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GOE 413 AIRFOIL (goe413-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 413 AIRFOIL (goe413-il)
Reynolds number: 200,000
Max Cl/Cd: 74.53 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe413-il-200000-n5.txt
Download as CSV file: xf-goe413-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 413 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.5854   0.04867   0.04342  -0.0960   0.8919   0.0477
 -11.000  -0.5980   0.04361   0.03804  -0.1029   0.8783   0.0478
 -10.750  -0.5938   0.04075   0.03492  -0.1054   0.8690   0.0481
 -10.500  -0.5845   0.03838   0.03230  -0.1070   0.8603   0.0484
 -10.250  -0.5718   0.03631   0.02996  -0.1079   0.8534   0.0487
 -10.000  -0.5555   0.03444   0.02786  -0.1087   0.8455   0.0490
  -9.750  -0.5377   0.03280   0.02597  -0.1092   0.8381   0.0494
  -9.500  -0.5179   0.03132   0.02424  -0.1095   0.8311   0.0497
  -9.250  -0.4966   0.02997   0.02267  -0.1099   0.8232   0.0501
  -9.000  -0.4745   0.02878   0.02123  -0.1100   0.8164   0.0505
  -8.750  -0.4510   0.02772   0.01993  -0.1102   0.8093   0.0510
  -8.500  -0.4269   0.02673   0.01874  -0.1103   0.8015   0.0515
  -8.250  -0.4024   0.02570   0.01766  -0.1102   0.7947   0.0519
  -8.000  -0.3769   0.02481   0.01674  -0.1102   0.7861   0.0524
  -7.750  -0.3514   0.02400   0.01586  -0.1101   0.7780   0.0529
  -7.500  -0.3254   0.02324   0.01502  -0.1101   0.7700   0.0533
  -7.250  -0.2991   0.02251   0.01422  -0.1101   0.7613   0.0538
  -7.000  -0.2727   0.02184   0.01345  -0.1100   0.7534   0.0543
  -6.750  -0.2459   0.02119   0.01275  -0.1100   0.7435   0.0548
  -6.500  -0.2191   0.02059   0.01205  -0.1099   0.7347   0.0553
  -6.250  -0.1919   0.02005   0.01143  -0.1099   0.7244   0.0559
  -6.000  -0.1645   0.01957   0.01084  -0.1098   0.7157   0.0566
  -5.750  -0.1374   0.01899   0.01024  -0.1098   0.7060   0.0573
  -5.500  -0.1105   0.01842   0.00967  -0.1097   0.6976   0.0581
  -5.250  -0.0830   0.01794   0.00918  -0.1098   0.6881   0.0588
  -4.750  -0.0275   0.01714   0.00828  -0.1098   0.6716   0.0602
  -4.500   0.0005   0.01680   0.00786  -0.1099   0.6644   0.0610
  -4.250   0.0288   0.01650   0.00750  -0.1100   0.6578   0.0618
  -4.000   0.0574   0.01623   0.00717  -0.1101   0.6507   0.0627
  -3.750   0.0857   0.01591   0.00679  -0.1102   0.6442   0.0638
  -3.500   0.1144   0.01564   0.00647  -0.1104   0.6383   0.0653
  -3.250   0.1433   0.01541   0.00620  -0.1106   0.6323   0.0670
  -3.000   0.1721   0.01524   0.00595  -0.1107   0.6266   0.0686
  -2.500   0.2301   0.01487   0.00550  -0.1110   0.6159   0.0729
  -2.250   0.2591   0.01471   0.00533  -0.1112   0.6105   0.0765
  -2.000   0.2880   0.01446   0.00513  -0.1114   0.6053   0.0878
  -1.750   0.3168   0.01416   0.00506  -0.1117   0.6005   0.1493
  -1.500   0.3459   0.01406   0.00506  -0.1119   0.5950   0.1729
  -1.250   0.3748   0.01401   0.00503  -0.1120   0.5893   0.1902
  -1.000   0.4037   0.01399   0.00500  -0.1121   0.5841   0.2035
  -0.750   0.4326   0.01398   0.00499  -0.1122   0.5792   0.2175
  -0.500   0.4616   0.01393   0.00502  -0.1123   0.5737   0.2354
  -0.250   0.4904   0.01390   0.00504  -0.1124   0.5685   0.2531
   0.000   0.5193   0.01390   0.00505  -0.1125   0.5639   0.2727
   0.250   0.5481   0.01390   0.00510  -0.1126   0.5594   0.2950
   0.500   0.5769   0.01387   0.00518  -0.1127   0.5541   0.3187
   0.750   0.6056   0.01387   0.00525  -0.1128   0.5489   0.3438
   1.000   0.6343   0.01389   0.00530  -0.1129   0.5443   0.3706
   1.250   0.6628   0.01389   0.00538  -0.1129   0.5398   0.4001
   1.500   0.6913   0.01387   0.00551  -0.1130   0.5342   0.4333
   1.750   0.7195   0.01385   0.00563  -0.1130   0.5289   0.4719
   2.000   0.7476   0.01387   0.00574  -0.1129   0.5242   0.5123
   2.250   0.7757   0.01391   0.00587  -0.1128   0.5192   0.5475
   2.500   0.8036   0.01394   0.00601  -0.1127   0.5133   0.5800
   2.750   0.8310   0.01397   0.00611  -0.1125   0.5078   0.6126
   3.000   0.8577   0.01398   0.00622  -0.1121   0.5030   0.6509
   3.250   0.8828   0.01392   0.00643  -0.1113   0.4970   0.7112
   3.500   0.9051   0.01384   0.00657  -0.1098   0.4906   0.8012
   3.750   0.9259   0.01364   0.00652  -0.1077   0.4846   0.9781
   4.000   0.9542   0.01379   0.00666  -0.1078   0.4763   1.0000
   4.250   0.9814   0.01397   0.00675  -0.1077   0.4677   1.0000
   4.500   1.0086   0.01415   0.00691  -0.1076   0.4589   1.0000
   4.750   1.0354   0.01436   0.00705  -0.1074   0.4503   1.0000
   5.000   1.0620   0.01457   0.00724  -0.1072   0.4412   1.0000
   5.250   1.0878   0.01481   0.00741  -0.1069   0.4311   1.0000
   5.500   1.1137   0.01506   0.00763  -0.1066   0.4210   1.0000
   6.000   1.1641   0.01562   0.00812  -0.1058   0.4017   1.0000
   6.250   1.1882   0.01595   0.00839  -0.1053   0.3914   1.0000
   6.500   1.2119   0.01630   0.00869  -0.1047   0.3801   1.0000
   6.750   1.2352   0.01667   0.00903  -0.1041   0.3700   1.0000
   7.000   1.2571   0.01710   0.00939  -0.1033   0.3595   1.0000
   7.250   1.2794   0.01751   0.00979  -0.1025   0.3489   1.0000
   7.500   1.2997   0.01800   0.01022  -0.1015   0.3384   1.0000
   7.750   1.3196   0.01851   0.01069  -0.1005   0.3273   1.0000
   8.000   1.3390   0.01902   0.01119  -0.0994   0.3179   1.0000
   8.250   1.3563   0.01961   0.01174  -0.0980   0.3082   1.0000
   8.500   1.3727   0.02017   0.01230  -0.0965   0.2992   1.0000
   8.750   1.3865   0.02089   0.01299  -0.0948   0.2897   1.0000
   9.000   1.4014   0.02160   0.01372  -0.0933   0.2788   1.0000
   9.250   1.4141   0.02247   0.01457  -0.0917   0.2690   1.0000
   9.500   1.4261   0.02343   0.01551  -0.0902   0.2577   1.0000
   9.750   1.4371   0.02450   0.01657  -0.0887   0.2453   1.0000
  10.000   1.4448   0.02584   0.01788  -0.0871   0.2303   1.0000
  10.250   1.4493   0.02748   0.01945  -0.0855   0.2125   1.0000
  10.500   1.4515   0.02939   0.02128  -0.0838   0.1941   1.0000
  10.750   1.4502   0.03166   0.02346  -0.0822   0.1723   1.0000
  11.000   1.4415   0.03468   0.02633  -0.0804   0.1440   1.0000
  11.250   1.4240   0.03866   0.03009  -0.0785   0.1099   1.0000
  11.500   1.4155   0.04201   0.03336  -0.0773   0.0956   1.0000
  11.750   1.4131   0.04488   0.03623  -0.0765   0.0895   1.0000
  12.000   1.4117   0.04771   0.03910  -0.0757   0.0857   1.0000
  12.250   1.4119   0.05047   0.04191  -0.0752   0.0833   1.0000
  12.500   1.4129   0.05324   0.04474  -0.0748   0.0814   1.0000
  12.750   1.4131   0.05615   0.04773  -0.0744   0.0798   1.0000
  13.000   1.4124   0.05922   0.05088  -0.0742   0.0784   1.0000
  13.250   1.4107   0.06247   0.05419  -0.0740   0.0773   1.0000
  13.500   1.4079   0.06590   0.05769  -0.0739   0.0764   1.0000
  13.750   1.4066   0.06920   0.06107  -0.0739   0.0756   1.0000
  14.000   1.4065   0.07236   0.06431  -0.0739   0.0749   1.0000
  14.250   1.4059   0.07563   0.06768  -0.0740   0.0742   1.0000
  14.500   1.4053   0.07894   0.07108  -0.0741   0.0736   1.0000
  14.750   1.4046   0.08228   0.07449  -0.0743   0.0730   1.0000
  15.000   1.4039   0.08563   0.07793  -0.0745   0.0724   1.0000
  15.250   1.4038   0.08892   0.08128  -0.0748   0.0718   1.0000
  15.500   1.4038   0.09222   0.08464  -0.0751   0.0713   1.0000
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