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USA 5 AIRFOIL (usa5-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: USA 5 AIRFOIL (usa5-il)
Reynolds number: 500,000
Max Cl/Cd: 91.89 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa5-il-500000-n5.txt
Download as CSV file: xf-usa5-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3205   0.09716   0.09503  -0.0238   1.0000   0.0076
  -8.000  -0.3213   0.09478   0.09269  -0.0233   1.0000   0.0079
  -7.750  -0.3215   0.09244   0.09038  -0.0230   0.9997   0.0077
  -7.250  -0.2885   0.08478   0.08273  -0.0330   0.9898   0.0090
  -7.000  -0.2708   0.08060   0.07856  -0.0383   0.9836   0.0089
  -6.750  -0.2440   0.07678   0.07471  -0.0457   0.9783   0.0095
  -6.500  -0.2226   0.07269   0.07060  -0.0512   0.9716   0.0096
  -6.250  -0.1951   0.06796   0.06585  -0.0582   0.9672   0.0096
  -6.000  -0.1793   0.06037   0.05820  -0.0648   0.9591   0.0054
  -5.750  -0.1495   0.05557   0.05335  -0.0715   0.9534   0.0052
  -5.500  -0.1239   0.05123   0.04893  -0.0764   0.9441   0.0049
  -5.250  -0.0965   0.04604   0.04361  -0.0814   0.9343   0.0049
  -5.000  -0.0700   0.04101   0.03843  -0.0851   0.9239   0.0050
  -4.750  -0.0454   0.03549   0.03269  -0.0877   0.9122   0.0051
  -4.500  -0.0250   0.02813   0.02495  -0.0885   0.8992   0.0052
  -4.250  -0.0157   0.01671   0.01248  -0.0859   0.8866   0.0054
  -4.000   0.0079   0.01498   0.01032  -0.0850   0.8740   0.0058
  -3.750   0.0299   0.01283   0.00762  -0.0837   0.8595   0.0063
  -3.500   0.0543   0.01172   0.00619  -0.0827   0.8435   0.0066
  -3.250   0.0793   0.01100   0.00524  -0.0819   0.8264   0.0071
  -3.000   0.1044   0.01042   0.00444  -0.0811   0.8092   0.0079
  -2.750   0.1295   0.00995   0.00377  -0.0802   0.7914   0.0090
  -2.500   0.1539   0.00957   0.00317  -0.0792   0.7676   0.0107
  -2.250   0.1778   0.00921   0.00261  -0.0781   0.7417   0.0144
  -2.000   0.2017   0.00905   0.00228  -0.0770   0.7142   0.0196
  -1.750   0.2259   0.00893   0.00205  -0.0761   0.6909   0.0317
  -1.500   0.2500   0.00885   0.00186  -0.0753   0.6691   0.0415
  -1.250   0.2742   0.00880   0.00175  -0.0744   0.6469   0.0561
  -1.000   0.2988   0.00885   0.00175  -0.0737   0.6244   0.0756
  -0.750   0.3231   0.00894   0.00168  -0.0729   0.5989   0.0829
  -0.500   0.3473   0.00905   0.00164  -0.0720   0.5685   0.0891
  -0.250   0.3713   0.00919   0.00159  -0.0712   0.5333   0.0928
   0.000   0.3947   0.00931   0.00154  -0.0703   0.4961   0.0973
   0.250   0.4183   0.00947   0.00153  -0.0694   0.4616   0.1015
   0.500   0.4427   0.00962   0.00154  -0.0687   0.4372   0.1056
   0.750   0.4672   0.00970   0.00154  -0.0680   0.4187   0.1108
   1.000   0.4921   0.00978   0.00156  -0.0675   0.4046   0.1162
   1.250   0.5173   0.00986   0.00158  -0.0669   0.3926   0.1195
   1.500   0.5424   0.00992   0.00160  -0.0664   0.3831   0.1235
   1.750   0.5677   0.00997   0.00165  -0.0659   0.3740   0.1296
   2.000   0.5930   0.01002   0.00170  -0.0654   0.3668   0.1393
   2.250   0.6180   0.01006   0.00178  -0.0649   0.3589   0.1623
   2.500   0.6425   0.01004   0.00189  -0.0643   0.3510   0.2280
   3.000   0.7858   0.00895   0.00239  -0.0853   0.3304   1.0000
   3.250   0.8107   0.00909   0.00251  -0.0847   0.3249   1.0000
   3.500   0.8358   0.00922   0.00264  -0.0842   0.3194   1.0000
   3.750   0.8600   0.00941   0.00279  -0.0835   0.3053   1.0000
   4.000   0.8840   0.00962   0.00295  -0.0829   0.2883   1.0000
   4.250   0.9073   0.00989   0.00311  -0.0821   0.2618   1.0000
   4.750   0.9450   0.01133   0.00393  -0.0792   0.1465   1.0000
   5.000   0.9565   0.01287   0.00482  -0.0765   0.0187   1.0000
   5.250   0.9789   0.01326   0.00527  -0.0755   0.0117   1.0000
   5.500   1.0015   0.01361   0.00571  -0.0745   0.0098   1.0000
   5.750   1.0235   0.01402   0.00619  -0.0734   0.0078   1.0000
   6.000   1.0430   0.01470   0.00703  -0.0719   0.0066   1.0000
   6.250   1.0637   0.01523   0.00765  -0.0705   0.0062   1.0000
   6.500   1.0836   0.01581   0.00831  -0.0691   0.0055   1.0000
   6.750   1.1039   0.01630   0.00883  -0.0679   0.0046   1.0000
   7.000   1.1195   0.01725   0.00987  -0.0658   0.0042   1.0000
   7.250   1.1342   0.01821   0.01094  -0.0635   0.0040   1.0000
   7.500   1.1487   0.01915   0.01198  -0.0612   0.0037   1.0000
   7.750   1.1607   0.02022   0.01320  -0.0585   0.0036   1.0000
   8.000   1.1709   0.02143   0.01451  -0.0555   0.0035   1.0000
   8.250   1.1800   0.02273   0.01591  -0.0524   0.0033   1.0000
   8.500   1.1893   0.02409   0.01735  -0.0494   0.0033   1.0000
   8.750   1.1988   0.02545   0.01880  -0.0465   0.0031   1.0000
   9.000   1.2086   0.02634   0.01975  -0.0438   0.0029   1.0000
   9.250   1.2165   0.02721   0.02069  -0.0411   0.0026   1.0000
   9.500   1.2222   0.02906   0.02264  -0.0380   0.0025   1.0000
   9.750   1.2328   0.03068   0.02443  -0.0355   0.0023   1.0000
  10.000   1.2433   0.03279   0.02670  -0.0332   0.0023   1.0000
  10.250   1.2524   0.03488   0.02895  -0.0308   0.0023   1.0000
  10.500   1.2603   0.03758   0.03190  -0.0282   0.0021   1.0000
  10.750   1.2640   0.04019   0.03475  -0.0254   0.0019   1.0000
  11.000   1.2636   0.04283   0.03760  -0.0225   0.0019   1.0000
  11.250   1.2597   0.04555   0.04054  -0.0197   0.0019   1.0000
  11.500   1.2527   0.04853   0.04374  -0.0171   0.0019   1.0000
  11.750   1.2440   0.05163   0.04705  -0.0150   0.0019   1.0000
  12.000   1.2345   0.05487   0.05048  -0.0135   0.0020   1.0000
  12.250   1.2207   0.05886   0.05468  -0.0126   0.0019   1.0000
  12.500   1.2060   0.06322   0.05925  -0.0124   0.0019   1.0000
  12.750   1.1926   0.06765   0.06385  -0.0130   0.0019   1.0000
  13.000   1.1777   0.07265   0.06902  -0.0143   0.0020   1.0000
  13.250   1.1603   0.07845   0.07500  -0.0165   0.0019   1.0000
  13.500   1.1464   0.08397   0.08066  -0.0190   0.0020   1.0000
  13.750   1.1309   0.09021   0.08706  -0.0221   0.0020   1.0000
  14.000   1.1138   0.09727   0.09426  -0.0259   0.0020   1.0000
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