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USA 5 AIRFOIL (usa5-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: USA 5 AIRFOIL (usa5-il)
Reynolds number: 1,000,000
Max Cl/Cd: 99.74 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa5-il-1000000-n5.txt
Download as CSV file: xf-usa5-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 5 AIRFOIL                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3567   0.12420   0.12254  -0.0196   1.0000   0.0035
 -10.500  -0.3521   0.12098   0.11933  -0.0204   1.0000   0.0035
  -8.500  -0.3205   0.09756   0.09603  -0.0251   0.9994   0.0042
  -8.000  -0.2955   0.09048   0.08895  -0.0314   0.9915   0.0048
  -7.750  -0.2823   0.08689   0.08537  -0.0350   0.9865   0.0046
  -7.500  -0.2705   0.08313   0.08162  -0.0387   0.9800   0.0046
  -7.250  -0.2538   0.07900   0.07748  -0.0441   0.9726   0.0054
  -7.000  -0.2314   0.07464   0.07311  -0.0508   0.9678   0.0049
  -6.750  -0.2037   0.06771   0.06615  -0.0610   0.9596   0.0034
  -6.500  -0.1757   0.06283   0.06122  -0.0689   0.9507   0.0032
  -6.250  -0.1503   0.05807   0.05639  -0.0756   0.9375   0.0031
  -6.000  -0.1301   0.05388   0.05212  -0.0800   0.9224   0.0030
  -5.000  -0.0932   0.01412   0.01028  -0.0863   0.8554   0.0029
  -4.750  -0.0721   0.01246   0.00822  -0.0849   0.8407   0.0031
  -4.500  -0.0493   0.01149   0.00694  -0.0838   0.8228   0.0033
  -4.250  -0.0262   0.01083   0.00600  -0.0826   0.8010   0.0035
  -4.000  -0.0030   0.01022   0.00513  -0.0815   0.7765   0.0036
  -3.750   0.0199   0.00953   0.00418  -0.0803   0.7523   0.0040
  -3.500   0.0439   0.00933   0.00381  -0.0795   0.7255   0.0044
  -3.250   0.0671   0.00914   0.00342  -0.0784   0.6905   0.0049
  -3.000   0.0913   0.00886   0.00295  -0.0774   0.6657   0.0053
  -2.750   0.1161   0.00866   0.00260  -0.0767   0.6466   0.0058
  -2.500   0.1406   0.00836   0.00212  -0.0758   0.6283   0.0070
  -2.250   0.1656   0.00823   0.00189  -0.0751   0.6089   0.0086
  -2.000   0.1902   0.00817   0.00169  -0.0744   0.5824   0.0104
  -1.750   0.2148   0.00808   0.00150  -0.0736   0.5579   0.0168
  -1.500   0.2391   0.00806   0.00137  -0.0728   0.5262   0.0283
  -1.250   0.2627   0.00817   0.00129  -0.0719   0.4808   0.0345
  -1.000   0.2864   0.00828   0.00124  -0.0711   0.4418   0.0419
  -0.750   0.3110   0.00829   0.00122  -0.0704   0.4182   0.0627
  -0.500   0.3365   0.00834   0.00123  -0.0699   0.4013   0.0769
  -0.250   0.3622   0.00840   0.00121  -0.0694   0.3876   0.0814
   0.000   0.3882   0.00844   0.00121  -0.0690   0.3767   0.0864
   0.250   0.4141   0.00849   0.00120  -0.0686   0.3669   0.0898
   0.500   0.4402   0.00855   0.00120  -0.0682   0.3579   0.0920
   0.750   0.4662   0.00857   0.00120  -0.0678   0.3508   0.0960
   1.000   0.4921   0.00861   0.00121  -0.0674   0.3436   0.0991
   1.250   0.5182   0.00865   0.00123  -0.0670   0.3374   0.1021
   1.500   0.5441   0.00870   0.00126  -0.0667   0.3306   0.1051
   1.750   0.5700   0.00875   0.00129  -0.0663   0.3241   0.1090
   2.000   0.5958   0.00880   0.00133  -0.0659   0.3170   0.1128
   2.250   0.6215   0.00886   0.00138  -0.0654   0.3107   0.1171
   2.750   0.6732   0.00894   0.00150  -0.0647   0.3008   0.1348
   3.000   0.6984   0.00894   0.00160  -0.0642   0.2963   0.1809
   3.250   0.7222   0.00876   0.00175  -0.0635   0.2916   0.3402
   3.750   0.8687   0.00871   0.00255  -0.0861   0.1700   1.0000
   4.000   0.8922   0.00899   0.00276  -0.0853   0.1555   1.0000
   4.250   0.9157   0.00927   0.00297  -0.0845   0.1408   1.0000
   4.500   0.9311   0.01038   0.00358  -0.0825   0.0428   1.0000
   4.750   0.9528   0.01085   0.00397  -0.0813   0.0115   1.0000
   5.000   0.9767   0.01108   0.00424  -0.0806   0.0093   1.0000
   5.250   0.9997   0.01140   0.00459  -0.0797   0.0068   1.0000
   5.500   1.0230   0.01168   0.00491  -0.0789   0.0059   1.0000
   5.750   1.0459   0.01200   0.00525  -0.0780   0.0050   1.0000
   6.000   1.0673   0.01247   0.00578  -0.0768   0.0041   1.0000
   6.250   1.0902   0.01275   0.00609  -0.0759   0.0036   1.0000
   6.500   1.1116   0.01319   0.00658  -0.0748   0.0033   1.0000
   6.750   1.1332   0.01358   0.00700  -0.0737   0.0028   1.0000
   7.000   1.1526   0.01420   0.00769  -0.0722   0.0026   1.0000
   7.250   1.1706   0.01492   0.00850  -0.0705   0.0024   1.0000
   7.500   1.1888   0.01559   0.00930  -0.0688   0.0022   1.0000
   7.750   1.2051   0.01638   0.01018  -0.0668   0.0022   1.0000
   8.000   1.2217   0.01710   0.01099  -0.0649   0.0020   1.0000
   8.250   1.2384   0.01776   0.01172  -0.0630   0.0018   1.0000
   8.500   1.2490   0.01888   0.01296  -0.0601   0.0017   1.0000
   8.750   1.2698   0.01914   0.01323  -0.0592   0.0015   1.0000
   9.000   1.2826   0.01999   0.01415  -0.0568   0.0015   1.0000
   9.250   1.2910   0.02112   0.01538  -0.0537   0.0014   1.0000
   9.500   1.2902   0.02279   0.01720  -0.0490   0.0013   1.0000
   9.750   1.2939   0.02385   0.01837  -0.0450   0.0013   1.0000
  10.000   1.2941   0.02537   0.02001  -0.0408   0.0013   1.0000
  10.250   1.2955   0.02711   0.02187  -0.0370   0.0013   1.0000
  10.500   1.2980   0.02971   0.02466  -0.0335   0.0011   1.0000
  10.750   1.3051   0.03354   0.02874  -0.0305   0.0009   1.0000
  11.000   1.3082   0.03654   0.03195  -0.0275   0.0009   1.0000
  11.250   1.3069   0.03948   0.03510  -0.0243   0.0009   1.0000
  11.500   1.3011   0.04246   0.03834  -0.0210   0.0008   1.0000
  11.750   1.2927   0.04544   0.04153  -0.0181   0.0009   1.0000
  12.000   1.2832   0.04848   0.04475  -0.0157   0.0009   1.0000
  12.250   1.2684   0.05231   0.04879  -0.0137   0.0009   1.0000
  12.500   1.2532   0.05635   0.05302  -0.0126   0.0009   1.0000
  12.750   1.2391   0.06049   0.05733  -0.0123   0.0009   1.0000
  13.000   1.2229   0.06523   0.06224  -0.0129   0.0009   1.0000
  13.250   1.2045   0.07076   0.06794  -0.0143   0.0009   1.0000
  13.500   1.1896   0.07602   0.07333  -0.0163   0.0009   1.0000
  13.750   1.1736   0.08191   0.07937  -0.0189   0.0009   1.0000
  14.000   1.1548   0.08881   0.08641  -0.0224   0.0009   1.0000
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