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DU 86-137/25 AIRFOIL (du861372-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: DU 86-137/25 AIRFOIL (du861372-il)
Reynolds number: 50,000
Max Cl/Cd: 28.94 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-du861372-il-50000.txt
Download as CSV file: xf-du861372-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DU 86-137/25 AIRFOIL                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.5954   0.10565   0.10048  -0.0237   1.0000   0.1604
 -11.000  -0.6223   0.09386   0.08876  -0.0317   1.0000   0.1384
 -10.750  -0.6967   0.08322   0.07816  -0.0393   1.0000   0.1328
 -10.500  -0.7489   0.07867   0.07350  -0.0396   1.0000   0.1316
 -10.250  -0.7369   0.07336   0.06814  -0.0400   1.0000   0.1248
 -10.000  -0.7625   0.06944   0.06411  -0.0381   1.0000   0.1222
  -9.750  -0.7931   0.06556   0.05994  -0.0353   1.0000   0.1190
  -9.500  -0.8236   0.06277   0.05654  -0.0312   1.0000   0.1152
  -9.250  -0.8101   0.05834   0.05208  -0.0306   1.0000   0.1122
  -9.000  -0.8102   0.05491   0.04838  -0.0284   1.0000   0.1098
  -8.750  -0.8028   0.05115   0.04419  -0.0273   0.9717   0.1073
  -8.500  -0.7890   0.04743   0.03987  -0.0268   0.9508   0.1051
  -8.250  -0.7694   0.04418   0.03594  -0.0263   0.9381   0.1032
  -8.000  -0.7404   0.04127   0.03255  -0.0267   0.9305   0.1018
  -7.750  -0.7046   0.03834   0.02939  -0.0278   0.9256   0.1007
  -7.500  -0.6598   0.03572   0.02655  -0.0296   0.9235   0.1000
  -7.250  -0.5992   0.03359   0.02426  -0.0325   0.9262   0.1005
  -7.000  -0.5421   0.03225   0.02285  -0.0348   0.9299   0.1026
  -6.750  -0.5133   0.03116   0.02178  -0.0348   0.9249   0.1057
  -6.500  -0.4912   0.03010   0.02067  -0.0344   0.9186   0.1103
  -6.250  -0.4731   0.02900   0.01951  -0.0336   0.9121   0.1174
  -6.000  -0.4587   0.02787   0.01840  -0.0323   0.9046   0.1322
  -5.750  -0.4496   0.02636   0.01711  -0.0305   0.8986   0.1715
  -5.500  -0.4597   0.02408   0.01607  -0.0263   0.8903   0.3185
  -5.250  -0.4264   0.02571   0.01905  -0.0215   0.8891   0.6001
  -5.000  -0.4054   0.02676   0.01983  -0.0186   0.8846   0.6462
  -4.750  -0.3851   0.02795   0.02079  -0.0155   0.8807   0.6843
  -4.500  -0.3489   0.02924   0.02183  -0.0147   0.8790   0.7064
  -4.250  -0.3159   0.03029   0.02265  -0.0137   0.8762   0.7288
  -4.000  -0.2907   0.03095   0.02310  -0.0122   0.8718   0.7507
  -3.750  -0.2470   0.03178   0.02372  -0.0130   0.8694   0.7706
  -3.500  -0.2106   0.03188   0.02361  -0.0141   0.8655   0.7841
  -3.250  -0.1652   0.03193   0.02344  -0.0166   0.8628   0.7962
  -3.000  -0.1340   0.03187   0.02323  -0.0172   0.8581   0.8091
  -2.750  -0.1103   0.03173   0.02297  -0.0169   0.8533   0.8219
  -2.500  -0.0732   0.03172   0.02283  -0.0184   0.8510   0.8379
  -2.250  -0.0328   0.03163   0.02263  -0.0206   0.8492   0.8543
  -2.000   0.0088   0.03128   0.02217  -0.0235   0.8473   0.8654
  -1.750   0.0480   0.03096   0.02176  -0.0260   0.8456   0.8791
  -1.500   0.0905   0.03077   0.02150  -0.0289   0.8441   0.9015
  -1.250   0.1603   0.03001   0.02069  -0.0368   0.8449   0.9319
  -1.000   0.2034   0.02941   0.02006  -0.0408   0.8427   0.9473
  -0.750   0.3227   0.02684   0.01750  -0.0599   0.8475   1.0000
  -0.500   0.3423   0.02674   0.01738  -0.0598   0.8431   1.0000
  -0.250   0.3608   0.02670   0.01737  -0.0595   0.8374   1.0000
   0.000   0.3801   0.02667   0.01735  -0.0593   0.8325   1.0000
   0.250   0.4003   0.02666   0.01735  -0.0591   0.8284   1.0000
   0.500   0.4178   0.02677   0.01750  -0.0586   0.8225   1.0000
   0.750   0.4359   0.02689   0.01766  -0.0581   0.8170   1.0000
   1.000   0.4553   0.02699   0.01779  -0.0576   0.8125   1.0000
   1.250   0.4729   0.02719   0.01807  -0.0570   0.8063   1.0000
   1.500   0.4907   0.02737   0.01830  -0.0562   0.7991   1.0000
   1.750   0.5100   0.02746   0.01843  -0.0553   0.7921   1.0000
   2.000   0.5254   0.02767   0.01872  -0.0539   0.7824   1.0000
   2.250   0.5427   0.02783   0.01897  -0.0527   0.7743   1.0000
   2.500   0.5587   0.02799   0.01922  -0.0511   0.7650   1.0000
   2.750   0.5728   0.02822   0.01956  -0.0493   0.7544   1.0000
   3.000   0.5902   0.02823   0.01967  -0.0476   0.7451   1.0000
   3.250   0.6031   0.02842   0.02002  -0.0455   0.7333   1.0000
   3.500   0.6150   0.02860   0.02036  -0.0433   0.7205   1.0000
   3.750   0.6279   0.02860   0.02050  -0.0409   0.7069   1.0000
   4.000   0.6404   0.02838   0.02044  -0.0381   0.6900   1.0000
   4.250   0.6536   0.02786   0.02008  -0.0349   0.6696   1.0000
   4.500   0.6653   0.02725   0.01966  -0.0314   0.6446   1.0000
   4.750   0.6775   0.02641   0.01897  -0.0275   0.6109   1.0000
   5.000   0.6930   0.02529   0.01786  -0.0234   0.5581   1.0000
   5.250   0.7085   0.02448   0.01644  -0.0186   0.4671   1.0000
   5.500   0.7115   0.02541   0.01646  -0.0137   0.3925   1.0000
   5.750   0.7116   0.02640   0.01717  -0.0096   0.3294   1.0000
   6.000   0.7879   0.03681   0.02578  -0.0165   0.2491   1.0000
   6.250   0.7945   0.03780   0.02737  -0.0132   0.2288   1.0000
   6.500   0.8049   0.03862   0.02843  -0.0106   0.2106   1.0000
   6.750   0.8144   0.03925   0.02940  -0.0076   0.1957   1.0000
   7.000   0.8248   0.03989   0.03019  -0.0049   0.1831   1.0000
   7.250   0.8336   0.03973   0.02998  -0.0021   0.1733   1.0000
   7.500   0.8433   0.04208   0.03275   0.0007   0.1641   1.0000
   7.750   0.8523   0.04282   0.03342   0.0034   0.1570   1.0000
   8.000   0.8537   0.04541   0.03651   0.0070   0.1499   1.0000
   8.250   0.8605   0.04676   0.03791   0.0099   0.1442   1.0000
   8.500   0.8633   0.04925   0.04051   0.0130   0.1411   1.0000
   8.750   0.8537   0.05210   0.04380   0.0177   0.1396   1.0000
   9.000   0.8416   0.05481   0.04685   0.0224   0.1386   1.0000
   9.250   0.8274   0.05765   0.04997   0.0269   0.1373   1.0000
   9.500   0.8148   0.06101   0.05360   0.0302   0.1368   1.0000
   9.750   0.8011   0.06468   0.05752   0.0327   0.1364   1.0000
  10.000   0.7853   0.06860   0.06163   0.0346   0.1367   1.0000
  10.250   0.7670   0.07263   0.06579   0.0361   0.1377   1.0000
  10.500   0.7475   0.07675   0.06998   0.0372   0.1389   1.0000
  10.750   0.7361   0.08147   0.07474   0.0371   0.1404   1.0000
  11.000   0.6223   0.09581   0.08902   0.0263   0.1668   1.0000
  11.250   0.6221   0.10219   0.09539   0.0239   0.1720   1.0000
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