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USA 45 M AIRFOIL (usa45m-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: USA 45 M AIRFOIL (usa45m-il)
Reynolds number: 50,000
Max Cl/Cd: 20.38 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa45m-il-50000.txt
Download as CSV file: xf-usa45m-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 45 M 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3473   0.10733   0.10051  -0.0116   1.0000   0.2598
  -8.750  -0.3586   0.10572   0.09903  -0.0124   1.0000   0.2699
  -8.500  -0.3590   0.10365   0.09702  -0.0120   1.0000   0.2836
  -8.250  -0.3447   0.09988   0.09328  -0.0109   1.0000   0.2984
  -8.000  -0.3406   0.09712   0.09059  -0.0100   1.0000   0.3145
  -7.750  -0.3413   0.09482   0.08839  -0.0089   1.0000   0.3313
  -7.500  -0.3468   0.09292   0.08660  -0.0076   1.0000   0.3483
  -7.250  -0.3143   0.08808   0.08174  -0.0058   1.0000   0.3720
  -7.000  -0.3164   0.08614   0.07991  -0.0039   1.0000   0.3943
  -6.500  -0.3121   0.08168   0.07562   0.0010   1.0000   0.4441
  -6.250  -0.2953   0.07865   0.07265   0.0034   1.0000   0.4751
  -6.000  -0.2942   0.07685   0.07096   0.0070   1.0000   0.5084
  -5.750  -0.2637   0.07341   0.06751   0.0093   1.0000   0.5550
  -4.250  -0.1324   0.05597   0.05041   0.0145   1.0000   0.7725
  -4.000  -0.2195   0.05745   0.05230   0.0247   1.0000   0.7033
  -3.750  -0.2841   0.05796   0.05314   0.0332   1.0000   0.6722
  -3.500  -0.3782   0.04538   0.03840  -0.0128   1.0000   0.2209
  -3.250  -0.3263   0.04124   0.03346  -0.0192   0.9875   0.1891
  -3.000  -0.2603   0.03776   0.02927  -0.0268   0.9672   0.1708
  -2.750  -0.1968   0.03554   0.02606  -0.0330   0.9446   0.1590
  -2.500  -0.1324   0.03346   0.02355  -0.0393   0.9231   0.1590
  -2.250  -0.0758   0.03168   0.02148  -0.0440   0.8995   0.1599
  -2.000  -0.0069   0.02976   0.01938  -0.0502   0.8800   0.1613
  -1.750   0.0622   0.02805   0.01760  -0.0559   0.8614   0.1683
  -1.500   0.1083   0.02701   0.01653  -0.0581   0.8376   0.1804
  -1.250   0.1517   0.02595   0.01547  -0.0595   0.8174   0.1958
  -1.000   0.3071   0.02133   0.01337  -0.0772   0.7987   1.0000
  -0.750   0.3294   0.02162   0.01323  -0.0757   0.7751   1.0000
  -0.500   0.3530   0.02188   0.01312  -0.0744   0.7553   1.0000
  -0.250   0.3759   0.02218   0.01311  -0.0730   0.7376   1.0000
   0.000   0.3976   0.02255   0.01322  -0.0717   0.7211   1.0000
   0.250   0.4183   0.02302   0.01346  -0.0703   0.7058   1.0000
   0.500   0.4383   0.02356   0.01381  -0.0689   0.6913   1.0000
   0.750   0.4580   0.02416   0.01425  -0.0675   0.6779   1.0000
   1.000   0.4782   0.02477   0.01470  -0.0662   0.6656   1.0000
   1.250   0.5011   0.02526   0.01499  -0.0650   0.6551   1.0000
   1.500   0.5192   0.02606   0.01571  -0.0637   0.6434   1.0000
   1.750   0.5368   0.02695   0.01652  -0.0624   0.6325   1.0000
   2.000   0.5603   0.02749   0.01691  -0.0613   0.6235   1.0000
   2.250   0.5756   0.02859   0.01800  -0.0600   0.6131   1.0000
   2.500   0.5935   0.02958   0.01894  -0.0587   0.6039   1.0000
   2.750   0.6141   0.03038   0.01967  -0.0575   0.5952   1.0000
   3.000   0.6268   0.03183   0.02113  -0.0561   0.5862   1.0000
   3.250   0.6503   0.03250   0.02171  -0.0551   0.5784   1.0000
   3.500   0.6581   0.03435   0.02364  -0.0536   0.5692   1.0000
   3.750   0.6843   0.03491   0.02411  -0.0527   0.5621   1.0000
   4.000   0.6845   0.03743   0.02674  -0.0509   0.5531   1.0000
   4.250   0.7145   0.03774   0.02698  -0.0502   0.5461   1.0000
   4.500   0.7049   0.04111   0.03047  -0.0483   0.5371   1.0000
   4.750   0.7393   0.04116   0.03048  -0.0477   0.5303   1.0000
   5.000   0.7152   0.04576   0.03521  -0.0455   0.5215   1.0000
   5.250   0.7570   0.04530   0.03471  -0.0450   0.5146   1.0000
   5.500   0.7039   0.05238   0.04189  -0.0428   0.5072   1.0000
   5.750   0.7592   0.05084   0.04034  -0.0423   0.4990   1.0000
   6.000   0.6833   0.05977   0.04926  -0.0404   0.4946   1.0000
   6.250   0.6522   0.06512   0.05459  -0.0397   0.4915   1.0000
   6.500   0.6920   0.06532   0.05483  -0.0390   0.4817   1.0000
   6.750   0.6608   0.07097   0.06045  -0.0390   0.4802   1.0000
   7.000   0.6463   0.07547   0.06495  -0.0392   0.4795   1.0000
   7.250   0.6398   0.07958   0.06908  -0.0397   0.4800   1.0000
   7.500   0.6465   0.08343   0.07298  -0.0406   0.4821   1.0000
   7.750   0.5582   0.09619   0.08580  -0.0488   0.5927   1.0000
   8.000   0.5665   0.09830   0.08793  -0.0481   0.5779   1.0000
   8.250   0.5627   0.10000   0.08963  -0.0470   0.5653   1.0000
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