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GOE 393 AIRFOIL (goe393-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 393 AIRFOIL (goe393-il)
Reynolds number: 500,000
Max Cl/Cd: 101.32 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe393-il-500000.txt
Download as CSV file: xf-goe393-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 393 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4792   0.10111   0.09896   0.0176   1.0000   0.0221
  -8.000  -0.4725   0.09793   0.09581   0.0158   1.0000   0.0228
  -7.750  -0.4661   0.09459   0.09248   0.0136   1.0000   0.0239
  -7.500  -0.4578   0.09050   0.08842   0.0052   1.0000   0.0252
  -7.250  -0.4422   0.08604   0.08395  -0.0018   1.0000   0.0254
  -7.000  -0.4255   0.08141   0.07931  -0.0073   1.0000   0.0255
  -6.750  -0.4204   0.07620   0.07411  -0.0078   1.0000   0.0261
  -6.500  -0.4056   0.07354   0.07145  -0.0086   1.0000   0.0266
  -6.250  -0.3882   0.07060   0.06851  -0.0110   1.0000   0.0273
  -6.000  -0.3683   0.06730   0.06520  -0.0144   1.0000   0.0285
  -5.500  -0.3008   0.05760   0.05528  -0.0303   1.0000   0.0323
  -5.250  -0.2882   0.05210   0.04977  -0.0325   1.0000   0.0335
  -5.000  -0.2581   0.04970   0.04734  -0.0354   0.9694   0.0344
  -4.750  -0.2330   0.04734   0.04471  -0.0369   0.8608   0.0360
  -4.500  -0.1943   0.04400   0.04079  -0.0409   0.7847   0.0407
  -4.250  -0.1745   0.03859   0.03509  -0.0433   0.7511   0.0422
  -4.000  -0.1518   0.03724   0.03357  -0.0435   0.7256   0.0432
  -3.750  -0.1264   0.03558   0.03175  -0.0442   0.7062   0.0448
  -3.500  -0.0869   0.03302   0.02875  -0.0461   0.6915   0.0505
  -3.250  -0.0589   0.02067   0.01548  -0.0488   0.6835   0.0409
  -3.000  -0.0327   0.01518   0.00920  -0.0493   0.6721   0.0390
  -2.750  -0.0051   0.01380   0.00748  -0.0491   0.6599   0.0395
  -2.500   0.0226   0.01299   0.00643  -0.0489   0.6487   0.0402
  -2.250   0.0503   0.01225   0.00545  -0.0486   0.6385   0.0405
  -2.000   0.0781   0.01161   0.00467  -0.0484   0.6284   0.0409
  -1.750   0.1056   0.01077   0.00365  -0.0481   0.6192   0.0418
  -1.500   0.1331   0.01030   0.00308  -0.0478   0.6098   0.0429
  -1.250   0.1609   0.00998   0.00272  -0.0476   0.6007   0.0443
  -1.000   0.1886   0.00979   0.00248  -0.0474   0.5924   0.0462
  -0.750   0.2166   0.00961   0.00227  -0.0472   0.5838   0.0487
  -0.500   0.2445   0.00944   0.00203  -0.0469   0.5760   0.0517
  -0.250   0.2725   0.00929   0.00192  -0.0467   0.5676   0.0598
   0.000   0.3006   0.00931   0.00200  -0.0465   0.5595   0.0790
   0.250   0.3287   0.00943   0.00209  -0.0464   0.5507   0.0908
   0.500   0.3569   0.00953   0.00216  -0.0462   0.5424   0.0978
   0.750   0.3847   0.00953   0.00213  -0.0461   0.5342   0.1032
   1.000   0.4127   0.00955   0.00217  -0.0459   0.5257   0.1095
   1.500   0.4683   0.00949   0.00208  -0.0456   0.5086   0.1169
   1.750   0.4961   0.00946   0.00206  -0.0455   0.4998   0.1219
   2.000   0.5238   0.00948   0.00206  -0.0453   0.4890   0.1269
   2.250   0.5516   0.00941   0.00201  -0.0452   0.4777   0.1318
   2.500   0.5794   0.00940   0.00201  -0.0450   0.4675   0.1365
   2.750   0.6071   0.00943   0.00201  -0.0449   0.4568   0.1416
   3.000   0.6348   0.00942   0.00204  -0.0448   0.4446   0.1503
   3.250   0.6625   0.00942   0.00208  -0.0446   0.4325   0.1656
   3.500   0.6904   0.00776   0.00222  -0.0449   0.4197   1.0000
   3.750   0.7179   0.00790   0.00229  -0.0447   0.4072   1.0000
   4.000   0.7453   0.00806   0.00238  -0.0445   0.3971   1.0000
   4.250   0.7727   0.00820   0.00249  -0.0444   0.3871   1.0000
   4.500   0.8001   0.00836   0.00263  -0.0442   0.3776   1.0000
   4.750   0.8273   0.00855   0.00278  -0.0440   0.3686   1.0000
   5.000   0.8546   0.00870   0.00294  -0.0438   0.3586   1.0000
   5.250   0.8818   0.00887   0.00311  -0.0436   0.3496   1.0000
   5.500   0.9088   0.00908   0.00331  -0.0435   0.3396   1.0000
   5.750   0.9358   0.00928   0.00349  -0.0433   0.3258   1.0000
   6.000   0.9625   0.00950   0.00368  -0.0431   0.3041   1.0000
   6.250   0.9889   0.00981   0.00391  -0.0429   0.2767   1.0000
   6.500   1.0142   0.01034   0.00422  -0.0427   0.2228   1.0000
   6.750   1.0368   0.01144   0.00490  -0.0424   0.1500   1.0000
   7.000   1.0614   0.01209   0.00544  -0.0421   0.1251   1.0000
   7.250   1.0866   0.01260   0.00590  -0.0418   0.1086   1.0000
   7.500   1.1117   0.01310   0.00637  -0.0416   0.0956   1.0000
   7.750   1.1366   0.01359   0.00685  -0.0413   0.0832   1.0000
   8.000   1.1606   0.01425   0.00739  -0.0409   0.0611   1.0000
   8.250   1.1820   0.01537   0.00829  -0.0404   0.0340   1.0000
   8.500   1.2049   0.01620   0.00918  -0.0398   0.0281   1.0000
   8.750   1.2259   0.01730   0.01034  -0.0391   0.0244   1.0000
   9.000   1.2487   0.01801   0.01114  -0.0385   0.0226   1.0000
   9.250   1.2704   0.01884   0.01203  -0.0379   0.0209   1.0000
   9.500   1.2872   0.02033   0.01360  -0.0369   0.0191   1.0000
   9.750   1.3072   0.02126   0.01464  -0.0361   0.0182   1.0000
  10.000   1.3265   0.02225   0.01572  -0.0353   0.0173   1.0000
  10.250   1.3444   0.02333   0.01689  -0.0343   0.0165   1.0000
  10.500   1.3610   0.02449   0.01813  -0.0333   0.0158   1.0000
  10.750   1.3751   0.02586   0.01957  -0.0321   0.0152   1.0000
  11.000   1.3829   0.02785   0.02165  -0.0304   0.0146   1.0000
  11.250   1.3877   0.03013   0.02408  -0.0285   0.0142   1.0000
  11.500   1.3984   0.03130   0.02538  -0.0270   0.0138   1.0000
  11.750   1.4054   0.03279   0.02700  -0.0255   0.0134   1.0000
  12.000   1.4104   0.03461   0.02894  -0.0243   0.0131   1.0000
  12.250   1.4141   0.03679   0.03125  -0.0236   0.0127   1.0000
  12.500   1.4171   0.03925   0.03383  -0.0234   0.0125   1.0000
  12.750   1.4194   0.04195   0.03667  -0.0236   0.0122   1.0000
  13.000   1.4207   0.04487   0.03971  -0.0240   0.0120   1.0000
  13.250   1.4209   0.04798   0.04294  -0.0245   0.0118   1.0000
  13.500   1.4198   0.05128   0.04637  -0.0251   0.0116   1.0000
  13.750   1.4171   0.05480   0.05001  -0.0258   0.0114   1.0000
  14.000   1.4127   0.05861   0.05394  -0.0266   0.0113   1.0000
  14.250   1.4063   0.06270   0.05815  -0.0275   0.0112   1.0000
  14.500   1.3978   0.06716   0.06275  -0.0286   0.0111   1.0000
  14.750   1.3870   0.07203   0.06777  -0.0299   0.0110   1.0000
  15.000   1.3741   0.07737   0.07326  -0.0316   0.0109   1.0000
  15.250   1.3600   0.08300   0.07906  -0.0337   0.0109   1.0000
  15.500   1.3446   0.08916   0.08538  -0.0363   0.0109   1.0000
  15.750   1.3289   0.09573   0.09212  -0.0394   0.0108   1.0000
  16.000   1.3132   0.10263   0.09918  -0.0429   0.0108   1.0000
  16.250   1.2982   0.10973   0.10644  -0.0467   0.0109   1.0000
  16.500   1.2827   0.11721   0.11407  -0.0509   0.0109   1.0000
  16.750   1.2663   0.12522   0.12223  -0.0556   0.0109   1.0000
  17.000   1.2493   0.13378   0.13095  -0.0607   0.0110   1.0000
  17.250   1.2290   0.14379   0.14114  -0.0669   0.0111   1.0000
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