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R140 12.04% (smoothed) (r140sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: R140 12.04% (smoothed) (r140sm-il)
Reynolds number: 1,000,000
Max Cl/Cd: 71.07 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-r140sm-il-1000000.txt
Download as CSV file: xf-r140sm-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.4585   0.09829   0.09676  -0.0301   1.0000   0.0085
 -11.750  -0.4683   0.09119   0.08967  -0.0326   1.0000   0.0085
  -9.000  -0.8454   0.03044   0.02693  -0.0177   1.0000   0.0057
  -8.500  -0.8263   0.02485   0.02072  -0.0132   0.9973   0.0056
  -8.250  -0.8019   0.02240   0.01800  -0.0138   0.9948   0.0058
  -8.000  -0.7785   0.01981   0.01509  -0.0136   0.9918   0.0057
  -7.750  -0.7498   0.01910   0.01434  -0.0146   0.9886   0.0062
  -7.500  -0.7204   0.01796   0.01306  -0.0156   0.9859   0.0065
  -7.250  -0.6902   0.01664   0.01162  -0.0166   0.9837   0.0068
  -7.000  -0.6626   0.01536   0.01021  -0.0170   0.9800   0.0072
  -6.750  -0.6354   0.01424   0.00899  -0.0172   0.9753   0.0075
  -6.500  -0.6034   0.01350   0.00817  -0.0185   0.9721   0.0081
  -6.250  -0.5684   0.01298   0.00759  -0.0204   0.9693   0.0085
  -6.000  -0.5464   0.01146   0.00589  -0.0198   0.9607   0.0093
  -5.750  -0.5155   0.01073   0.00508  -0.0209   0.9546   0.0102
  -5.500  -0.4879   0.01032   0.00463  -0.0211   0.9449   0.0117
  -5.250  -0.4605   0.01004   0.00430  -0.0213   0.9351   0.0130
  -5.000  -0.4361   0.00962   0.00378  -0.0206   0.9241   0.0141
  -4.750  -0.4134   0.00922   0.00329  -0.0196   0.9122   0.0175
  -4.500  -0.3901   0.00894   0.00294  -0.0188   0.8999   0.0237
  -4.250  -0.3699   0.00847   0.00263  -0.0174   0.8865   0.0641
  -4.000  -0.3499   0.00801   0.00236  -0.0160   0.8723   0.1216
  -3.750  -0.3311   0.00747   0.00207  -0.0144   0.8569   0.2011
  -3.500  -0.3199   0.00644   0.00168  -0.0116   0.8394   0.3792
  -3.250  -0.3022   0.00593   0.00148  -0.0097   0.8223   0.4792
  -3.000  -0.2814   0.00568   0.00136  -0.0084   0.8053   0.5385
  -2.750  -0.2591   0.00556   0.00131  -0.0073   0.7890   0.5844
  -2.500  -0.2347   0.00553   0.00126  -0.0066   0.7735   0.6088
  -2.250  -0.2092   0.00553   0.00119  -0.0061   0.7593   0.6221
  -1.750  -0.1585   0.00550   0.00111  -0.0052   0.7343   0.6508
  -1.500  -0.1327   0.00549   0.00107  -0.0049   0.7231   0.6634
  -1.250  -0.1066   0.00548   0.00103  -0.0046   0.7132   0.6720
  -0.750  -0.0540   0.00546   0.00097  -0.0041   0.6951   0.6907
  -0.500  -0.0280   0.00544   0.00095  -0.0038   0.6870   0.7005
  -0.250  -0.0017   0.00543   0.00094  -0.0036   0.6789   0.7096
   0.000   0.0247   0.00541   0.00093  -0.0034   0.6719   0.7199
   0.500   0.0769   0.00538   0.00095  -0.0029   0.6584   0.7459
   0.750   0.1028   0.00536   0.00098  -0.0025   0.6516   0.7615
   1.000   0.1285   0.00536   0.00102  -0.0021   0.6458   0.7783
   1.250   0.1545   0.00534   0.00106  -0.0018   0.6389   0.7952
   1.500   0.1802   0.00536   0.00111  -0.0014   0.6314   0.8112
   1.750   0.2061   0.00537   0.00115  -0.0010   0.6226   0.8257
   2.000   0.2319   0.00538   0.00119  -0.0007   0.6119   0.8391
   2.250   0.2578   0.00540   0.00124  -0.0003   0.6029   0.8513
   2.500   0.2836   0.00544   0.00130   0.0001   0.5918   0.8631
   2.750   0.3101   0.00545   0.00137   0.0003   0.5827   0.8744
   3.250   0.3616   0.00557   0.00150   0.0010   0.5480   0.8968
   3.500   0.3875   0.00567   0.00159   0.0014   0.5229   0.9077
   3.750   0.4136   0.00582   0.00170   0.0016   0.4908   0.9184
   4.000   0.4354   0.00632   0.00189   0.0026   0.3997   0.9303
   4.250   0.4499   0.00770   0.00245   0.0044   0.2014   0.9438
   4.500   0.4712   0.00881   0.00300   0.0049   0.0626   0.9550
   4.750   0.5029   0.00957   0.00358   0.0036   0.0160   0.9603
   5.000   0.5342   0.00992   0.00398   0.0026   0.0139   0.9663
   5.250   0.5658   0.01032   0.00441   0.0014   0.0118   0.9706
   5.500   0.5953   0.01123   0.00545   0.0006   0.0098   0.9739
   5.750   0.6254   0.01173   0.00600  -0.0002   0.0093   0.9778
   6.000   0.6514   0.01234   0.00669  -0.0002   0.0089   0.9831
   6.250   0.6825   0.01306   0.00746  -0.0014   0.0081   0.9851
   6.500   0.7121   0.01390   0.00837  -0.0023   0.0077   0.9879
   6.750   0.7425   0.01445   0.00894  -0.0034   0.0069   0.9909
   7.000   0.7687   0.01545   0.00999  -0.0037   0.0066   0.9941
   7.250   0.7966   0.01685   0.01149  -0.0045   0.0064   0.9961
   7.500   0.8229   0.01896   0.01373  -0.0049   0.0062   0.9978
   7.750   0.8492   0.02141   0.01644  -0.0052   0.0059   0.9992
   8.000   0.8712   0.02280   0.01800  -0.0046   0.0058   1.0000
   8.250   0.8834   0.02310   0.01840  -0.0018   0.0055   1.0000
   8.500   0.8924   0.02504   0.02057   0.0015   0.0053   1.0000
   8.750   0.8967   0.02777   0.02360   0.0055   0.0051   1.0000
   9.000   0.8920   0.03135   0.02752   0.0105   0.0055   1.0000
  12.250   0.6754   0.09174   0.09013   0.0260   0.0070   1.0000
  12.500   0.6523   0.10698   0.10537   0.0171   0.0071   1.0000
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