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R140 12.04% (smoothed) (r140sm-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: R140 12.04% (smoothed) (r140sm-il)
Reynolds number: 50,000
Max Cl/Cd: 22.77 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-r140sm-il-50000.txt
Download as CSV file: xf-r140sm-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5918   0.08357   0.07719  -0.0293   1.0000   0.2079
  -8.750  -0.6345   0.07741   0.07113  -0.0325   1.0000   0.1932
  -8.500  -0.6913   0.07326   0.06682  -0.0318   1.0000   0.1745
  -8.250  -0.6988   0.06658   0.05988  -0.0315   1.0000   0.1433
  -8.000  -0.7127   0.06231   0.05527  -0.0288   1.0000   0.1302
  -7.750  -0.7261   0.05880   0.05121  -0.0248   1.0000   0.1191
  -7.500  -0.7194   0.05471   0.04698  -0.0226   1.0000   0.1151
  -7.250  -0.7233   0.05131   0.04302  -0.0186   1.0000   0.1090
  -7.000  -0.7178   0.04849   0.03970  -0.0151   1.0000   0.1055
  -6.750  -0.7068   0.04504   0.03599  -0.0125   1.0000   0.1030
  -6.500  -0.6953   0.04194   0.03249  -0.0096   1.0000   0.1003
  -6.250  -0.6803   0.03908   0.02919  -0.0070   1.0000   0.0987
  -6.000  -0.6615   0.03639   0.02610  -0.0048   1.0000   0.0989
  -5.750  -0.6415   0.03424   0.02356  -0.0028   1.0000   0.1034
  -5.500  -0.6164   0.03188   0.02102  -0.0017   1.0000   0.1111
  -5.250  -0.5825   0.02977   0.01871  -0.0014   1.0000   0.1198
  -5.000  -0.5519   0.02762   0.01681  -0.0009   1.0000   0.1405
  -4.750  -0.5366   0.02575   0.01512   0.0017   1.0000   0.1717
  -4.500  -0.2741   0.03374   0.02467  -0.0056   1.0000   0.8917
  -4.250  -0.2384   0.03288   0.02345  -0.0081   1.0000   0.9118
  -4.000  -0.2064   0.03188   0.02219  -0.0106   1.0000   0.9254
  -3.750  -0.1732   0.03088   0.02097  -0.0133   1.0000   0.9383
  -3.500  -0.1401   0.02990   0.01976  -0.0161   1.0000   0.9505
  -3.250  -0.1059   0.02894   0.01863  -0.0193   1.0000   0.9628
  -3.000  -0.0699   0.02798   0.01751  -0.0229   1.0000   0.9751
  -2.750  -0.0316   0.02700   0.01640  -0.0271   1.0000   0.9871
  -2.500   0.0114   0.02597   0.01521  -0.0323   1.0000   0.9993
  -2.250   0.0188   0.02564   0.01488  -0.0308   1.0000   1.0000
  -2.000   0.0204   0.02547   0.01474  -0.0282   1.0000   1.0000
  -1.750   0.0173   0.02542   0.01473  -0.0250   1.0000   1.0000
  -1.500   0.0093   0.02551   0.01483  -0.0211   1.0000   1.0000
  -1.250  -0.0021   0.02565   0.01500  -0.0169   1.0000   1.0000
  -1.000  -0.0150   0.02580   0.01515  -0.0126   1.0000   1.0000
  -0.750  -0.0279   0.02588   0.01522  -0.0084   1.0000   1.0000
  -0.500  -0.0406   0.02588   0.01522  -0.0042   1.0000   1.0000
  -0.250  -0.0527   0.02582   0.01512  -0.0001   1.0000   1.0000
   0.000  -0.0637   0.02571   0.01498   0.0041   1.0000   1.0000
   0.250  -0.0726   0.02561   0.01481   0.0080   1.0000   1.0000
   0.500  -0.0780   0.02556   0.01469   0.0116   1.0000   1.0000
   0.750  -0.0793   0.02561   0.01466   0.0147   1.0000   1.0000
   1.000  -0.0766   0.02576   0.01472   0.0172   1.0000   1.0000
   1.250  -0.0466   0.02641   0.01533   0.0146   0.9930   1.0000
   1.500  -0.0127   0.02717   0.01606   0.0114   0.9841   1.0000
   1.750   0.0164   0.02784   0.01673   0.0092   0.9751   1.0000
   2.000   0.0475   0.02867   0.01755   0.0067   0.9668   1.0000
   2.250   0.0747   0.02940   0.01830   0.0050   0.9580   1.0000
   2.500   0.0990   0.03014   0.01907   0.0039   0.9497   1.0000
   2.750   0.1328   0.03113   0.02015   0.0011   0.9412   1.0000
   3.000   0.1499   0.03179   0.02085   0.0014   0.9323   1.0000
   3.250   0.1760   0.03269   0.02183   0.0001   0.9232   1.0000
   3.500   0.2077   0.03371   0.02297  -0.0021   0.9138   1.0000
   3.750   0.2257   0.03449   0.02389  -0.0019   0.9034   1.0000
   4.000   0.2512   0.03542   0.02496  -0.0029   0.8915   1.0000
   4.250   0.2790   0.03638   0.02608  -0.0042   0.8784   1.0000
   4.500   0.3079   0.03734   0.02725  -0.0055   0.8641   1.0000
   4.750   0.3370   0.03830   0.02848  -0.0068   0.8491   1.0000
   5.000   0.3686   0.03927   0.02973  -0.0083   0.8332   1.0000
   5.250   0.4102   0.04023   0.03106  -0.0111   0.8159   1.0000
   5.500   0.5539   0.03655   0.02881  -0.0215   0.7477   1.0000
   5.750   0.6172   0.02711   0.01627   0.0013   0.1515   1.0000
   6.000   0.6238   0.02894   0.01792   0.0051   0.1302   1.0000
   6.250   0.6502   0.03119   0.01992   0.0061   0.1099   1.0000
   6.500   0.6995   0.03373   0.02253   0.0044   0.0983   1.0000
   6.750   0.7401   0.03685   0.02589   0.0037   0.0945   1.0000
   7.000   0.7628   0.03927   0.02874   0.0053   0.0914   1.0000
   7.250   0.7815   0.04187   0.03169   0.0072   0.0886   1.0000
   7.500   0.7972   0.04487   0.03511   0.0096   0.0886   1.0000
   7.750   0.8093   0.04817   0.03885   0.0123   0.0911   1.0000
   8.000   0.8188   0.05173   0.04276   0.0148   0.0938   1.0000
   8.250   0.8336   0.05603   0.04724   0.0164   0.0971   1.0000
   8.500   0.8180   0.05851   0.05057   0.0220   0.1036   1.0000
   8.750   0.8365   0.06421   0.05634   0.0224   0.1103   1.0000
   9.000   0.8018   0.06619   0.05898   0.0281   0.1163   1.0000
   9.250   0.7986   0.07078   0.06378   0.0299   0.1257   1.0000
   9.500   0.7620   0.07427   0.06750   0.0331   0.1291   1.0000
   9.750   0.7495   0.07900   0.07231   0.0342   0.1389   1.0000
  10.000   0.7127   0.08306   0.07640   0.0344   0.1399   1.0000
  10.250   0.6745   0.08915   0.08245   0.0309   0.1417   1.0000
  10.500   0.5685   0.08608   0.07970   0.0333   0.1271   1.0000
  10.750   0.5501   0.09434   0.08794   0.0293   0.1386   1.0000
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