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R140 (original) (r140-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: R140 (original) (r140-il)
Reynolds number: 100,000
Max Cl/Cd: 36.12 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-r140-il-100000-n5.txt
Download as CSV file: xf-r140-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: R140 (original)                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5525   0.09318   0.08839  -0.0330   1.0000   0.0124
 -10.500  -0.5621   0.08560   0.08085  -0.0378   1.0000   0.0122
 -10.250  -0.5744   0.07912   0.07435  -0.0420   1.0000   0.0120
 -10.000  -0.5891   0.07364   0.06882  -0.0451   1.0000   0.0119
  -9.750  -0.6086   0.06854   0.06364  -0.0469   1.0000   0.0118
  -9.500  -0.6243   0.06487   0.05987  -0.0470   1.0000   0.0117
  -9.250  -0.6434   0.06131   0.05621  -0.0453   1.0000   0.0117
  -9.000  -0.6599   0.05852   0.05330  -0.0422   1.0000   0.0116
  -8.750  -0.6739   0.05577   0.05040  -0.0386   1.0000   0.0115
  -8.500  -0.6849   0.05271   0.04714  -0.0350   1.0000   0.0114
  -8.250  -0.6926   0.04970   0.04390  -0.0313   1.0000   0.0112
  -8.000  -0.6976   0.04669   0.04063  -0.0275   1.0000   0.0111
  -7.750  -0.6997   0.04376   0.03739  -0.0237   1.0000   0.0110
  -7.500  -0.6994   0.04080   0.03411  -0.0199   1.0000   0.0109
  -7.250  -0.6959   0.03807   0.03103  -0.0162   1.0000   0.0108
  -7.000  -0.6895   0.03539   0.02799  -0.0127   1.0000   0.0107
  -6.750  -0.6800   0.03285   0.02510  -0.0096   1.0000   0.0107
  -6.500  -0.6674   0.03062   0.02243  -0.0069   1.0000   0.0107
  -6.250  -0.6526   0.02852   0.02005  -0.0044   1.0000   0.0107
  -6.000  -0.6376   0.02671   0.01801  -0.0019   1.0000   0.0109
  -5.750  -0.6238   0.02526   0.01638   0.0006   1.0000   0.0110
  -5.500  -0.6083   0.02391   0.01486   0.0027   0.9989   0.0113
  -5.250  -0.5775   0.02237   0.01308   0.0017   0.9916   0.0118
  -5.000  -0.5463   0.02116   0.01159   0.0006   0.9837   0.0127
  -4.750  -0.5147   0.02022   0.01036  -0.0005   0.9753   0.0139
  -4.500  -0.4842   0.01933   0.00933  -0.0013   0.9668   0.0183
  -4.250  -0.4499   0.01859   0.00857  -0.0031   0.9603   0.0438
  -4.000  -0.4218   0.01773   0.00783  -0.0037   0.9513   0.0955
  -3.750  -0.3895   0.01686   0.00705  -0.0053   0.9449   0.1644
  -3.500  -0.3691   0.01543   0.00642  -0.0049   0.9346   0.3558
  -3.250  -0.3463   0.01474   0.00617  -0.0042   0.9236   0.4716
  -3.000  -0.3209   0.01436   0.00613  -0.0035   0.9138   0.5746
  -2.750  -0.2957   0.01411   0.00622  -0.0023   0.9056   0.6789
  -2.500  -0.2646   0.01411   0.00640  -0.0022   0.8970   0.7218
  -2.250  -0.2339   0.01415   0.00634  -0.0023   0.8881   0.7508
  -2.000  -0.2007   0.01417   0.00629  -0.0031   0.8801   0.7707
  -1.750  -0.1726   0.01420   0.00625  -0.0030   0.8684   0.7855
  -1.500  -0.1449   0.01420   0.00618  -0.0028   0.8565   0.8011
  -1.250  -0.1148   0.01418   0.00605  -0.0031   0.8456   0.8141
  -1.000  -0.0814   0.01416   0.00598  -0.0041   0.8367   0.8260
  -0.750  -0.0479   0.01414   0.00589  -0.0051   0.8284   0.8375
  -0.500  -0.0128   0.01416   0.00586  -0.0064   0.8203   0.8473
  -0.250   0.0229   0.01415   0.00578  -0.0080   0.8135   0.8564
   0.000   0.0532   0.01419   0.00579  -0.0086   0.8039   0.8665
   0.250   0.0865   0.01426   0.00586  -0.0098   0.7951   0.8756
   0.500   0.1224   0.01434   0.00595  -0.0115   0.7866   0.8837
   0.750   0.1535   0.01443   0.00607  -0.0123   0.7770   0.8934
   1.000   0.1899   0.01451   0.00618  -0.0142   0.7690   0.9003
   1.250   0.2239   0.01456   0.00625  -0.0155   0.7615   0.9082
   1.500   0.2585   0.01464   0.00639  -0.0171   0.7533   0.9159
   1.750   0.2948   0.01469   0.00655  -0.0188   0.7456   0.9231
   2.000   0.3265   0.01478   0.00669  -0.0197   0.7356   0.9328
   2.250   0.3660   0.01485   0.00686  -0.0222   0.7246   0.9380
   2.500   0.3977   0.01491   0.00699  -0.0230   0.7113   0.9469
   2.750   0.4352   0.01495   0.00720  -0.0250   0.6961   0.9526
   3.000   0.4612   0.01481   0.00690  -0.0239   0.6420   0.9611
   3.250   0.4945   0.01481   0.00696  -0.0249   0.6087   0.9677
   3.500   0.5261   0.01488   0.00712  -0.0257   0.5846   0.9749
   3.750   0.5504   0.01524   0.00700  -0.0249   0.4492   0.9832
   4.000   0.5668   0.01717   0.00762  -0.0241   0.1892   0.9917
   4.250   0.5880   0.01919   0.00868  -0.0245   0.0212   0.9997
   4.500   0.6017   0.01973   0.00933  -0.0220   0.0152   1.0000
   4.750   0.6125   0.02041   0.01021  -0.0190   0.0122   1.0000
   5.000   0.6238   0.02104   0.01096  -0.0162   0.0106   1.0000
   5.250   0.6345   0.02171   0.01179  -0.0132   0.0098   1.0000
   5.500   0.6437   0.02252   0.01277  -0.0099   0.0092   1.0000
   5.750   0.6529   0.02340   0.01378  -0.0067   0.0091   1.0000
   6.000   0.6614   0.02446   0.01499  -0.0033   0.0089   1.0000
   6.250   0.6717   0.02562   0.01627  -0.0003   0.0088   1.0000
   6.500   0.6845   0.02696   0.01773   0.0023   0.0088   1.0000
   6.750   0.7006   0.02864   0.01956   0.0045   0.0087   1.0000
   7.000   0.7190   0.03051   0.02163   0.0062   0.0088   1.0000
   7.250   0.7373   0.03261   0.02398   0.0080   0.0089   1.0000
   7.500   0.7533   0.03505   0.02673   0.0100   0.0089   1.0000
   7.750   0.7657   0.03748   0.02949   0.0125   0.0090   1.0000
   8.000   0.7742   0.04012   0.03248   0.0153   0.0092   1.0000
   8.250   0.7786   0.04299   0.03570   0.0186   0.0093   1.0000
   8.500   0.7797   0.04581   0.03884   0.0220   0.0095   1.0000
   8.750   0.7781   0.04852   0.04196   0.0254   0.0096   1.0000
   9.000   0.7723   0.05138   0.04509   0.0290   0.0097   1.0000
   9.250   0.7628   0.05407   0.04800   0.0327   0.0099   1.0000
   9.500   0.7495   0.05666   0.05077   0.0364   0.0099   1.0000
   9.750   0.7354   0.05948   0.05376   0.0392   0.0100   1.0000
  10.000   0.7196   0.06274   0.05719   0.0410   0.0101   1.0000
  10.250   0.7047   0.06622   0.06080   0.0416   0.0101   1.0000
  10.500   0.6859   0.07066   0.06539   0.0410   0.0102   1.0000
  10.750   0.6696   0.07533   0.07016   0.0394   0.0102   1.0000
  11.000   0.6533   0.08069   0.07562   0.0368   0.0104   1.0000
  11.250   0.6363   0.08725   0.08214   0.0329   0.0104   1.0000
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