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BOEING AIRFOIL J (no closed TE) (bacj-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: BOEING AIRFOIL J (no closed TE) (bacj-il)
Reynolds number: 200,000
Max Cl/Cd: 31.09 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-bacj-il-200000.txt
Download as CSV file: xf-bacj-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING AIRFOIL J                                
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.6199   0.09158   0.08779  -0.0405   1.0000   0.0822
 -10.000  -0.6234   0.08823   0.08445  -0.0402   1.0000   0.0831
  -9.750  -0.6287   0.08494   0.08119  -0.0402   1.0000   0.0845
  -9.500  -0.8861   0.05284   0.04789  -0.0400   1.0000   0.0474
  -9.250  -0.8799   0.05078   0.04582  -0.0382   1.0000   0.0481
  -9.000  -0.8885   0.04631   0.04089  -0.0348   1.0000   0.0451
  -8.750  -0.8892   0.04371   0.03789  -0.0320   1.0000   0.0457
  -8.500  -0.8855   0.04000   0.03390  -0.0299   1.0000   0.0452
  -8.250  -0.8785   0.03670   0.03026  -0.0278   1.0000   0.0449
  -8.000  -0.8674   0.03397   0.02718  -0.0260   1.0000   0.0447
  -7.750  -0.8535   0.03161   0.02447  -0.0243   1.0000   0.0449
  -7.500  -0.8372   0.02961   0.02213  -0.0228   1.0000   0.0453
  -7.250  -0.8191   0.02809   0.02034  -0.0214   1.0000   0.0457
  -7.000  -0.8003   0.02650   0.01848  -0.0200   1.0000   0.0466
  -6.750  -0.7808   0.02460   0.01652  -0.0190   1.0000   0.0479
  -6.500  -0.7609   0.02368   0.01558  -0.0179   1.0000   0.0496
  -6.250  -0.7406   0.02288   0.01471  -0.0168   1.0000   0.0518
  -6.000  -0.7198   0.02203   0.01374  -0.0156   1.0000   0.0545
  -5.750  -0.6989   0.02134   0.01293  -0.0144   1.0000   0.0558
  -5.500  -0.6800   0.01997   0.01163  -0.0130   1.0000   0.0585
  -5.250  -0.6599   0.01937   0.01104  -0.0119   1.0000   0.0623
  -5.000  -0.6391   0.01889   0.01048  -0.0107   1.0000   0.0673
  -4.750  -0.6203   0.01799   0.00968  -0.0094   1.0000   0.0732
  -4.500  -0.6003   0.01741   0.00909  -0.0081   1.0000   0.0819
  -4.250  -0.5800   0.01697   0.00866  -0.0070   1.0000   0.0938
  -4.000  -0.5612   0.01626   0.00814  -0.0057   1.0000   0.1146
  -3.750  -0.5421   0.01571   0.00778  -0.0044   1.0000   0.1493
  -3.500  -0.5229   0.01524   0.00751  -0.0031   1.0000   0.1949
  -3.250  -0.5048   0.01472   0.00726  -0.0018   1.0000   0.2450
  -3.000  -0.4885   0.01407   0.00702  -0.0001   1.0000   0.3262
  -2.750  -0.4798   0.01315   0.00715   0.0034   1.0000   0.5298
  -2.500  -0.4638   0.01325   0.00758   0.0061   1.0000   0.6292
  -2.250  -0.4452   0.01350   0.00787   0.0082   1.0000   0.6701
  -2.000  -0.4260   0.01377   0.00811   0.0101   1.0000   0.6962
  -1.750  -0.3979   0.01433   0.00868   0.0103   0.9976   0.7180
  -1.500  -0.3653   0.01506   0.00943   0.0097   0.9931   0.7397
  -1.250  -0.3332   0.01565   0.01001   0.0091   0.9884   0.7559
  -1.000  -0.3010   0.01611   0.01044   0.0083   0.9844   0.7670
  -0.750  -0.2712   0.01645   0.01074   0.0078   0.9798   0.7781
  -0.500  -0.2426   0.01672   0.01104   0.0078   0.9750   0.7879
  -0.250  -0.2116   0.01705   0.01135   0.0072   0.9703   0.7988
   0.000  -0.1834   0.01726   0.01157   0.0071   0.9658   0.8078
   0.250  -0.1562   0.01743   0.01175   0.0073   0.9612   0.8164
   0.500  -0.1271   0.01770   0.01205   0.0072   0.9566   0.8295
   0.750  -0.1018   0.01778   0.01217   0.0077   0.9504   0.8398
   1.000  -0.0658   0.01798   0.01238   0.0060   0.9462   0.8463
   1.250  -0.0361   0.01793   0.01237   0.0056   0.9382   0.8524
   1.500   0.0019   0.01791   0.01237   0.0036   0.9293   0.8575
   1.750   0.0540   0.01787   0.01238  -0.0010   0.9233   0.8606
   2.000   0.0897   0.01756   0.01214  -0.0024   0.9128   0.8641
   2.250   0.1294   0.01722   0.01186  -0.0043   0.9024   0.8678
   2.500   0.2212   0.01537   0.01013  -0.0145   0.8836   0.8678
   2.750   0.2719   0.01401   0.00886  -0.0173   0.8651   0.8704
   3.000   0.3123   0.01269   0.00763  -0.0179   0.8418   0.8737
   3.250   0.3461   0.01164   0.00667  -0.0175   0.8013   0.8767
   3.500   0.3866   0.01353   0.00575  -0.0191   0.2086   0.8782
   3.750   0.3940   0.01475   0.00628  -0.0154   0.0907   0.8844
   4.000   0.4114   0.01531   0.00679  -0.0134   0.0781   0.8897
   4.250   0.4321   0.01570   0.00719  -0.0119   0.0713   0.8952
   4.500   0.4520   0.01649   0.00791  -0.0106   0.0653   0.9007
   4.750   0.4787   0.01709   0.00856  -0.0104   0.0619   0.9056
   5.000   0.5068   0.01778   0.00925  -0.0107   0.0582   0.9111
   5.250   0.5433   0.01935   0.01072  -0.0128   0.0540   0.9157
   5.500   0.5784   0.02019   0.01169  -0.0142   0.0517   0.9211
   5.750   0.6158   0.02145   0.01306  -0.0162   0.0509   0.9261
   6.000   0.6516   0.02264   0.01436  -0.0178   0.0484   0.9318
   6.250   0.6868   0.02409   0.01581  -0.0198   0.0459   0.9381
   6.500   0.7245   0.02623   0.01815  -0.0220   0.0454   0.9445
   6.750   0.7627   0.02903   0.02126  -0.0243   0.0452   0.9507
   7.000   0.7936   0.03349   0.02675  -0.0239   0.0512   0.9612
   7.250   0.7240   0.02329   0.01855  -0.0049   0.0990   0.9474
   7.500   0.7343   0.03082   0.02596  -0.0063   0.0950   0.9518
   7.750   0.7584   0.03129   0.02702  -0.0057   0.0844   1.0000
   8.000   0.7699   0.03426   0.03001  -0.0047   0.0827   1.0000
   8.250   0.8370   0.05558   0.05119  -0.0112   0.0746   1.0000
   8.500   0.8413   0.05818   0.05394  -0.0092   0.0713   1.0000
   8.750   0.8498   0.06076   0.05656  -0.0079   0.0695   1.0000
   9.000   0.8585   0.06366   0.05947  -0.0069   0.0685   1.0000
   9.250   0.8706   0.07354   0.06909  -0.0091   0.0662   1.0000
   9.500   0.8586   0.07573   0.07154  -0.0057   0.0660   1.0000
   9.750   0.8412   0.07772   0.07376  -0.0022   0.0657   1.0000
  10.000   0.7960   0.08004   0.07636   0.0022   0.0649   1.0000
  10.250   0.7589   0.08555   0.08204   0.0008   0.0639   1.0000
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