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USA 5 AIRFOIL (usa5-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: USA 5 AIRFOIL (usa5-il)
Reynolds number: 50,000
Max Cl/Cd: 40.72 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa5-il-50000-n5.txt
Download as CSV file: xf-usa5-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3244   0.10110   0.09477  -0.0244   1.0000   0.0756
  -7.250  -0.3323   0.09995   0.09375  -0.0242   1.0000   0.0774
  -7.000  -0.3362   0.09868   0.09260  -0.0256   1.0000   0.0782
  -6.750  -0.3377   0.09720   0.09121  -0.0274   1.0000   0.0787
  -6.500  -0.3366   0.09550   0.08956  -0.0293   1.0000   0.0789
  -6.250  -0.3318   0.09003   0.08420  -0.0251   1.0000   0.0806
  -6.000  -0.3287   0.08689   0.08111  -0.0236   1.0000   0.0823
  -5.750  -0.3260   0.08419   0.07847  -0.0232   1.0000   0.0840
  -5.500  -0.3225   0.08160   0.07592  -0.0232   1.0000   0.0853
  -5.250  -0.3178   0.07894   0.07329  -0.0236   1.0000   0.0866
  -5.000  -0.3114   0.07626   0.07063  -0.0243   1.0000   0.0876
  -4.750  -0.3031   0.07347   0.06780  -0.0252   1.0000   0.0884
  -4.500  -0.2938   0.07046   0.06477  -0.0258   1.0000   0.0876
  -4.250  -0.2631   0.06489   0.05890  -0.0329   1.0000   0.0516
  -4.000  -0.2584   0.06170   0.05571  -0.0305   1.0000   0.0486
  -3.750  -0.2447   0.05847   0.05240  -0.0309   1.0000   0.0468
  -3.500  -0.2278   0.05530   0.04911  -0.0319   1.0000   0.0461
  -3.250  -0.2089   0.05224   0.04589  -0.0329   1.0000   0.0466
  -3.000  -0.1737   0.04842   0.04176  -0.0368   0.9952   0.0476
  -2.750  -0.1338   0.04428   0.03724  -0.0409   0.9884   0.0476
  -2.500  -0.0953   0.04051   0.03303  -0.0442   0.9814   0.0476
  -2.250  -0.0533   0.03669   0.02854  -0.0473   0.9735   0.0500
  -2.000  -0.0130   0.03433   0.02581  -0.0503   0.9628   0.0575
  -1.750   0.0330   0.03105   0.02174  -0.0532   0.9526   0.0626
  -1.500   0.0779   0.02907   0.01903  -0.0558   0.9406   0.0790
  -1.250   0.1197   0.02739   0.01696  -0.0581   0.9280   0.0953
  -1.000   0.1577   0.02618   0.01536  -0.0597   0.9159   0.1154
  -0.750   0.2025   0.02505   0.01376  -0.0625   0.9053   0.1378
  -0.500   0.2464   0.02425   0.01269  -0.0653   0.8949   0.1649
  -0.250   0.2913   0.02344   0.01170  -0.0682   0.8851   0.1902
   0.000   0.3287   0.02278   0.01095  -0.0698   0.8725   0.2098
   0.500   0.4000   0.02153   0.00979  -0.0722   0.8455   0.2683
   1.000   0.5006   0.01940   0.00880  -0.0804   0.8176   1.0000
   1.250   0.5315   0.01935   0.00853  -0.0804   0.7994   1.0000
   1.500   0.5609   0.01934   0.00835  -0.0802   0.7797   1.0000
   1.750   0.5922   0.01929   0.00815  -0.0802   0.7604   1.0000
   2.000   0.6205   0.01932   0.00806  -0.0797   0.7384   1.0000
   2.250   0.6501   0.01934   0.00795  -0.0794   0.7171   1.0000
   2.500   0.6773   0.01947   0.00799  -0.0787   0.6939   1.0000
   2.750   0.7058   0.01959   0.00798  -0.0783   0.6720   1.0000
   3.000   0.7318   0.01984   0.00815  -0.0776   0.6493   1.0000
   3.250   0.7586   0.02010   0.00835  -0.0770   0.6286   1.0000
   3.500   0.7833   0.02045   0.00865  -0.0761   0.6068   1.0000
   3.750   0.8086   0.02079   0.00893  -0.0753   0.5869   1.0000
   4.000   0.8322   0.02121   0.00934  -0.0744   0.5667   1.0000
   4.250   0.8559   0.02162   0.00980  -0.0735   0.5479   1.0000
   4.500   0.8797   0.02203   0.01022  -0.0725   0.5305   1.0000
   4.750   0.9033   0.02246   0.01068  -0.0716   0.5141   1.0000
   5.000   0.9264   0.02293   0.01124  -0.0706   0.4979   1.0000
   5.250   0.9495   0.02342   0.01189  -0.0697   0.4826   1.0000
   5.500   0.9727   0.02393   0.01253  -0.0687   0.4680   1.0000
   5.750   0.9964   0.02447   0.01323  -0.0679   0.4552   1.0000
   6.000   1.0169   0.02499   0.01391  -0.0664   0.4368   1.0000
   6.250   1.0304   0.02539   0.01433  -0.0636   0.4038   1.0000
   6.500   1.0445   0.02590   0.01487  -0.0611   0.3742   1.0000
   6.750   1.0544   0.02645   0.01540  -0.0580   0.3349   1.0000
   7.000   1.0701   0.02706   0.01619  -0.0559   0.3078   1.0000
   7.250   1.0812   0.02778   0.01693  -0.0532   0.2524   1.0000
   7.500   1.0889   0.02905   0.01776  -0.0504   0.1820   1.0000
   8.000   1.0919   0.03429   0.02184  -0.0447   0.0397   1.0000
   8.250   1.0964   0.03644   0.02403  -0.0420   0.0340   1.0000
   8.500   1.1009   0.03828   0.02609  -0.0392   0.0310   1.0000
   8.750   1.1015   0.04034   0.02848  -0.0362   0.0292   1.0000
   9.000   1.1009   0.04249   0.03085  -0.0335   0.0283   1.0000
   9.250   1.0971   0.04500   0.03355  -0.0311   0.0276   1.0000
   9.500   1.0910   0.04786   0.03660  -0.0290   0.0271   1.0000
   9.750   1.0862   0.05080   0.03970  -0.0276   0.0268   1.0000
  10.000   1.0824   0.05383   0.04295  -0.0265   0.0264   1.0000
  10.250   1.0795   0.05694   0.04627  -0.0258   0.0260   1.0000
  10.500   1.0767   0.06024   0.04977  -0.0252   0.0254   1.0000
  10.750   1.0759   0.06339   0.05312  -0.0247   0.0250   1.0000
  11.000   1.0763   0.06651   0.05644  -0.0242   0.0241   1.0000
  11.250   1.0785   0.06948   0.05960  -0.0234   0.0233   1.0000
  11.500   1.0830   0.07227   0.06259  -0.0224   0.0226   1.0000
  11.750   1.0914   0.07479   0.06533  -0.0210   0.0224   1.0000
  12.000   1.0999   0.07752   0.06833  -0.0198   0.0223   1.0000
  12.250   1.1049   0.08091   0.07203  -0.0190   0.0222   1.0000
  12.500   1.1045   0.08501   0.07642  -0.0192   0.0222   1.0000
  12.750   1.0998   0.08968   0.08135  -0.0202   0.0223   1.0000
  13.000   1.0918   0.09493   0.08686  -0.0219   0.0224   1.0000
  13.250   1.0817   0.10066   0.09282  -0.0243   0.0225   1.0000
  13.500   1.0704   0.10681   0.09919  -0.0272   0.0226   1.0000
  13.750   1.0587   0.11330   0.10588  -0.0306   0.0229   1.0000
  14.000   1.0457   0.12047   0.11323  -0.0345   0.0230   1.0000
  14.250   1.0330   0.12796   0.12088  -0.0388   0.0232   1.0000
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