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USA 46 AIRFOIL (usa46-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: USA 46 AIRFOIL (usa46-il)
Reynolds number: 1,000,000
Max Cl/Cd: 80.77 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa46-il-1000000-n5.txt
Download as CSV file: xf-usa46-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 46 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.6916   0.07483   0.07320  -0.0183   1.0000   0.0028
 -10.000  -0.7949   0.03196   0.02979  -0.0573   1.0000   0.0022
  -9.750  -0.7845   0.02670   0.02411  -0.0596   1.0000   0.0023
  -9.500  -0.7682   0.02364   0.02073  -0.0602   1.0000   0.0023
  -9.250  -0.7492   0.02142   0.01823  -0.0603   1.0000   0.0024
  -9.000  -0.7289   0.01956   0.01611  -0.0602   1.0000   0.0025
  -8.750  -0.7074   0.01803   0.01433  -0.0599   1.0000   0.0026
  -8.500  -0.6849   0.01688   0.01299  -0.0595   1.0000   0.0028
  -8.250  -0.6621   0.01580   0.01173  -0.0591   1.0000   0.0029
  -8.000  -0.6387   0.01492   0.01069  -0.0586   1.0000   0.0030
  -7.750  -0.6155   0.01390   0.00951  -0.0580   1.0000   0.0031
  -7.500  -0.5923   0.01289   0.00833  -0.0575   1.0000   0.0034
  -7.250  -0.5684   0.01222   0.00757  -0.0569   1.0000   0.0035
  -7.000  -0.5442   0.01168   0.00695  -0.0563   1.0000   0.0038
  -6.750  -0.5137   0.01112   0.00630  -0.0571   0.9988   0.0041
  -6.500  -0.4808   0.01063   0.00572  -0.0584   0.9967   0.0045
  -6.250  -0.4477   0.01023   0.00523  -0.0596   0.9941   0.0049
  -6.000  -0.4161   0.00963   0.00452  -0.0605   0.9905   0.0056
  -5.750  -0.3839   0.00918   0.00402  -0.0616   0.9874   0.0063
  -5.500  -0.3538   0.00883   0.00361  -0.0621   0.9832   0.0071
  -5.250  -0.3225   0.00853   0.00325  -0.0628   0.9786   0.0079
  -5.000  -0.2909   0.00812   0.00283  -0.0637   0.9736   0.0111
  -4.750  -0.2586   0.00779   0.00250  -0.0647   0.9675   0.0193
  -4.500  -0.2259   0.00750   0.00226  -0.0658   0.9597   0.0307
  -4.250  -0.1915   0.00732   0.00205  -0.0672   0.9498   0.0352
  -4.000  -0.1576   0.00712   0.00184  -0.0684   0.9352   0.0407
  -3.750  -0.1267   0.00702   0.00165  -0.0690   0.9136   0.0437
  -3.500  -0.0992   0.00691   0.00148  -0.0687   0.8896   0.0512
  -3.250  -0.0726   0.00686   0.00134  -0.0683   0.8677   0.0553
  -3.000  -0.0461   0.00678   0.00120  -0.0679   0.8470   0.0634
  -2.750  -0.0197   0.00673   0.00107  -0.0675   0.8256   0.0726
  -2.500   0.0068   0.00666   0.00096  -0.0670   0.8026   0.0857
  -2.250   0.0331   0.00659   0.00087  -0.0667   0.7787   0.1063
  -2.000   0.0596   0.00658   0.00081  -0.0663   0.7540   0.1216
  -1.750   0.0862   0.00660   0.00076  -0.0659   0.7275   0.1312
  -1.500   0.1127   0.00666   0.00070  -0.0655   0.6970   0.1382
  -1.250   0.1392   0.00672   0.00067  -0.0651   0.6635   0.1450
  -1.000   0.1659   0.00680   0.00064  -0.0648   0.6319   0.1509
  -0.750   0.1928   0.00685   0.00061  -0.0645   0.6071   0.1570
  -0.500   0.2198   0.00689   0.00060  -0.0643   0.5851   0.1669
  -0.250   0.2468   0.00691   0.00060  -0.0641   0.5624   0.1825
   0.000   0.2736   0.00693   0.00061  -0.0638   0.5385   0.2048
   0.250   0.3006   0.00692   0.00062  -0.0637   0.5195   0.2335
   0.500   0.3276   0.00683   0.00064  -0.0635   0.5059   0.2877
   0.750   0.3545   0.00668   0.00067  -0.0634   0.4926   0.3672
   1.000   0.3813   0.00656   0.00072  -0.0632   0.4761   0.4454
   1.250   0.4077   0.00649   0.00078  -0.0630   0.4533   0.5224
   1.500   0.4336   0.00646   0.00086  -0.0626   0.4180   0.6023
   1.750   0.4576   0.00661   0.00102  -0.0620   0.3523   0.6935
   2.000   0.4827   0.00680   0.00118  -0.0614   0.3125   0.7477
   2.250   0.5091   0.00687   0.00128  -0.0610   0.2978   0.7762
   2.500   0.5350   0.00705   0.00141  -0.0606   0.2671   0.7979
   2.750   0.5608   0.00717   0.00152  -0.0602   0.2438   0.8215
   3.000   0.5840   0.00723   0.00164  -0.0591   0.2068   0.8768
   3.250   0.6177   0.00780   0.00196  -0.0608   0.1125   1.0000
   3.500   0.6423   0.00836   0.00226  -0.0603   0.0549   1.0000
   3.750   0.6676   0.00882   0.00256  -0.0598   0.0196   1.0000
   4.000   0.6941   0.00907   0.00279  -0.0595   0.0121   1.0000
   4.250   0.7207   0.00929   0.00305  -0.0592   0.0105   1.0000
   4.500   0.7470   0.00956   0.00333  -0.0589   0.0090   1.0000
   4.750   0.7727   0.00995   0.00375  -0.0584   0.0070   1.0000
   5.000   0.7989   0.01022   0.00405  -0.0581   0.0064   1.0000
   5.250   0.8249   0.01053   0.00440  -0.0577   0.0058   1.0000
   5.500   0.8506   0.01088   0.00479  -0.0572   0.0052   1.0000
   5.750   0.8758   0.01131   0.00524  -0.0568   0.0048   1.0000
   6.000   0.9000   0.01195   0.00596  -0.0561   0.0043   1.0000
   6.250   0.9251   0.01237   0.00643  -0.0556   0.0041   1.0000
   6.500   0.9501   0.01278   0.00689  -0.0551   0.0037   1.0000
   6.750   0.9746   0.01328   0.00744  -0.0545   0.0034   1.0000
   7.000   0.9988   0.01381   0.00802  -0.0539   0.0032   1.0000
   7.250   1.0225   0.01442   0.00872  -0.0533   0.0030   1.0000
   7.500   1.0458   0.01505   0.00941  -0.0526   0.0029   1.0000
   7.750   1.0661   0.01622   0.01070  -0.0514   0.0026   1.0000
   8.000   1.0883   0.01705   0.01164  -0.0506   0.0026   1.0000
   8.250   1.1102   0.01792   0.01262  -0.0497   0.0025   1.0000
   8.500   1.1309   0.01899   0.01384  -0.0486   0.0024   1.0000
   8.750   1.1505   0.02029   0.01531  -0.0474   0.0023   1.0000
   9.000   1.1690   0.02177   0.01698  -0.0461   0.0021   1.0000
   9.250   1.1856   0.02359   0.01903  -0.0446   0.0020   1.0000
   9.500   1.1994   0.02590   0.02162  -0.0429   0.0020   1.0000
   9.750   1.2091   0.02883   0.02489  -0.0407   0.0019   1.0000
  10.000   1.2092   0.03321   0.02972  -0.0377   0.0019   1.0000
  10.250   1.2100   0.03670   0.03353  -0.0352   0.0018   1.0000
  10.500   1.1908   0.04242   0.03969  -0.0313   0.0018   1.0000
  10.750   1.1751   0.04554   0.04302  -0.0274   0.0017   1.0000
  11.000   1.1471   0.05010   0.04781  -0.0246   0.0018   1.0000
  11.250   1.1246   0.05490   0.05279  -0.0246   0.0017   1.0000
  11.500   1.1063   0.06018   0.05822  -0.0269   0.0017   1.0000
  11.750   1.0478   0.07551   0.07385  -0.0372   0.0019   1.0000
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