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USA 5 AIRFOIL (usa5-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: USA 5 AIRFOIL (usa5-il)
Reynolds number: 500,000
Max Cl/Cd: 94.96 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa5-il-500000.txt
Download as CSV file: xf-usa5-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3529   0.09098   0.08897  -0.0212   1.0000   0.0127
  -7.250  -0.3613   0.08925   0.08728  -0.0191   1.0000   0.0127
  -7.000  -0.3666   0.08702   0.08508  -0.0182   1.0000   0.0127
  -6.750  -0.3550   0.08331   0.08137  -0.0217   0.9985   0.0127
  -6.500  -0.3415   0.07684   0.07491  -0.0257   0.9956   0.0137
  -6.250  -0.3152   0.07273   0.07076  -0.0315   0.9922   0.0142
  -6.000  -0.2869   0.06865   0.06664  -0.0377   0.9880   0.0160
  -5.750  -0.2520   0.06367   0.06161  -0.0461   0.9844   0.0175
  -5.500  -0.2062   0.05923   0.05706  -0.0558   0.9807   0.0192
  -5.250  -0.1718   0.05479   0.05252  -0.0617   0.9752   0.0194
  -5.000  -0.1454   0.04673   0.04434  -0.0686   0.9714   0.0205
  -4.750  -0.1125   0.04340   0.04093  -0.0726   0.9693   0.0213
  -4.500  -0.0851   0.04048   0.03792  -0.0749   0.9634   0.0223
  -4.250  -0.0509   0.03689   0.03417  -0.0784   0.9592   0.0237
  -4.000  -0.0135   0.03274   0.02981  -0.0819   0.9554   0.0262
  -3.750   0.0009   0.01915   0.01523  -0.0795   0.9444   0.0163
  -3.500   0.0228   0.01507   0.01043  -0.0779   0.9366   0.0172
  -3.250   0.0497   0.01324   0.00819  -0.0772   0.9293   0.0180
  -3.000   0.0775   0.01310   0.00793  -0.0768   0.9207   0.0194
  -2.750   0.1033   0.01069   0.00509  -0.0761   0.9134   0.0218
  -2.500   0.1284   0.01011   0.00443  -0.0752   0.9025   0.0246
  -2.250   0.1549   0.00961   0.00381  -0.0745   0.8910   0.0277
  -2.000   0.1805   0.00898   0.00308  -0.0737   0.8777   0.0343
  -1.750   0.2068   0.00870   0.00268  -0.0730   0.8617   0.0408
  -1.250   0.2579   0.00824   0.00217  -0.0714   0.8244   0.0718
  -1.000   0.2845   0.00836   0.00220  -0.0709   0.8034   0.0894
  -0.750   0.3100   0.00837   0.00212  -0.0702   0.7819   0.0996
  -0.500   0.3351   0.00840   0.00202  -0.0694   0.7586   0.1078
  -0.250   0.3593   0.00840   0.00192  -0.0685   0.7329   0.1146
   0.000   0.3835   0.00848   0.00183  -0.0675   0.7056   0.1190
   0.250   0.4066   0.00843   0.00169  -0.0664   0.6776   0.1252
   0.500   0.4304   0.00852   0.00165  -0.0655   0.6505   0.1314
   0.750   0.4538   0.00855   0.00159  -0.0644   0.6235   0.1387
   1.000   0.4771   0.00865   0.00157  -0.0634   0.5937   0.1449
   1.250   0.5002   0.00874   0.00155  -0.0624   0.5579   0.1518
   1.500   0.5229   0.00888   0.00156  -0.0613   0.5186   0.1623
   1.750   0.5451   0.00901   0.00161  -0.0601   0.4811   0.1899
   2.000   0.6663   0.00778   0.00195  -0.0825   0.4321   1.0000
   2.250   0.6906   0.00798   0.00204  -0.0817   0.4175   1.0000
   2.500   0.7151   0.00816   0.00214  -0.0810   0.4059   1.0000
   2.750   0.7397   0.00835   0.00225  -0.0804   0.3962   1.0000
   3.000   0.7643   0.00852   0.00237  -0.0797   0.3870   1.0000
   3.250   0.7892   0.00867   0.00252  -0.0791   0.3794   1.0000
   3.500   0.8135   0.00887   0.00266  -0.0784   0.3704   1.0000
   3.750   0.8379   0.00904   0.00279  -0.0777   0.3572   1.0000
   4.000   0.8623   0.00922   0.00292  -0.0771   0.3434   1.0000
   4.250   0.8865   0.00940   0.00308  -0.0764   0.3291   1.0000
   4.500   0.9107   0.00959   0.00322  -0.0757   0.3094   1.0000
   4.750   0.9337   0.00988   0.00337  -0.0749   0.2751   1.0000
   5.000   0.9504   0.01080   0.00373  -0.0731   0.1776   1.0000
   5.250   0.9698   0.01150   0.00422  -0.0717   0.1403   1.0000
   5.500   0.9814   0.01305   0.00514  -0.0690   0.0232   1.0000
   5.750   1.0034   0.01351   0.00568  -0.0679   0.0183   1.0000
   6.000   1.0252   0.01397   0.00626  -0.0666   0.0162   1.0000
   6.250   1.0458   0.01458   0.00701  -0.0652   0.0148   1.0000
   6.500   1.0644   0.01537   0.00794  -0.0634   0.0142   1.0000
   6.750   1.0813   0.01627   0.00897  -0.0613   0.0135   1.0000
   7.000   1.1006   0.01689   0.00966  -0.0598   0.0127   1.0000
   7.250   1.1168   0.01777   0.01066  -0.0577   0.0122   1.0000
   7.500   1.1311   0.01878   0.01178  -0.0553   0.0120   1.0000
   7.750   1.1439   0.01992   0.01301  -0.0526   0.0116   1.0000
   8.000   1.1550   0.02123   0.01442  -0.0497   0.0113   1.0000
   8.250   1.1657   0.02273   0.01601  -0.0467   0.0116   1.0000
   8.500   1.1775   0.02464   0.01802  -0.0439   0.0124   1.0000
  14.000   0.9359   0.09906   0.09630  -0.0096   0.0136   1.0000
  14.250   0.9118   0.10526   0.10260  -0.0128   0.0136   1.0000
  14.500   0.8858   0.11073   0.10818  -0.0162   0.0136   1.0000
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