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GOE 591 AIRFOIL (goe591-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 591 AIRFOIL (goe591-il)
Reynolds number: 200,000
Max Cl/Cd: 77.18 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe591-il-200000.txt
Download as CSV file: xf-goe591-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 591 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2966   0.10340   0.10017  -0.0338   1.0000   0.0485
  -8.750  -0.3128   0.10253   0.09940  -0.0310   1.0000   0.0495
  -8.500  -0.3195   0.09991   0.09682  -0.0379   0.9959   0.0512
  -8.250  -0.3115   0.09480   0.09172  -0.0524   0.9855   0.0517
  -8.000  -0.2870   0.08969   0.08661  -0.0473   0.9864   0.0531
  -7.750  -0.2614   0.08623   0.08312  -0.0499   0.9836   0.0551
  -7.500  -0.2450   0.08259   0.07947  -0.0545   0.9756   0.0574
  -7.250  -0.2217   0.07447   0.07118  -0.0813   0.9591   0.0625
  -7.000  -0.2051   0.06957   0.06637  -0.0795   0.9574   0.0641
  -6.750  -0.1853   0.06717   0.06397  -0.0790   0.9511   0.0659
  -6.500  -0.1588   0.06328   0.06002  -0.0842   0.9452   0.0691
  -6.250  -0.1331   0.05472   0.05097  -0.1002   0.9335   0.0759
  -6.000  -0.1060   0.05145   0.04782  -0.1011   0.9305   0.0777
  -5.750  -0.0742   0.04897   0.04532  -0.1035   0.9274   0.0818
  -5.500  -0.0549   0.04361   0.03936  -0.1088   0.9157   0.0906
  -5.250  -0.0251   0.04046   0.03628  -0.1106   0.9122   0.0926
  -5.000  -0.0052   0.03844   0.03420  -0.1103   0.9028   0.0955
  -4.750   0.0162   0.02667   0.02071  -0.1116   0.8963   0.0634
  -4.500   0.0377   0.02481   0.01860  -0.1104   0.8865   0.0618
  -4.250   0.0690   0.02253   0.01590  -0.1111   0.8816   0.0620
  -4.000   0.0918   0.02118   0.01422  -0.1099   0.8721   0.0628
  -3.750   0.1231   0.01921   0.01194  -0.1104   0.8666   0.0634
  -3.500   0.1470   0.01797   0.01055  -0.1095   0.8570   0.0644
  -3.250   0.1789   0.01694   0.00939  -0.1099   0.8509   0.0661
  -3.000   0.2033   0.01643   0.00882  -0.1090   0.8407   0.0692
  -2.750   0.2324   0.01580   0.00805  -0.1088   0.8330   0.0722
  -2.500   0.2593   0.01527   0.00740  -0.1082   0.8236   0.0747
  -2.250   0.2846   0.01448   0.00663  -0.1075   0.8144   0.0791
  -2.000   0.3125   0.01403   0.00613  -0.1072   0.8059   0.0867
  -1.750   0.3363   0.01356   0.00571  -0.1062   0.7956   0.1009
  -1.500   0.3621   0.01299   0.00527  -0.1055   0.7868   0.1397
  -1.250   0.3872   0.01272   0.00511  -0.1048   0.7765   0.1832
  -1.000   0.4113   0.01241   0.00497  -0.1040   0.7662   0.2412
  -0.750   0.4340   0.01170   0.00485  -0.1031   0.7574   0.4110
  -0.500   0.5290   0.01025   0.00472  -0.1161   0.7471   1.0000
  -0.250   0.5521   0.01032   0.00463  -0.1150   0.7361   1.0000
   0.000   0.5764   0.01038   0.00452  -0.1141   0.7258   1.0000
   0.250   0.5992   0.01045   0.00446  -0.1129   0.7141   1.0000
   0.500   0.6219   0.01054   0.00444  -0.1117   0.7024   1.0000
   0.750   0.6454   0.01064   0.00441  -0.1107   0.6911   1.0000
   1.000   0.6697   0.01074   0.00436  -0.1098   0.6803   1.0000
   1.250   0.6926   0.01085   0.00437  -0.1086   0.6683   1.0000
   1.500   0.7155   0.01098   0.00441  -0.1075   0.6563   1.0000
   1.750   0.7388   0.01111   0.00444  -0.1065   0.6446   1.0000
   2.000   0.7625   0.01126   0.00447  -0.1055   0.6331   1.0000
   2.250   0.7859   0.01140   0.00451  -0.1045   0.6214   1.0000
   2.500   0.8084   0.01156   0.00461  -0.1034   0.6093   1.0000
   2.750   0.8318   0.01174   0.00473  -0.1024   0.5983   1.0000
   3.000   0.8561   0.01194   0.00482  -0.1016   0.5885   1.0000
   3.250   0.8792   0.01213   0.00497  -0.1006   0.5779   1.0000
   3.500   0.9026   0.01234   0.00514  -0.0997   0.5677   1.0000
   3.750   0.9273   0.01257   0.00528  -0.0991   0.5588   1.0000
   4.000   0.9501   0.01278   0.00550  -0.0981   0.5488   1.0000
   4.250   0.9741   0.01302   0.00570  -0.0973   0.5399   1.0000
   4.500   0.9979   0.01325   0.00588  -0.0966   0.5303   1.0000
   4.750   1.0204   0.01348   0.00612  -0.0955   0.5200   1.0000
   5.000   1.0440   0.01373   0.00632  -0.0947   0.5106   1.0000
   5.250   1.0669   0.01396   0.00656  -0.0938   0.5008   1.0000
   5.500   1.0893   0.01421   0.00683  -0.0928   0.4907   1.0000
   5.750   1.1123   0.01448   0.00705  -0.0919   0.4810   1.0000
   6.000   1.1339   0.01471   0.00729  -0.0908   0.4703   1.0000
   6.250   1.1554   0.01497   0.00760  -0.0896   0.4598   1.0000
   6.500   1.1777   0.01526   0.00787  -0.0886   0.4502   1.0000
   6.750   1.1991   0.01554   0.00818  -0.0875   0.4403   1.0000
   7.000   1.2203   0.01584   0.00854  -0.0863   0.4305   1.0000
   7.250   1.2420   0.01617   0.00885  -0.0853   0.4210   1.0000
   7.500   1.2609   0.01645   0.00918  -0.0837   0.4093   1.0000
   7.750   1.2788   0.01673   0.00952  -0.0820   0.3967   1.0000
   8.000   1.2953   0.01702   0.00985  -0.0800   0.3829   1.0000
   8.250   1.3114   0.01734   0.01019  -0.0780   0.3693   1.0000
   8.500   1.3262   0.01768   0.01055  -0.0758   0.3552   1.0000
   8.750   1.3401   0.01805   0.01094  -0.0735   0.3411   1.0000
   9.000   1.3509   0.01845   0.01134  -0.0706   0.3257   1.0000
   9.250   1.3604   0.01890   0.01181  -0.0676   0.3107   1.0000
   9.500   1.3694   0.01943   0.01235  -0.0646   0.2955   1.0000
   9.750   1.3786   0.02004   0.01296  -0.0618   0.2809   1.0000
  10.000   1.3869   0.02073   0.01365  -0.0590   0.2659   1.0000
  10.250   1.3934   0.02154   0.01444  -0.0561   0.2493   1.0000
  10.500   1.3986   0.02249   0.01537  -0.0532   0.2324   1.0000
  10.750   1.4038   0.02352   0.01639  -0.0505   0.2165   1.0000
  11.000   1.4071   0.02473   0.01757  -0.0479   0.1946   1.0000
  11.250   1.4073   0.02624   0.01899  -0.0451   0.1697   1.0000
  11.500   1.4030   0.02818   0.02078  -0.0423   0.1410   1.0000
  11.750   1.3934   0.03071   0.02311  -0.0394   0.1112   1.0000
  12.000   1.3791   0.03383   0.02596  -0.0367   0.0681   1.0000
  12.250   1.3619   0.03745   0.02939  -0.0342   0.0482   1.0000
  12.500   1.3538   0.04051   0.03247  -0.0326   0.0403   1.0000
  12.750   1.3490   0.04340   0.03544  -0.0314   0.0361   1.0000
  13.000   1.3428   0.04659   0.03871  -0.0305   0.0338   1.0000
  13.250   1.3402   0.04954   0.04181  -0.0299   0.0322   1.0000
  13.500   1.3358   0.05281   0.04522  -0.0296   0.0308   1.0000
  13.750   1.3301   0.05638   0.04892  -0.0294   0.0297   1.0000
  14.000   1.3231   0.06025   0.05290  -0.0296   0.0289   1.0000
  14.250   1.3147   0.06444   0.05720  -0.0300   0.0282   1.0000
  14.500   1.3032   0.06916   0.06202  -0.0306   0.0276   1.0000
  14.750   1.2972   0.07326   0.06623  -0.0312   0.0270   1.0000
  15.000   1.2934   0.07713   0.07022  -0.0319   0.0263   1.0000
  15.250   1.2896   0.08101   0.07421  -0.0325   0.0259   1.0000
  15.500   1.2866   0.08487   0.07816  -0.0332   0.0252   1.0000
  15.750   1.2848   0.08849   0.08186  -0.0339   0.0247   1.0000
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