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GOE 394 AIRFOIL (goe394-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 394 AIRFOIL (goe394-il)
Reynolds number: 100,000
Max Cl/Cd: 66.64 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe394-il-100000-n5.txt
Download as CSV file: xf-goe394-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 394 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2905   0.10330   0.09861  -0.0240   1.0000   0.0454
  -8.000  -0.2838   0.10071   0.09608  -0.0256   1.0000   0.0475
  -7.750  -0.2834   0.09949   0.09498  -0.0281   1.0000   0.0500
  -7.500  -0.2756   0.09817   0.09373  -0.0352   0.9846   0.0506
  -7.250  -0.2563   0.09310   0.08867  -0.0391   0.9730   0.0514
  -7.000  -0.2389   0.08862   0.08417  -0.0387   0.9652   0.0530
  -6.750  -0.2182   0.08506   0.08058  -0.0426   0.9535   0.0549
  -6.500  -0.1968   0.08164   0.07712  -0.0475   0.9416   0.0574
  -6.250  -0.1571   0.07901   0.07436  -0.0646   0.9260   0.0615
  -6.000  -0.1453   0.07449   0.06984  -0.0630   0.9199   0.0626
  -5.750  -0.1293   0.07127   0.06659  -0.0635   0.9114   0.0640
  -5.500  -0.1069   0.06804   0.06329  -0.0670   0.9047   0.0654
  -5.250  -0.0834   0.06493   0.06013  -0.0711   0.8967   0.0671
  -4.750  -0.0184   0.05656   0.05146  -0.0854   0.8835   0.0602
  -4.500   0.0062   0.05302   0.04783  -0.0883   0.8782   0.0562
  -4.000   0.0736   0.04610   0.04059  -0.0989   0.8689   0.0571
  -3.750   0.1097   0.04227   0.03655  -0.1042   0.8641   0.0554
  -3.500   0.1482   0.03817   0.03215  -0.1095   0.8597   0.0542
  -3.250   0.1836   0.03455   0.02822  -0.1135   0.8525   0.0538
  -3.000   0.2154   0.03212   0.02553  -0.1154   0.8457   0.0556
  -2.750   0.2478   0.02943   0.02248  -0.1175   0.8370   0.0579
  -2.500   0.2808   0.02642   0.01902  -0.1192   0.8304   0.0580
  -2.250   0.3125   0.02378   0.01590  -0.1206   0.8230   0.0587
  -2.000   0.3439   0.02140   0.01293  -0.1214   0.8175   0.0602
  -1.750   0.3733   0.01993   0.01107  -0.1217   0.8123   0.0623
  -1.500   0.4007   0.01956   0.01063  -0.1215   0.8062   0.0647
  -1.250   0.4288   0.01896   0.00981  -0.1213   0.8011   0.0694
  -1.000   0.4562   0.01871   0.00946  -0.1211   0.7949   0.0766
  -0.750   0.4841   0.01821   0.00877  -0.1208   0.7889   0.0863
  -0.500   0.5117   0.01784   0.00821  -0.1203   0.7833   0.0985
  -0.250   0.5388   0.01767   0.00791  -0.1200   0.7761   0.1097
   0.000   0.5657   0.01754   0.00774  -0.1196   0.7703   0.1221
   0.250   0.5922   0.01748   0.00771  -0.1194   0.7625   0.1356
   0.500   0.6188   0.01727   0.00753  -0.1189   0.7559   0.1449
   0.750   0.6454   0.01717   0.00737  -0.1184   0.7478   0.1508
   1.000   0.6719   0.01695   0.00716  -0.1178   0.7405   0.1546
   1.250   0.6987   0.01684   0.00706  -0.1174   0.7316   0.1574
   1.500   0.7258   0.01671   0.00688  -0.1168   0.7240   0.1604
   1.750   0.7522   0.01667   0.00687  -0.1163   0.7136   0.1637
   2.250   0.8054   0.01654   0.00677  -0.1151   0.6943   0.1737
   2.500   0.8315   0.01654   0.00683  -0.1146   0.6822   0.1822
   2.750   0.8576   0.01649   0.00691  -0.1141   0.6695   0.1926
   3.000   0.8838   0.01644   0.00697  -0.1136   0.6557   0.2105
   3.250   0.9097   0.01613   0.00715  -0.1132   0.6405   0.3558
   3.500   0.9354   0.01526   0.00717  -0.1125   0.6238   1.0000
   3.750   0.9612   0.01534   0.00720  -0.1118   0.6061   1.0000
   4.000   0.9869   0.01545   0.00727  -0.1111   0.5869   1.0000
   4.250   1.0124   0.01555   0.00730  -0.1103   0.5682   1.0000
   4.500   1.0375   0.01570   0.00731  -0.1094   0.5489   1.0000
   4.750   1.0621   0.01596   0.00744  -0.1085   0.5287   1.0000
   5.000   1.0863   0.01630   0.00767  -0.1076   0.5092   1.0000
   5.250   1.1106   0.01671   0.00802  -0.1068   0.4920   1.0000
   5.500   1.1348   0.01714   0.00841  -0.1061   0.4757   1.0000
   5.750   1.1587   0.01758   0.00883  -0.1053   0.4595   1.0000
   6.000   1.1822   0.01805   0.00930  -0.1045   0.4424   1.0000
   6.250   1.2057   0.01851   0.00979  -0.1037   0.4263   1.0000
   6.500   1.2295   0.01896   0.01033  -0.1030   0.4127   1.0000
   6.750   1.2528   0.01943   0.01088  -0.1022   0.3977   1.0000
   7.000   1.2754   0.01991   0.01148  -0.1013   0.3814   1.0000
   7.250   1.2977   0.02040   0.01211  -0.1004   0.3635   1.0000
   7.500   1.3191   0.02093   0.01275  -0.0994   0.3422   1.0000
   7.750   1.3371   0.02161   0.01340  -0.0980   0.3048   1.0000
   8.000   1.3503   0.02271   0.01419  -0.0962   0.2403   1.0000
   8.250   1.3586   0.02444   0.01538  -0.0940   0.1714   1.0000
   8.500   1.3687   0.02608   0.01680  -0.0921   0.1360   1.0000
   8.750   1.3800   0.02754   0.01819  -0.0902   0.1132   1.0000
   9.000   1.3898   0.02907   0.01967  -0.0883   0.0911   1.0000
   9.250   1.3988   0.03062   0.02116  -0.0862   0.0647   1.0000
   9.500   1.4025   0.03240   0.02287  -0.0834   0.0489   1.0000
   9.750   1.4032   0.03437   0.02480  -0.0806   0.0412   1.0000
  10.000   1.4049   0.03633   0.02685  -0.0781   0.0362   1.0000
  10.250   1.4037   0.03863   0.02921  -0.0758   0.0332   1.0000
  10.500   1.4051   0.04083   0.03164  -0.0738   0.0310   1.0000
  10.750   1.4057   0.04319   0.03416  -0.0720   0.0293   1.0000
  11.000   1.4055   0.04573   0.03682  -0.0705   0.0277   1.0000
  11.250   1.4028   0.04861   0.03979  -0.0691   0.0263   1.0000
  11.500   1.4018   0.05142   0.04273  -0.0677   0.0251   1.0000
  11.750   1.4034   0.05404   0.04554  -0.0665   0.0238   1.0000
  12.000   1.4040   0.05682   0.04850  -0.0654   0.0229   1.0000
  12.250   1.4045   0.05969   0.05153  -0.0642   0.0221   1.0000
  12.500   1.4049   0.06264   0.05463  -0.0632   0.0215   1.0000
  12.750   1.4049   0.06569   0.05784  -0.0622   0.0209   1.0000
  13.000   1.4042   0.06888   0.06117  -0.0615   0.0203   1.0000
  13.250   1.4019   0.07229   0.06471  -0.0610   0.0197   1.0000
  13.500   1.3987   0.07592   0.06845  -0.0606   0.0191   1.0000
  13.750   1.3943   0.07992   0.07263  -0.0601   0.0185   1.0000
  14.000   1.3881   0.08417   0.07715  -0.0605   0.0182   1.0000
  14.250   1.3804   0.08880   0.08205  -0.0613   0.0179   1.0000
  14.500   1.3711   0.09387   0.08739  -0.0625   0.0176   1.0000
  14.750   1.3607   0.09936   0.09313  -0.0642   0.0174   1.0000
  15.000   1.3488   0.10536   0.09938  -0.0665   0.0173   1.0000
  15.250   1.3358   0.11188   0.10614  -0.0694   0.0172   1.0000
  15.500   1.3216   0.11894   0.11343  -0.0729   0.0172   1.0000
  15.750   1.3063   0.12658   0.12129  -0.0772   0.0172   1.0000
  16.000   1.2902   0.13485   0.12977  -0.0821   0.0173   1.0000
  16.250   1.2730   0.14395   0.13906  -0.0879   0.0174   1.0000
  16.500   1.2550   0.15392   0.14921  -0.0944   0.0175   1.0000
  16.750   1.2363   0.16495   0.16033  -0.1018   0.0178   1.0000
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