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GOE 401 AIRFOIL (goe401-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 401 AIRFOIL (goe401-il)
Reynolds number: 200,000
Max Cl/Cd: 75.4 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe401-il-200000-n5.txt
Download as CSV file: xf-goe401-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 401 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  -0.3067   0.09295   0.08952  -0.0231   1.0000   0.0262
  -7.500  -0.3141   0.09122   0.08787  -0.0234   1.0000   0.0264
  -7.250  -0.3161   0.08882   0.08554  -0.0249   1.0000   0.0265
  -7.000  -0.3144   0.08613   0.08290  -0.0270   1.0000   0.0266
  -6.750  -0.3090   0.08304   0.07984  -0.0288   0.9995   0.0267
  -6.500  -0.2801   0.07786   0.07462  -0.0363   0.9915   0.0267
  -6.250  -0.2531   0.07294   0.06963  -0.0427   0.9805   0.0267
  -6.000  -0.2281   0.06822   0.06486  -0.0480   0.9656   0.0267
  -5.750  -0.2016   0.06351   0.06007  -0.0530   0.9509   0.0267
  -5.500  -0.1843   0.06125   0.05786  -0.0523   0.9384   0.0285
  -5.250  -0.1270   0.05634   0.05265  -0.0659   0.9245   0.0340
  -5.000  -0.1012   0.05165   0.04794  -0.0696   0.9128   0.0352
  -4.750  -0.0685   0.04875   0.04495  -0.0733   0.9009   0.0369
  -4.500  -0.0307   0.04527   0.04127  -0.0786   0.8866   0.0404
  -4.250   0.0053   0.04134   0.03709  -0.0835   0.8706   0.0452
  -4.000   0.0428   0.03869   0.03403  -0.0871   0.8546   0.0536
  -3.750   0.0639   0.03632   0.03163  -0.0875   0.8390   0.0548
  -3.500   0.0873   0.03481   0.03002  -0.0877   0.8233   0.0578
  -3.250   0.1202   0.02835   0.02276  -0.0887   0.8102   0.0436
  -3.000   0.1437   0.02603   0.02015  -0.0884   0.7954   0.0439
  -2.750   0.1693   0.02434   0.01815  -0.0879   0.7810   0.0432
  -2.500   0.1927   0.02253   0.01614  -0.0874   0.7666   0.0424
  -2.250   0.2170   0.02078   0.01408  -0.0867   0.7520   0.0418
  -2.000   0.2417   0.01918   0.01213  -0.0859   0.7370   0.0413
  -1.750   0.2667   0.01780   0.01041  -0.0851   0.7217   0.0411
  -1.500   0.2920   0.01673   0.00902  -0.0843   0.7057   0.0410
  -1.250   0.3173   0.01590   0.00791  -0.0835   0.6885   0.0411
  -1.000   0.3427   0.01533   0.00710  -0.0828   0.6702   0.0419
  -0.750   0.3680   0.01483   0.00637  -0.0820   0.6507   0.0423
  -0.500   0.3931   0.01434   0.00570  -0.0812   0.6298   0.0421
  -0.250   0.4180   0.01395   0.00515  -0.0803   0.6072   0.0419
   0.000   0.4426   0.01364   0.00468  -0.0794   0.5837   0.0418
   0.250   0.4669   0.01341   0.00430  -0.0785   0.5604   0.0418
   0.500   0.4912   0.01323   0.00401  -0.0776   0.5377   0.0417
   0.750   0.5153   0.01312   0.00377  -0.0767   0.5177   0.0418
   1.000   0.5395   0.01305   0.00359  -0.0758   0.5002   0.0419
   1.250   0.5639   0.01302   0.00346  -0.0750   0.4852   0.0421
   1.500   0.5886   0.01302   0.00338  -0.0743   0.4722   0.0424
   1.750   0.6135   0.01304   0.00333  -0.0736   0.4609   0.0428
   2.000   0.6384   0.01309   0.00331  -0.0729   0.4511   0.0434
   2.250   0.6633   0.01314   0.00331  -0.0722   0.4419   0.0449
   2.500   0.6885   0.01320   0.00335  -0.0715   0.4336   0.0474
   2.750   0.7134   0.01329   0.00343  -0.0709   0.4259   0.0520
   3.000   0.7385   0.01332   0.00358  -0.0703   0.4186   0.0949
   3.250   0.7634   0.01340   0.00376  -0.0697   0.4114   0.1566
   3.500   0.8228   0.01210   0.00406  -0.0770   0.4019   1.0000
   3.750   0.8473   0.01233   0.00420  -0.0763   0.3952   1.0000
   4.000   0.8722   0.01252   0.00437  -0.0757   0.3883   1.0000
   4.250   0.8968   0.01274   0.00456  -0.0750   0.3817   1.0000
   4.500   0.9215   0.01296   0.00476  -0.0743   0.3754   1.0000
   4.750   0.9460   0.01317   0.00495  -0.0736   0.3680   1.0000
   5.000   0.9701   0.01339   0.00515  -0.0728   0.3596   1.0000
   5.250   0.9940   0.01361   0.00537  -0.0721   0.3502   1.0000
   5.500   1.0183   0.01382   0.00560  -0.0713   0.3416   1.0000
   5.750   1.0418   0.01408   0.00583  -0.0705   0.3338   1.0000
   6.000   1.0659   0.01429   0.00609  -0.0698   0.3241   1.0000
   6.250   1.0892   0.01453   0.00636  -0.0690   0.3138   1.0000
   6.500   1.1121   0.01480   0.00662  -0.0681   0.3027   1.0000
   6.750   1.1351   0.01508   0.00692  -0.0672   0.2922   1.0000
   7.000   1.1582   0.01536   0.00725  -0.0664   0.2829   1.0000
   7.250   1.1804   0.01568   0.00760  -0.0654   0.2719   1.0000
   7.500   1.2021   0.01604   0.00795  -0.0644   0.2596   1.0000
   8.000   1.2443   0.01683   0.00876  -0.0622   0.2327   1.0000
   8.250   1.2649   0.01727   0.00922  -0.0611   0.2190   1.0000
   8.500   1.2845   0.01777   0.00975  -0.0598   0.2029   1.0000
   8.750   1.3018   0.01844   0.01034  -0.0583   0.1762   1.0000
   9.000   1.3160   0.01936   0.01108  -0.0564   0.1376   1.0000
   9.250   1.3226   0.02089   0.01226  -0.0536   0.0862   1.0000
   9.500   1.3335   0.02203   0.01332  -0.0513   0.0726   1.0000
   9.750   1.3463   0.02294   0.01431  -0.0492   0.0668   1.0000
  10.000   1.3571   0.02391   0.01535  -0.0468   0.0626   1.0000
  10.250   1.3633   0.02498   0.01648  -0.0438   0.0592   1.0000
  10.500   1.3726   0.02583   0.01748  -0.0412   0.0571   1.0000
  10.750   1.3803   0.02680   0.01857  -0.0387   0.0545   1.0000
  11.000   1.3853   0.02797   0.01984  -0.0360   0.0519   1.0000
  11.250   1.3858   0.02950   0.02143  -0.0333   0.0491   1.0000
  11.500   1.3905   0.03085   0.02291  -0.0312   0.0459   1.0000
  11.750   1.3987   0.03204   0.02424  -0.0297   0.0429   1.0000
  12.000   1.4043   0.03351   0.02581  -0.0283   0.0399   1.0000
  12.250   1.4050   0.03548   0.02785  -0.0269   0.0372   1.0000
  12.500   1.4032   0.03785   0.03032  -0.0258   0.0357   1.0000
  12.750   1.4084   0.03969   0.03233  -0.0250   0.0341   1.0000
  13.000   1.4119   0.04180   0.03459  -0.0245   0.0318   1.0000
  13.250   1.4133   0.04425   0.03715  -0.0242   0.0295   1.0000
  13.500   1.4111   0.04724   0.04024  -0.0242   0.0276   1.0000
  13.750   1.4097   0.05027   0.04340  -0.0244   0.0251   1.0000
  14.000   1.4074   0.05353   0.04679  -0.0248   0.0226   1.0000
  14.250   1.4019   0.05736   0.05068  -0.0257   0.0204   1.0000
  14.500   1.3959   0.06136   0.05481  -0.0266   0.0184   1.0000
  14.750   1.3885   0.06569   0.05924  -0.0277   0.0167   1.0000
  15.000   1.3783   0.07056   0.06419  -0.0292   0.0155   1.0000
  15.250   1.3691   0.07538   0.06913  -0.0307   0.0146   1.0000
  15.500   1.3599   0.08030   0.07417  -0.0323   0.0133   1.0000
  15.750   1.3508   0.08526   0.07925  -0.0340   0.0130   1.0000
  16.000   1.3412   0.09041   0.08451  -0.0359   0.0125   1.0000
  16.250   1.3307   0.09583   0.09002  -0.0379   0.0120   1.0000
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