   2.000   0.8504   0.02063   0.01177  -0.1284   0.7316   0.1045
   2.250   0.8767   0.02024   0.01133  -0.1273   0.7187   0.1062
   2.500   0.9040   0.01995   0.01095  -0.1265   0.7058   0.1131
   2.750   0.9320   0.01966   0.01058  -0.1258   0.6929   0.1236
   3.000   0.9603   0.01943   0.01029  -0.1251   0.6796   0.1429
   3.250   0.9843   0.01797   0.01014  -0.1236   0.6660   1.0000
   3.500   1.0102   0.01813   0.01003  -0.1226   0.6510   1.0000
   3.750   1.0357   0.01832   0.01005  -0.1217   0.6358   1.0000
   4.000   1.0609   0.01855   0.01017  -0.1208   0.6210   1.0000
   4.250   1.0860   0.01880   0.01033  -0.1201   0.6066   1.0000
   4.500   1.1109   0.01907   0.01053  -0.1193   0.5925   1.0000
   4.750   1.1359   0.01931   0.01073  -0.1185   0.5787   1.0000
   5.000   1.1610   0.01955   0.01092  -0.1178   0.5656   1.0000
   5.250   1.1868   0.01978   0.01108  -0.1172   0.5538   1.0000
   5.500   1.2116   0.02005   0.01134  -0.1165   0.5414   1.0000
   5.750   1.2354   0.02035   0.01169  -0.1157   0.5281   1.0000
   6.000   1.2593   0.02064   0.01199  -0.1149   0.5151   1.0000
   6.250   1.2833   0.02094   0.01229  -0.1141   0.5022   1.0000
   6.500   1.3075   0.02126   0.01260  -0.1133   0.4898   1.0000
   6.750   1.3320   0.02160   0.01292  -0.1126   0.4773   1.0000
   7.000   1.3558   0.02197   0.01324  -0.1118   0.4636   1.0000
   7.250   1.3789   0.02239   0.01364  -0.1109   0.4491   1.0000
   7.500   1.4008   0.02289   0.01416  -0.1098   0.4340   1.0000
   7.750   1.4221   0.02343   0.01474  -0.1087   0.4190   1.0000
   8.000   1.4429   0.02401   0.01538  -0.1076   0.4042   1.0000
   8.250   1.4630   0.02461   0.01605  -0.1063   0.3892   1.0000
   8.500   1.4821   0.02520   0.01674  -0.1049   0.3735   1.0000
   8.750   1.5003   0.02579   0.01740  -0.1034   0.3574   1.0000
   9.000   1.5172   0.02636   0.01801  -0.1016   0.3403   1.0000
   9.250   1.5295   0.02696   0.01875  -0.0992   0.3204   1.0000
   9.500   1.5405   0.02757   0.01942  -0.0967   0.3000   1.0000
   9.750   1.5504   0.02829   0.02012  -0.0941   0.2809   1.0000
  10.000   1.5585   0.02919   0.02104  -0.0913   0.2623   1.0000
  10.250   1.5654   0.03018   0.02207  -0.0885   0.2453   1.0000
  10.500   1.5710   0.03126   0.02317  -0.0855   0.2313   1.0000
  10.750   1.5751   0.03244   0.02436  -0.0825   0.2185   1.0000
  11.000   1.5777   0.03375   0.02567  -0.0795   0.2062   1.0000
  11.250   1.5794   0.03519   0.02724  -0.0768   0.1938   1.0000
  11.500   1.5816   0.03678   0.02896  -0.0743   0.1823   1.0000
  11.750   1.5825   0.03856   0.03084  -0.0720   0.1715   1.0000
  12.000   1.5798   0.04067   0.03300  -0.0698   0.1597   1.0000
  12.250   1.5742   0.04315   0.03551  -0.0678   0.1475   1.0000
  12.500   1.5669   0.04601   0.03836  -0.0661   0.1359   1.0000
  12.750   1.5575   0.04928   0.04167  -0.0645   0.1238   1.0000
  13.000   1.5460   0.05302   0.04551  -0.0634   0.1110   1.0000
  13.250   1.5323   0.05728   0.04986  -0.0627   0.0976   1.0000
  13.500   1.5180   0.06191   0.05458  -0.0624   0.0846   1.0000
  13.750   1.5049   0.06661   0.05931  -0.0625   0.0747   1.0000
  14.000   1.4927   0.07122   0.06394  -0.0624   0.0684   1.0000
  14.250   1.4812   0.07579   0.06846  -0.0624   0.0640   1.0000
  14.500   1.4750   0.07958   0.07227  -0.0617   0.0598   1.0000
  14.750   1.4706   0.08326   0.07601  -0.0613   0.0561   1.0000
  15.000   1.4735   0.08542   0.07796  -0.0593   0.0520   1.0000
  15.250   1.4710   0.08919   0.08200  -0.0593   0.0501   1.0000
  15.500   1.4711   0.09252   0.08553  -0.0589   0.0481   1.0000
  15.750   1.4719   0.09578   0.08894  -0.0585   0.0465   1.0000
  16.000   1.4736   0.09891   0.09217  -0.0581   0.0450   1.0000
  16.250   1.4803   0.10135   0.09465  -0.0569   0.0436   1.0000
  16.500   1.4828   0.10487   0.09828  -0.0560   0.0424   1.0000
  16.750   1.4700   0.11049   0.10419  -0.0581   0.0421   1.0000
  17.000   1.4562   0.11654   0.11052  -0.0607   0.0419   1.0000
  17.250   1.4410   0.12312   0.11736  -0.0639   0.0417   1.0000
  17.500   1.4246   0.13025   0.12474  -0.0678   0.0417   1.0000
  17.750   1.4062   0.13811   0.13285  -0.0725   0.0417   1.0000
  18.000   1.3869   0.14660   0.14155  -0.0778   0.0419   1.0000
  18.250   1.3664   0.15582   0.15097  -0.0839   0.0422   1.0000
  18.500   1.3456   0.16569   0.16100  -0.0905   0.0426   1.0000
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