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R140 12.04% (smoothed) (r140sm-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: R140 12.04% (smoothed) (r140sm-il)
Reynolds number: 500,000
Max Cl/Cd: 62.01 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-r140sm-il-500000.txt
Download as CSV file: xf-r140sm-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: R140  12.04% (smoothed)                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4991   0.07284   0.07074  -0.0430   1.0000   0.0180
 -10.500  -0.5294   0.06370   0.06154  -0.0481   1.0000   0.0170
 -10.250  -0.5599   0.05666   0.05440  -0.0511   1.0000   0.0163
 -10.000  -0.5874   0.05151   0.04915  -0.0520   1.0000   0.0162
  -9.750  -0.6140   0.04725   0.04478  -0.0511   1.0000   0.0160
  -9.500  -0.6353   0.04425   0.04167  -0.0487   1.0000   0.0161
  -9.250  -0.6563   0.04161   0.03893  -0.0446   1.0000   0.0161
  -7.000  -0.7063   0.02580   0.02043  -0.0088   0.9909   0.0138
  -6.750  -0.6787   0.02188   0.01622  -0.0090   0.9880   0.0124
  -6.500  -0.6468   0.01958   0.01365  -0.0100   0.9854   0.0126
  -6.250  -0.6125   0.01810   0.01201  -0.0115   0.9833   0.0131
  -6.000  -0.5829   0.01658   0.01034  -0.0121   0.9792   0.0137
  -5.750  -0.5570   0.01464   0.00827  -0.0122   0.9742   0.0150
  -5.500  -0.5237   0.01376   0.00737  -0.0139   0.9710   0.0172
  -5.250  -0.4918   0.01291   0.00643  -0.0151   0.9670   0.0190
  -5.000  -0.4610   0.01227   0.00571  -0.0159   0.9609   0.0205
  -4.750  -0.4291   0.01137   0.00473  -0.0171   0.9561   0.0265
  -4.500  -0.4025   0.01066   0.00407  -0.0170   0.9472   0.0501
  -4.250  -0.3785   0.00962   0.00350  -0.0169   0.9384   0.1591
  -4.000  -0.3672   0.00806   0.00288  -0.0145   0.9257   0.3866
  -3.750  -0.3500   0.00738   0.00264  -0.0125   0.9135   0.5074
  -3.500  -0.3289   0.00712   0.00253  -0.0110   0.9006   0.5658
  -3.250  -0.3069   0.00700   0.00245  -0.0097   0.8874   0.6112
  -3.000  -0.2833   0.00692   0.00236  -0.0087   0.8740   0.6388
  -2.750  -0.2580   0.00685   0.00224  -0.0081   0.8602   0.6535
  -2.500  -0.2331   0.00678   0.00213  -0.0074   0.8460   0.6696
  -2.250  -0.2086   0.00673   0.00202  -0.0066   0.8316   0.6876
  -2.000  -0.1837   0.00668   0.00193  -0.0060   0.8173   0.7030
  -1.750  -0.1582   0.00663   0.00185  -0.0055   0.8033   0.7146
  -1.500  -0.1327   0.00660   0.00179  -0.0050   0.7898   0.7264
  -1.250  -0.1070   0.00658   0.00173  -0.0045   0.7773   0.7376
  -1.000  -0.0810   0.00658   0.00169  -0.0042   0.7656   0.7481
  -0.750  -0.0550   0.00658   0.00166  -0.0038   0.7548   0.7592
  -0.500  -0.0289   0.00659   0.00165  -0.0035   0.7449   0.7703
  -0.250  -0.0029   0.00660   0.00165  -0.0032   0.7351   0.7822
   0.000   0.0233   0.00661   0.00167  -0.0029   0.7263   0.7947
   0.250   0.0494   0.00664   0.00169  -0.0026   0.7183   0.8079
   0.500   0.0755   0.00665   0.00173  -0.0022   0.7097   0.8215
   0.750   0.1019   0.00669   0.00177  -0.0020   0.7025   0.8350
   1.000   0.1284   0.00671   0.00183  -0.0017   0.6949   0.8485
   1.250   0.1552   0.00676   0.00189  -0.0015   0.6883   0.8615
   1.500   0.1821   0.00679   0.00197  -0.0013   0.6811   0.8743
   1.750   0.2094   0.00686   0.00205  -0.0012   0.6751   0.8867
   2.000   0.2371   0.00690   0.00215  -0.0012   0.6674   0.8983
   2.250   0.2667   0.00697   0.00225  -0.0016   0.6587   0.9083
   2.500   0.2958   0.00705   0.00234  -0.0019   0.6467   0.9180
   2.750   0.3239   0.00712   0.00244  -0.0019   0.6353   0.9283
   3.000   0.3575   0.00722   0.00258  -0.0032   0.6232   0.9348
   3.250   0.3875   0.00731   0.00270  -0.0037   0.6103   0.9429
   3.500   0.4220   0.00744   0.00284  -0.0052   0.5887   0.9477
   3.750   0.4494   0.00758   0.00294  -0.0051   0.5601   0.9556
   4.000   0.4855   0.00783   0.00309  -0.0071   0.5121   0.9583
   4.250   0.5130   0.00867   0.00337  -0.0076   0.3716   0.9627
   4.500   0.5237   0.01101   0.00438  -0.0058   0.0825   0.9710
   4.750   0.5540   0.01207   0.00517  -0.0069   0.0228   0.9747
   5.000   0.5855   0.01263   0.00582  -0.0079   0.0197   0.9793
   5.250   0.6143   0.01341   0.00666  -0.0086   0.0167   0.9839
   5.500   0.6441   0.01456   0.00793  -0.0096   0.0148   0.9873
   5.750   0.6746   0.01542   0.00891  -0.0106   0.0140   0.9913
   6.000   0.7035   0.01656   0.01013  -0.0113   0.0135   0.9949
   6.250   0.7341   0.01796   0.01163  -0.0123   0.0130   0.9975
   6.500   0.7643   0.01982   0.01364  -0.0129   0.0133   0.9994
   6.750   0.7855   0.02134   0.01530  -0.0117   0.0130   1.0000
   7.000   0.7996   0.02265   0.01675  -0.0092   0.0127   1.0000
   7.250   0.8132   0.02425   0.01853  -0.0066   0.0126   1.0000
  13.000   0.6101   0.12482   0.12247   0.0129   0.0152   1.0000
  13.250   0.6097   0.13018   0.12781   0.0106   0.0151   1.0000
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