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WB-140/35/FB 14% (wb140-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: WB-140/35/FB 14% (wb140-il)
Reynolds number: 200,000
Max Cl/Cd: 83.95 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-wb140-il-200000.txt
Download as CSV file: xf-wb140-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WB-140/35/FB 14%                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.0277   0.09709   0.09360  -0.0994   0.9043   0.0675
 -10.500  -0.0514   0.09346   0.09003  -0.1050   0.8989   0.0713
 -10.250  -0.0426   0.08896   0.08551  -0.1041   0.8952   0.0730
 -10.000  -0.0221   0.08714   0.08366  -0.1022   0.8919   0.0757
  -9.750  -0.0164   0.08445   0.08094  -0.1025   0.8891   0.0799
  -9.500  -0.0467   0.08002   0.07658  -0.1100   0.8841   0.0846
  -9.250  -0.0284   0.07620   0.07275  -0.1074   0.8815   0.0867
  -9.000  -0.0089   0.07455   0.07106  -0.1058   0.8787   0.0905
  -8.750  -0.1046   0.07990   0.07636  -0.1097   0.8853   0.0865
  -8.500  -0.0836   0.07873   0.07516  -0.1073   0.8822   0.0895
  -8.250  -0.0064   0.06434   0.06088  -0.1095   0.8699   0.1023
  -8.000  -0.0025   0.06133   0.05787  -0.1105   0.8663   0.1058
  -7.750  -0.0290   0.05585   0.05246  -0.1164   0.8616   0.1116
  -7.500  -0.1499   0.03728   0.03245  -0.1428   0.8615   0.0574
  -7.250  -0.1402   0.03180   0.02581  -0.1426   0.8587   0.0490
  -7.000  -0.1180   0.02973   0.02348  -0.1424   0.8562   0.0479
  -6.750  -0.0994   0.02713   0.02058  -0.1419   0.8527   0.0465
  -6.500  -0.0768   0.02538   0.01852  -0.1415   0.8498   0.0458
  -6.250  -0.0520   0.02399   0.01689  -0.1412   0.8473   0.0456
  -6.000  -0.0258   0.02296   0.01567  -0.1411   0.8452   0.0467
  -5.750   0.0016   0.02216   0.01470  -0.1411   0.8433   0.0480
  -5.500   0.0291   0.02130   0.01372  -0.1410   0.8417   0.0484
  -5.250   0.0513   0.02056   0.01297  -0.1405   0.8385   0.0491
  -5.000   0.0740   0.01995   0.01237  -0.1400   0.8349   0.0508
  -4.750   0.0997   0.01954   0.01192  -0.1399   0.8320   0.0535
  -4.500   0.1274   0.01921   0.01148  -0.1399   0.8296   0.0554
  -4.250   0.1568   0.01888   0.01101  -0.1402   0.8275   0.0575
  -4.000   0.1872   0.01856   0.01057  -0.1405   0.8255   0.0607
  -3.750   0.2084   0.01863   0.01069  -0.1397   0.8205   0.0683
  -3.500   0.2345   0.01831   0.01057  -0.1396   0.8165   0.1324
  -3.250   0.2664   0.01908   0.01106  -0.1397   0.8132   0.1742
  -3.000   0.2981   0.01907   0.01070  -0.1402   0.8105   0.1891
  -2.750   0.3216   0.01841   0.01022  -0.1399   0.8060   0.2007
  -2.500   0.3454   0.01801   0.00997  -0.1395   0.8008   0.2097
  -2.250   0.3742   0.01778   0.00988  -0.1397   0.7972   0.2230
  -2.000   0.4056   0.01772   0.00974  -0.1402   0.7946   0.2350
  -1.750   0.4317   0.01785   0.00980  -0.1400   0.7906   0.2411
  -1.500   0.4555   0.01795   0.00991  -0.1395   0.7854   0.2459
  -1.250   0.4838   0.01790   0.00984  -0.1397   0.7821   0.2535
  -1.000   0.5137   0.01774   0.00971  -0.1401   0.7797   0.2628
  -0.750   0.5449   0.01761   0.00955  -0.1407   0.7776   0.2720
  -0.500   0.5646   0.01798   0.01000  -0.1398   0.7720   0.2775
  -0.250   0.5920   0.01796   0.00998  -0.1398   0.7681   0.2793
   0.000   0.6226   0.01778   0.00977  -0.1402   0.7652   0.2806
   0.250   0.6551   0.01756   0.00950  -0.1410   0.7629   0.2820
   0.500   0.6760   0.01789   0.00988  -0.1401   0.7569   0.2834
   0.750   0.7042   0.01785   0.00985  -0.1402   0.7530   0.2851
   1.000   0.7356   0.01766   0.00967  -0.1408   0.7502   0.2875
   1.250   0.7674   0.01749   0.00950  -0.1414   0.7473   0.2909
   1.500   0.7892   0.01772   0.00979  -0.1405   0.7403   0.2946
   1.750   0.8220   0.01738   0.00944  -0.1412   0.7358   0.3008
   2.000   0.8520   0.01722   0.00932  -0.1414   0.7305   0.3116
   2.250   0.8778   0.01722   0.00942  -0.1411   0.7236   0.3349
   2.500   0.9101   0.01688   0.00926  -0.1419   0.7191   0.4090
   2.750   0.9288   0.01641   0.00966  -0.1403   0.7121   0.6939
   3.000   0.9588   0.01592   0.00963  -0.1400   0.7064   1.0000
   3.250   0.9864   0.01606   0.00973  -0.1400   0.7006   1.0000
   3.500   1.0104   0.01620   0.00990  -0.1393   0.6929   1.0000
   3.750   1.0385   0.01620   0.00986  -0.1393   0.6865   1.0000
   4.000   1.0610   0.01620   0.00990  -0.1382   0.6774   1.0000
   4.250   1.0839   0.01614   0.00987  -0.1373   0.6685   1.0000
   4.500   1.1106   0.01589   0.00964  -0.1369   0.6606   1.0000
   4.750   1.1304   0.01585   0.00969  -0.1354   0.6502   1.0000
   5.000   1.1547   0.01564   0.00951  -0.1347   0.6415   1.0000
   5.250   1.1800   0.01535   0.00924  -0.1340   0.6319   1.0000
   5.500   1.2032   0.01520   0.00910  -0.1330   0.6200   1.0000
   5.750   1.2276   0.01508   0.00896  -0.1323   0.6080   1.0000
   6.000   1.2514   0.01505   0.00890  -0.1315   0.5943   1.0000
   6.250   1.2724   0.01517   0.00900  -0.1302   0.5780   1.0000
   6.500   1.2911   0.01538   0.00919  -0.1285   0.5592   1.0000
   6.750   1.3092   0.01564   0.00937  -0.1268   0.5395   1.0000
   7.000   1.3257   0.01600   0.00961  -0.1247   0.5191   1.0000
   7.250   1.3371   0.01650   0.01003  -0.1219   0.4969   1.0000
   7.500   1.3455   0.01713   0.01052  -0.1185   0.4744   1.0000
   7.750   1.3529   0.01788   0.01115  -0.1152   0.4521   1.0000
   8.000   1.3600   0.01872   0.01189  -0.1120   0.4310   1.0000
   8.250   1.3672   0.01962   0.01270  -0.1090   0.4114   1.0000
   8.500   1.3738   0.02058   0.01359  -0.1060   0.3919   1.0000
   8.750   1.3803   0.02157   0.01456  -0.1032   0.3727   1.0000
   9.000   1.3872   0.02262   0.01557  -0.1006   0.3550   1.0000
   9.250   1.3939   0.02374   0.01664  -0.0981   0.3395   1.0000
   9.750   1.4093   0.02609   0.01892  -0.0937   0.3129   1.0000
  10.000   1.4179   0.02727   0.02013  -0.0918   0.2999   1.0000
  10.250   1.4257   0.02854   0.02139  -0.0898   0.2878   1.0000
  10.500   1.4314   0.02998   0.02278  -0.0878   0.2756   1.0000
  10.750   1.4374   0.03144   0.02418  -0.0858   0.2649   1.0000
  11.000   1.4450   0.03284   0.02565  -0.0842   0.2522   1.0000
  11.250   1.4520   0.03433   0.02721  -0.0826   0.2374   1.0000
  11.500   1.4549   0.03619   0.02903  -0.0809   0.2173   1.0000
  11.750   1.4578   0.03816   0.03098  -0.0792   0.1954   1.0000
  12.000   1.4533   0.04085   0.03347  -0.0772   0.1621   1.0000
  12.250   1.4441   0.04401   0.03638  -0.0749   0.1248   1.0000
  12.500   1.4193   0.04867   0.04056  -0.0718   0.0639   1.0000
  12.750   1.4075   0.05234   0.04409  -0.0696   0.0412   1.0000
  13.000   1.4041   0.05531   0.04708  -0.0681   0.0344   1.0000
  13.250   1.4028   0.05817   0.05002  -0.0669   0.0314   1.0000
  13.500   1.3993   0.06138   0.05334  -0.0658   0.0293   1.0000
  13.750   1.3959   0.06469   0.05680  -0.0648   0.0281   1.0000
  14.000   1.3929   0.06805   0.06032  -0.0641   0.0274   1.0000
  14.250   1.3881   0.07172   0.06416  -0.0636   0.0267   1.0000
  14.500   1.3819   0.07571   0.06832  -0.0632   0.0261   1.0000
  14.750   1.3746   0.07994   0.07269  -0.0631   0.0256   1.0000
  15.000   1.3661   0.08441   0.07731  -0.0631   0.0251   1.0000
  15.250   1.3572   0.08904   0.08207  -0.0634   0.0246   1.0000
  15.500   1.3481   0.09377   0.08690  -0.0638   0.0241   1.0000
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