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R140 12.04% (smoothed) (r140sm-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: R140 12.04% (smoothed) (r140sm-il)
Reynolds number: 500,000
Max Cl/Cd: 53.26 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-r140sm-il-500000-n5.txt
Download as CSV file: xf-r140sm-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.7157   0.05986   0.05742  -0.0471   1.0000   0.0032
 -11.250  -0.7340   0.05537   0.05283  -0.0490   1.0000   0.0031
 -11.000  -0.7660   0.04832   0.04548  -0.0488   1.0000   0.0032
 -10.750  -0.7896   0.04404   0.04097  -0.0468   1.0000   0.0032
 -10.500  -0.8135   0.04055   0.03727  -0.0431   1.0000   0.0031
 -10.250  -0.8226   0.03801   0.03448  -0.0392   1.0000   0.0033
 -10.000  -0.8421   0.03521   0.03142  -0.0332   1.0000   0.0032
  -9.750  -0.8495   0.03262   0.02854  -0.0286   1.0000   0.0033
  -9.500  -0.8636   0.02878   0.02426  -0.0230   1.0000   0.0034
  -9.250  -0.8608   0.02692   0.02216  -0.0194   1.0000   0.0036
  -9.000  -0.8542   0.02552   0.02055  -0.0162   1.0000   0.0037
  -8.750  -0.8432   0.02463   0.01955  -0.0137   0.9997   0.0038
  -8.500  -0.8170   0.02324   0.01797  -0.0145   0.9962   0.0040
  -8.250  -0.7905   0.02231   0.01691  -0.0151   0.9914   0.0043
  -8.000  -0.7627   0.02152   0.01600  -0.0159   0.9869   0.0049
  -7.750  -0.7371   0.01995   0.01421  -0.0161   0.9821   0.0052
  -7.500  -0.7110   0.01866   0.01275  -0.0163   0.9767   0.0055
  -7.250  -0.6821   0.01738   0.01130  -0.0171   0.9728   0.0059
  -7.000  -0.6544   0.01649   0.01028  -0.0176   0.9668   0.0062
  -6.750  -0.6282   0.01502   0.00865  -0.0180   0.9610   0.0070
  -6.500  -0.5996   0.01424   0.00779  -0.0188   0.9543   0.0077
  -6.250  -0.5686   0.01366   0.00715  -0.0200   0.9475   0.0086
  -6.000  -0.5385   0.01324   0.00667  -0.0208   0.9393   0.0101
  -5.750  -0.5093   0.01274   0.00608  -0.0215   0.9303   0.0109
  -5.500  -0.4853   0.01207   0.00527  -0.0210   0.9189   0.0122
  -5.250  -0.4612   0.01162   0.00474  -0.0204   0.9068   0.0142
  -5.000  -0.4367   0.01130   0.00433  -0.0199   0.8946   0.0169
  -4.750  -0.4128   0.01099   0.00393  -0.0192   0.8814   0.0211
  -4.500  -0.3899   0.01065   0.00360  -0.0184   0.8672   0.0333
  -4.250  -0.3671   0.01034   0.00331  -0.0175   0.8523   0.0548
  -4.000  -0.3452   0.00999   0.00301  -0.0165   0.8366   0.0860
  -3.750  -0.3258   0.00946   0.00271  -0.0152   0.8202   0.1565
  -3.500  -0.3146   0.00835   0.00222  -0.0125   0.8032   0.3291
  -3.000  -0.2807   0.00732   0.00184  -0.0085   0.7725   0.5318
  -2.750  -0.2574   0.00722   0.00176  -0.0076   0.7592   0.5639
  -2.500  -0.2336   0.00715   0.00169  -0.0068   0.7468   0.5943
  -2.250  -0.2090   0.00712   0.00161  -0.0062   0.7353   0.6158
  -2.000  -0.1842   0.00709   0.00155  -0.0056   0.7248   0.6335
  -1.750  -0.1584   0.00706   0.00149  -0.0052   0.7150   0.6449
  -1.250  -0.1065   0.00703   0.00137  -0.0046   0.6972   0.6649
  -1.000  -0.0801   0.00701   0.00132  -0.0044   0.6887   0.6723
  -0.750  -0.0537   0.00700   0.00129  -0.0042   0.6814   0.6800
  -0.500  -0.0272   0.00698   0.00126  -0.0040   0.6738   0.6873
  -0.250  -0.0008   0.00698   0.00124  -0.0038   0.6670   0.6957
   0.000   0.0254   0.00696   0.00124  -0.0036   0.6599   0.7045
   0.250   0.0517   0.00695   0.00124  -0.0033   0.6540   0.7145
   0.500   0.0780   0.00693   0.00126  -0.0031   0.6476   0.7258
   1.000   0.1301   0.00692   0.00133  -0.0025   0.6355   0.7526
   1.250   0.1560   0.00692   0.00138  -0.0022   0.6300   0.7675
   1.500   0.1822   0.00692   0.00145  -0.0019   0.6245   0.7827
   1.750   0.2085   0.00693   0.00152  -0.0017   0.6186   0.7970
   2.000   0.2347   0.00696   0.00159  -0.0014   0.6125   0.8109
   2.250   0.2607   0.00699   0.00166  -0.0011   0.6033   0.8241
   2.500   0.2862   0.00703   0.00174  -0.0006   0.5895   0.8367
   2.750   0.3118   0.00708   0.00182  -0.0002   0.5754   0.8491
   3.000   0.3377   0.00714   0.00191   0.0001   0.5611   0.8611
   3.500   0.3892   0.00733   0.00212   0.0009   0.5143   0.8848
   3.750   0.4106   0.00771   0.00227   0.0020   0.4378   0.8969
   4.000   0.4273   0.00866   0.00265   0.0037   0.2929   0.9099
   4.250   0.4437   0.00998   0.00326   0.0050   0.1208   0.9228
   4.500   0.4709   0.01055   0.00367   0.0046   0.0709   0.9329
   4.750   0.4996   0.01124   0.00413   0.0038   0.0210   0.9410
   5.000   0.5306   0.01165   0.00459   0.0027   0.0154   0.9478
   5.250   0.5619   0.01217   0.00521   0.0017   0.0127   0.9537
   5.500   0.5916   0.01258   0.00569   0.0009   0.0116   0.9600
   5.750   0.6236   0.01303   0.00619  -0.0005   0.0099   0.9638
   6.000   0.6509   0.01357   0.00677  -0.0008   0.0085   0.9697
   6.250   0.6748   0.01456   0.00787  -0.0006   0.0075   0.9757
   6.500   0.6995   0.01546   0.00887  -0.0006   0.0071   0.9816
   6.750   0.7256   0.01622   0.00974  -0.0008   0.0067   0.9866
   7.000   0.7524   0.01711   0.01073  -0.0012   0.0061   0.9908
   7.250   0.7808   0.01756   0.01122  -0.0020   0.0052   0.9944
   7.500   0.8088   0.01841   0.01215  -0.0028   0.0049   0.9979
   7.750   0.8347   0.01921   0.01302  -0.0032   0.0045   1.0000
   8.000   0.8453   0.02006   0.01396  -0.0003   0.0044   1.0000
   8.250   0.8564   0.02095   0.01492   0.0024   0.0042   1.0000
   8.500   0.8639   0.02299   0.01715   0.0056   0.0039   1.0000
   8.750   0.8757   0.02434   0.01867   0.0081   0.0038   1.0000
   9.000   0.8877   0.02556   0.02012   0.0106   0.0037   1.0000
   9.250   0.8978   0.02712   0.02190   0.0132   0.0035   1.0000
   9.500   0.9046   0.02911   0.02414   0.0163   0.0034   1.0000
   9.750   0.9069   0.03155   0.02688   0.0198   0.0033   1.0000
  10.000   0.9005   0.03440   0.03006   0.0246   0.0032   1.0000
  10.250   0.8927   0.03667   0.03255   0.0292   0.0032   1.0000
  10.500   0.8724   0.04079   0.03704   0.0345   0.0031   1.0000
  10.750   0.8583   0.04383   0.04030   0.0379   0.0032   1.0000
  11.000   0.8425   0.04725   0.04394   0.0405   0.0032   1.0000
  11.250   0.8234   0.05126   0.04815   0.0421   0.0032   1.0000
  11.500   0.8017   0.05618   0.05327   0.0425   0.0032   1.0000
  11.750   0.7815   0.06121   0.05846   0.0416   0.0032   1.0000
  12.000   0.7582   0.06742   0.06484   0.0393   0.0032   1.0000
  12.250   0.7395   0.07369   0.07123   0.0360   0.0033   1.0000
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