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GOE 381 AIRFOIL (goe381-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 381 AIRFOIL (goe381-il)
Reynolds number: 200,000
Max Cl/Cd: 80.02 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe381-il-200000.txt
Download as CSV file: xf-goe381-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 381 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2907   0.10503   0.10184  -0.0247   1.0000   0.0224
  -7.750  -0.2895   0.10332   0.10020  -0.0262   1.0000   0.0225
  -7.500  -0.2912   0.10183   0.09877  -0.0267   1.0000   0.0225
  -6.250  -0.2862   0.08778   0.08492  -0.0254   0.9970   0.0230
  -6.000  -0.2675   0.08246   0.07961  -0.0268   0.9941   0.0236
  -5.750  -0.2414   0.07804   0.07516  -0.0316   0.9891   0.0243
  -5.500  -0.2082   0.07362   0.07071  -0.0386   0.9846   0.0252
  -5.250  -0.1741   0.06942   0.06646  -0.0457   0.9791   0.0266
  -5.000  -0.1323   0.06531   0.06225  -0.0543   0.9734   0.0292
  -4.750  -0.0542   0.06270   0.05935  -0.0711   0.9695   0.0311
  -4.500  -0.0172   0.05849   0.05502  -0.0767   0.9623   0.0314
  -4.250   0.0030   0.05181   0.04840  -0.0795   0.9586   0.0327
  -4.000   0.0398   0.04793   0.04447  -0.0843   0.9555   0.0344
  -3.750   0.0735   0.04486   0.04130  -0.0880   0.9469   0.0370
  -3.500   0.1397   0.04386   0.03977  -0.0956   0.9419   0.0425
  -3.250   0.1556   0.03836   0.03438  -0.0969   0.9324   0.0447
  -3.000   0.1857   0.03579   0.03173  -0.0986   0.9247   0.0482
  -2.750   0.2307   0.03490   0.03031  -0.1005   0.9143   0.0552
  -2.000   0.3018   0.02751   0.02261  -0.1001   0.8762   0.0706
  -1.750   0.3341   0.02832   0.02295  -0.0989   0.8616   0.0808
  -1.500   0.3556   0.02437   0.01901  -0.0990   0.8470   0.0835
  -1.250   0.3854   0.02465   0.01883  -0.0979   0.8304   0.0948
  -1.000   0.4076   0.02149   0.01570  -0.0978   0.8133   0.0986
  -0.750   0.4364   0.02103   0.01484  -0.0969   0.7926   0.1087
   0.250   0.5489   0.01604   0.00870  -0.0942   0.7164   0.0784
   0.750   0.6042   0.01421   0.00625  -0.0928   0.6797   0.0678
   1.000   0.6307   0.01353   0.00541  -0.0922   0.6612   0.0684
   1.250   0.6568   0.01326   0.00504  -0.0918   0.6432   0.0726
   1.500   0.6831   0.01305   0.00472  -0.0913   0.6263   0.0763
   1.750   0.7094   0.01279   0.00437  -0.0908   0.6109   0.0788
   2.000   0.7358   0.01257   0.00412  -0.0904   0.5973   0.0839
   2.250   0.7624   0.01248   0.00401  -0.0901   0.5840   0.0997
   2.500   0.7889   0.01237   0.00387  -0.0898   0.5708   0.1482
   2.750   0.8146   0.01204   0.00392  -0.0897   0.5573   0.3600
   3.000   0.8396   0.01105   0.00397  -0.0889   0.5435   1.0000
   3.250   0.8657   0.01127   0.00406  -0.0885   0.5284   1.0000
   3.500   0.8915   0.01149   0.00419  -0.0881   0.5118   1.0000
   3.750   0.9173   0.01169   0.00432  -0.0877   0.4936   1.0000
   4.000   0.9428   0.01191   0.00446  -0.0873   0.4741   1.0000
   4.250   0.9682   0.01215   0.00462  -0.0868   0.4527   1.0000
   4.500   0.9930   0.01241   0.00482  -0.0863   0.4271   1.0000
   4.750   1.0174   0.01274   0.00502  -0.0858   0.3978   1.0000
   5.000   1.0412   0.01315   0.00529  -0.0852   0.3711   1.0000
   5.250   1.0648   0.01361   0.00561  -0.0846   0.3458   1.0000
   5.500   1.0879   0.01411   0.00596  -0.0841   0.3212   1.0000
   5.750   1.1115   0.01458   0.00639  -0.0835   0.3044   1.0000
   6.000   1.1344   0.01510   0.00680  -0.0830   0.2842   1.0000
   6.250   1.1575   0.01557   0.00720  -0.0824   0.2629   1.0000
   6.500   1.1806   0.01605   0.00763  -0.0819   0.2457   1.0000
   6.750   1.2035   0.01653   0.00809  -0.0813   0.2230   1.0000
   7.000   1.2259   0.01707   0.00856  -0.0807   0.1959   1.0000
   7.250   1.2465   0.01784   0.00909  -0.0798   0.1477   1.0000
   7.500   1.2623   0.01921   0.01010  -0.0784   0.1060   1.0000
   7.750   1.2726   0.02124   0.01171  -0.0763   0.0316   1.0000
   8.000   1.2911   0.02222   0.01282  -0.0749   0.0272   1.0000
   8.250   1.3088   0.02326   0.01406  -0.0735   0.0251   1.0000
   8.500   1.3246   0.02446   0.01550  -0.0718   0.0239   1.0000
   8.750   1.3368   0.02589   0.01719  -0.0697   0.0232   1.0000
   9.000   1.3459   0.02742   0.01891  -0.0673   0.0230   1.0000
   9.250   1.3520   0.02892   0.02058  -0.0646   0.0227   1.0000
   9.500   1.3557   0.03047   0.02226  -0.0617   0.0220   1.0000
   9.750   1.3576   0.03225   0.02415  -0.0590   0.0214   1.0000
  10.000   1.3580   0.03430   0.02633  -0.0564   0.0212   1.0000
  10.250   1.3589   0.03651   0.02862  -0.0540   0.0211   1.0000
  10.500   1.3615   0.03876   0.03096  -0.0519   0.0212   1.0000
  10.750   1.3672   0.04101   0.03327  -0.0499   0.0214   1.0000
  11.000   1.3791   0.04321   0.03549  -0.0479   0.0219   1.0000
  11.250   1.2373   0.03821   0.03127  -0.0358   0.0216   1.0000
  11.500   1.2477   0.04097   0.03405  -0.0336   0.0220   1.0000
  11.750   1.5138   0.05182   0.04456  -0.0487   0.0327   1.0000
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