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R140 12.04% (smoothed) (r140sm-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: R140 12.04% (smoothed) (r140sm-il)
Reynolds number: 200,000
Max Cl/Cd: 46.55 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-r140sm-il-200000-n5.txt
Download as CSV file: xf-r140sm-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.5579   0.11377   0.11012  -0.0222   1.0000   0.0109
 -12.000  -0.5629   0.10826   0.10465  -0.0244   1.0000   0.0107
 -11.750  -0.5679   0.10273   0.09915  -0.0268   1.0000   0.0105
 -11.500  -0.5754   0.09611   0.09257  -0.0300   1.0000   0.0104
 -11.250  -0.5835   0.08876   0.08526  -0.0342   1.0000   0.0102
 -11.000  -0.6011   0.07894   0.07541  -0.0408   1.0000   0.0100
 -10.750  -0.6202   0.07190   0.06829  -0.0452   1.0000   0.0099
 -10.500  -0.6369   0.06696   0.06327  -0.0477   1.0000   0.0097
 -10.250  -0.6572   0.06214   0.05832  -0.0488   1.0000   0.0097
 -10.000  -0.6755   0.05841   0.05446  -0.0482   1.0000   0.0096
  -9.750  -0.6939   0.05510   0.05102  -0.0460   1.0000   0.0096
  -9.500  -0.7122   0.05216   0.04792  -0.0421   1.0000   0.0096
  -9.250  -0.7288   0.04934   0.04493  -0.0375   1.0000   0.0095
  -9.000  -0.7397   0.04632   0.04168  -0.0334   1.0000   0.0095
  -8.750  -0.7481   0.04320   0.03830  -0.0292   1.0000   0.0094
  -8.500  -0.7527   0.04026   0.03507  -0.0250   1.0000   0.0094
  -8.250  -0.7549   0.03734   0.03183  -0.0208   1.0000   0.0095
  -8.000  -0.7544   0.03458   0.02873  -0.0167   1.0000   0.0095
  -7.750  -0.7506   0.03214   0.02596  -0.0129   1.0000   0.0097
  -7.500  -0.7440   0.02996   0.02345  -0.0094   1.0000   0.0099
  -7.250  -0.7349   0.02793   0.02110  -0.0062   1.0000   0.0102
  -7.000  -0.7088   0.02582   0.01865  -0.0063   0.9968   0.0106
  -6.750  -0.6800   0.02347   0.01595  -0.0070   0.9926   0.0115
  -6.500  -0.6512   0.02188   0.01426  -0.0080   0.9876   0.0131
  -6.250  -0.6208   0.02071   0.01297  -0.0091   0.9827   0.0147
  -6.000  -0.5924   0.01933   0.01146  -0.0096   0.9765   0.0160
  -5.750  -0.5629   0.01816   0.01016  -0.0104   0.9711   0.0174
  -5.500  -0.5363   0.01715   0.00904  -0.0106   0.9636   0.0194
  -5.250  -0.5059   0.01619   0.00801  -0.0118   0.9581   0.0238
  -5.000  -0.4784   0.01549   0.00713  -0.0120   0.9497   0.0274
  -4.750  -0.4489   0.01473   0.00633  -0.0127   0.9426   0.0379
  -4.500  -0.4220   0.01395   0.00570  -0.0130   0.9339   0.0738
  -4.250  -0.3986   0.01306   0.00513  -0.0128   0.9238   0.1508
  -4.000  -0.3878   0.01134   0.00446  -0.0106   0.9116   0.3778
  -3.750  -0.3737   0.01051   0.00435  -0.0080   0.8997   0.5440
  -3.500  -0.3473   0.01032   0.00417  -0.0075   0.8899   0.5954
  -3.250  -0.3214   0.01020   0.00400  -0.0070   0.8783   0.6240
  -3.000  -0.2962   0.01007   0.00386  -0.0063   0.8664   0.6530
  -2.750  -0.2702   0.00994   0.00374  -0.0057   0.8546   0.6767
  -2.500  -0.2434   0.00984   0.00359  -0.0054   0.8427   0.6943
  -2.250  -0.2159   0.00975   0.00342  -0.0052   0.8308   0.7071
  -2.000  -0.1881   0.00968   0.00328  -0.0052   0.8190   0.7170
  -1.750  -0.1605   0.00962   0.00314  -0.0051   0.8073   0.7266
  -1.500  -0.1333   0.00958   0.00303  -0.0050   0.7955   0.7362
  -1.250  -0.1060   0.00955   0.00294  -0.0048   0.7840   0.7459
  -1.000  -0.0790   0.00953   0.00288  -0.0047   0.7732   0.7563
  -0.750  -0.0520   0.00953   0.00282  -0.0045   0.7630   0.7674
  -0.500  -0.0249   0.00954   0.00279  -0.0043   0.7534   0.7787
  -0.250   0.0022   0.00955   0.00278  -0.0042   0.7438   0.7900
   0.000   0.0296   0.00958   0.00279  -0.0041   0.7350   0.8015
   0.250   0.0570   0.00961   0.00281  -0.0040   0.7266   0.8131
   0.500   0.0844   0.00965   0.00286  -0.0039   0.7184   0.8249
   1.000   0.1397   0.00975   0.00297  -0.0039   0.7030   0.8484
   1.250   0.1696   0.00982   0.00305  -0.0044   0.6965   0.8588
   1.500   0.1995   0.00989   0.00319  -0.0049   0.6891   0.8692
   1.750   0.2297   0.00999   0.00329  -0.0054   0.6829   0.8796
   2.000   0.2592   0.01007   0.00344  -0.0059   0.6757   0.8904
   2.250   0.2934   0.01020   0.00360  -0.0073   0.6698   0.8981
   2.500   0.3250   0.01030   0.00381  -0.0082   0.6628   0.9070
   2.750   0.3575   0.01043   0.00399  -0.0092   0.6563   0.9152
   3.000   0.3903   0.01054   0.00416  -0.0103   0.6440   0.9221
   3.250   0.4195   0.01063   0.00428  -0.0106   0.6260   0.9305
   3.500   0.4528   0.01074   0.00448  -0.0118   0.6069   0.9360
   3.750   0.4831   0.01086   0.00464  -0.0123   0.5876   0.9430
   4.000   0.5125   0.01101   0.00471  -0.0126   0.5353   0.9489
   4.250   0.5313   0.01172   0.00478  -0.0111   0.3851   0.9575
   4.500   0.5437   0.01385   0.00564  -0.0098   0.1306   0.9657
   4.750   0.5657   0.01493   0.00640  -0.0095   0.0507   0.9737
   5.000   0.5949   0.01576   0.00715  -0.0104   0.0269   0.9791
   5.250   0.6220   0.01656   0.00802  -0.0108   0.0205   0.9857
   5.500   0.6520   0.01732   0.00895  -0.0118   0.0185   0.9908
   5.750   0.6798   0.01827   0.01003  -0.0124   0.0168   0.9963
   6.000   0.7044   0.01923   0.01105  -0.0126   0.0146   1.0000
   6.250   0.7094   0.02036   0.01224  -0.0088   0.0132   1.0000
   6.500   0.7186   0.02140   0.01334  -0.0056   0.0124   1.0000
   6.750   0.7311   0.02237   0.01445  -0.0029   0.0119   1.0000
   7.000   0.7453   0.02357   0.01576  -0.0005   0.0114   1.0000
   7.250   0.7614   0.02496   0.01730   0.0016   0.0109   1.0000
   7.500   0.7785   0.02656   0.01908   0.0034   0.0106   1.0000
   7.750   0.7952   0.02842   0.02117   0.0054   0.0103   1.0000
   8.000   0.8100   0.03047   0.02349   0.0075   0.0101   1.0000
   8.250   0.8221   0.03225   0.02551   0.0099   0.0096   1.0000
   8.500   0.8324   0.03347   0.02688   0.0123   0.0088   1.0000
   8.750   0.8404   0.03527   0.02890   0.0150   0.0084   1.0000
   9.000   0.8451   0.03663   0.03036   0.0177   0.0078   1.0000
   9.250   0.8423   0.03969   0.03369   0.0213   0.0074   1.0000
   9.500   0.8384   0.04242   0.03670   0.0250   0.0074   1.0000
   9.750   0.8298   0.04498   0.03951   0.0293   0.0073   1.0000
  10.000   0.8143   0.04761   0.04237   0.0341   0.0072   1.0000
  10.500   0.7871   0.05304   0.04827   0.0402   0.0071   1.0000
  10.750   0.7716   0.05649   0.05188   0.0417   0.0072   1.0000
  11.000   0.7567   0.06014   0.05567   0.0423   0.0073   1.0000
  11.500   0.7222   0.06909   0.06495   0.0406   0.0072   1.0000
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