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GOE 574 AIRFOIL (goe574-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 574 AIRFOIL (goe574-il)
Reynolds number: 100,000
Max Cl/Cd: 55.8 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe574-il-100000-n5.txt
Download as CSV file: xf-goe574-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 574 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3303   0.10957   0.10514  -0.0363   1.0000   0.0339
  -8.250  -0.3333   0.10696   0.10260  -0.0360   1.0000   0.0339
  -8.000  -0.3429   0.10494   0.10069  -0.0356   1.0000   0.0340
  -7.750  -0.3264   0.09862   0.09438  -0.0322   1.0000   0.0357
  -7.500  -0.3309   0.09630   0.09214  -0.0308   1.0000   0.0361
  -7.250  -0.3411   0.09447   0.09041  -0.0291   1.0000   0.0362
  -7.000  -0.3249   0.09036   0.08631  -0.0337   0.9942   0.0373
  -6.750  -0.3034   0.08554   0.08143  -0.0402   0.9860   0.0390
  -6.500  -0.2830   0.08066   0.07652  -0.0467   0.9752   0.0403
  -6.250  -0.2641   0.07598   0.07181  -0.0527   0.9618   0.0420
  -6.000  -0.2384   0.07104   0.06666  -0.0635   0.9406   0.0452
  -5.750  -0.2250   0.06468   0.06026  -0.0641   0.9285   0.0332
  -5.500  -0.2033   0.05969   0.05511  -0.0679   0.9149   0.0334
  -5.250  -0.1787   0.05453   0.04972  -0.0714   0.9042   0.0335
  -5.000  -0.1589   0.05010   0.04514  -0.0730   0.8922   0.0328
  -4.750  -0.1355   0.04557   0.04037  -0.0749   0.8809   0.0321
  -4.500  -0.1084   0.04073   0.03514  -0.0768   0.8705   0.0319
  -4.000  -0.0505   0.03256   0.02601  -0.0796   0.8504   0.0363
  -3.750  -0.0195   0.02926   0.02215  -0.0806   0.8396   0.0373
  -3.500   0.0159   0.02683   0.01917  -0.0822   0.8289   0.0416
  -3.250   0.0551   0.02426   0.01584  -0.0841   0.8182   0.0440
  -3.000   0.0925   0.02224   0.01329  -0.0859   0.8052   0.0471
  -2.750   0.1295   0.02097   0.01172  -0.0879   0.7913   0.0506
  -2.500   0.1656   0.01978   0.01017  -0.0893   0.7769   0.0523
  -2.250   0.1999   0.01887   0.00899  -0.0904   0.7622   0.0542
  -2.000   0.2327   0.01836   0.00822  -0.0913   0.7469   0.0581
  -1.750   0.2628   0.01763   0.00737  -0.0918   0.7315   0.0601
  -1.500   0.2913   0.01714   0.00675  -0.0918   0.7160   0.0614
  -1.250   0.3187   0.01680   0.00625  -0.0916   0.7005   0.0630
  -1.000   0.3460   0.01655   0.00582  -0.0914   0.6854   0.0654
  -0.750   0.3737   0.01638   0.00547  -0.0913   0.6711   0.0691
  -0.500   0.4024   0.01620   0.00519  -0.0914   0.6574   0.0780
  -0.250   0.4326   0.01595   0.00501  -0.0920   0.6443   0.1333
   0.250   0.5995   0.01444   0.00510  -0.1167   0.6140   1.0000
   0.500   0.6230   0.01461   0.00510  -0.1159   0.6026   1.0000
   0.750   0.6464   0.01479   0.00513  -0.1150   0.5923   1.0000
   1.000   0.6706   0.01498   0.00516  -0.1143   0.5837   1.0000
   1.250   0.6940   0.01518   0.00525  -0.1135   0.5752   1.0000
   1.500   0.7179   0.01539   0.00534  -0.1128   0.5678   1.0000
   1.750   0.7413   0.01560   0.00548  -0.1120   0.5605   1.0000
   2.000   0.7652   0.01582   0.00561  -0.1113   0.5541   1.0000
   2.250   0.7882   0.01605   0.00580  -0.1104   0.5473   1.0000
   2.500   0.8126   0.01629   0.00597  -0.1098   0.5419   1.0000
   2.750   0.8354   0.01654   0.00623  -0.1090   0.5360   1.0000
   3.000   0.8592   0.01679   0.00647  -0.1083   0.5311   1.0000
   3.250   0.8842   0.01707   0.00672  -0.1079   0.5271   1.0000
   3.500   0.9066   0.01735   0.00707  -0.1069   0.5222   1.0000
   3.750   0.9299   0.01763   0.00738  -0.1062   0.5175   1.0000
   4.000   0.9545   0.01792   0.00768  -0.1057   0.5136   1.0000
   4.250   0.9770   0.01824   0.00811  -0.1048   0.5094   1.0000
   4.500   0.9997   0.01856   0.00854  -0.1040   0.5053   1.0000
   4.750   1.0233   0.01889   0.00895  -0.1033   0.5016   1.0000
   5.000   1.0485   0.01923   0.00936  -0.1029   0.4983   1.0000
   5.250   1.0683   0.01959   0.00991  -0.1015   0.4935   1.0000
   5.500   1.0890   0.01986   0.01028  -0.1001   0.4865   1.0000
   5.750   1.1022   0.01989   0.01028  -0.0969   0.4697   1.0000
   6.000   1.1062   0.01988   0.01028  -0.0919   0.4457   1.0000
   6.250   1.1182   0.02004   0.01055  -0.0887   0.4300   1.0000
   6.500   1.1268   0.02021   0.01072  -0.0847   0.4098   1.0000
   6.750   1.1310   0.02042   0.01098  -0.0800   0.3814   1.0000
   7.000   1.1341   0.02075   0.01132  -0.0751   0.3356   1.0000
   7.250   1.1183   0.02189   0.01176  -0.0671   0.2348   1.0000
   7.500   1.0976   0.02404   0.01323  -0.0593   0.1402   1.0000
   7.750   1.0726   0.02657   0.01515  -0.0513   0.0428   1.0000
   8.000   1.0715   0.02790   0.01648  -0.0470   0.0326   1.0000
   8.250   1.0732   0.02913   0.01784  -0.0433   0.0290   1.0000
   8.500   1.0731   0.03053   0.01938  -0.0397   0.0271   1.0000
   8.750   1.0738   0.03197   0.02100  -0.0364   0.0258   1.0000
   9.000   1.0734   0.03359   0.02282  -0.0333   0.0240   1.0000
   9.250   1.0716   0.03543   0.02489  -0.0306   0.0224   1.0000
   9.500   1.0688   0.03751   0.02715  -0.0282   0.0215   1.0000
   9.750   1.0637   0.03997   0.02980  -0.0261   0.0208   1.0000
  10.000   1.0580   0.04267   0.03268  -0.0244   0.0204   1.0000
  10.250   1.0521   0.04557   0.03573  -0.0230   0.0199   1.0000
  10.500   1.0468   0.04853   0.03885  -0.0219   0.0197   1.0000
  10.750   1.0420   0.05153   0.04197  -0.0209   0.0193   1.0000
  11.000   1.0367   0.05454   0.04508  -0.0197   0.0187   1.0000
  11.250   1.0370   0.05690   0.04751  -0.0184   0.0184   1.0000
  11.500   1.0451   0.05803   0.04852  -0.0152   0.0170   1.0000
  11.750   1.0583   0.05926   0.04985  -0.0137   0.0164   1.0000
  12.000   1.0784   0.06007   0.05075  -0.0116   0.0158   1.0000
  12.250   1.1034   0.06098   0.05176  -0.0096   0.0155   1.0000
  12.500   1.1265   0.06251   0.05354  -0.0080   0.0152   1.0000
  12.750   1.1465   0.06466   0.05591  -0.0066   0.0151   1.0000
  13.000   1.1572   0.06744   0.05894  -0.0055   0.0150   1.0000
  13.250   1.1609   0.07041   0.06216  -0.0046   0.0150   1.0000
  13.500   1.1593   0.07366   0.06566  -0.0039   0.0147   1.0000
  13.750   1.1548   0.07720   0.06945  -0.0035   0.0144   1.0000
  14.000   1.1487   0.08090   0.07340  -0.0033   0.0144   1.0000
  14.250   1.1398   0.08493   0.07767  -0.0034   0.0142   1.0000
  14.500   1.1287   0.08917   0.08214  -0.0040   0.0139   1.0000
  14.750   1.1171   0.09369   0.08688  -0.0048   0.0138   1.0000
  15.000   1.1038   0.09863   0.09205  -0.0061   0.0138   1.0000
  15.250   1.0900   0.10379   0.09741  -0.0078   0.0137   1.0000
  15.500   1.0758   0.10930   0.10312  -0.0099   0.0138   1.0000
  15.750   1.0618   0.11496   0.10897  -0.0124   0.0139   1.0000
  16.000   1.0458   0.12135   0.11554  -0.0155   0.0141   1.0000
  16.250   1.0304   0.12794   0.12230  -0.0189   0.0141   1.0000
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