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BOEING 103 AIRFOIL (boe103-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: BOEING 103 AIRFOIL (boe103-il)
Reynolds number: 200,000
Max Cl/Cd: 72.01 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-boe103-il-200000.txt
Download as CSV file: xf-boe103-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING 103 AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3887   0.08786   0.08449  -0.0401   1.0000   0.0766
  -8.500  -0.4271   0.08558   0.08234  -0.0387   1.0000   0.0777
  -8.250  -0.4612   0.08403   0.08090  -0.0354   1.0000   0.0777
  -8.000  -0.5030   0.07335   0.06998  -0.0487   0.9944   0.0795
  -7.750  -0.4752   0.07128   0.06806  -0.0470   0.9929   0.0808
  -7.500  -0.4499   0.06934   0.06614  -0.0475   0.9891   0.0828
  -7.250  -0.4451   0.05952   0.05569  -0.0614   0.9774   0.0924
  -7.000  -0.4158   0.05677   0.05313  -0.0621   0.9746   0.0941
  -6.500  -0.3921   0.03275   0.02661  -0.0690   0.9597   0.0576
  -6.250  -0.3641   0.02966   0.02318  -0.0700   0.9545   0.0574
  -6.000  -0.3343   0.02696   0.02014  -0.0710   0.9490   0.0570
  -5.750  -0.2975   0.02480   0.01765  -0.0730   0.9458   0.0569
  -5.500  -0.2567   0.02346   0.01598  -0.0755   0.9436   0.0577
  -5.250  -0.2314   0.02166   0.01406  -0.0752   0.9356   0.0588
  -5.000  -0.1924   0.02033   0.01266  -0.0773   0.9323   0.0598
  -4.750  -0.1505   0.01922   0.01150  -0.0800   0.9302   0.0612
  -4.500  -0.1187   0.01842   0.01067  -0.0806   0.9238   0.0627
  -4.250  -0.0831   0.01768   0.00989  -0.0820   0.9186   0.0653
  -4.000  -0.0439   0.01695   0.00909  -0.0839   0.9153   0.0677
  -3.750  -0.0148   0.01610   0.00833  -0.0841   0.9082   0.0707
  -3.500   0.0182   0.01550   0.00774  -0.0848   0.9020   0.0750
  -3.250   0.0547   0.01482   0.00707  -0.0863   0.8979   0.0826
  -3.000   0.0794   0.01437   0.00673  -0.0854   0.8879   0.0999
  -2.750   0.1119   0.01354   0.00626  -0.0862   0.8824   0.1837
  -2.500   0.1363   0.01314   0.00606  -0.0855   0.8722   0.2356
  -2.250   0.1654   0.01236   0.00575  -0.0858   0.8659   0.3531
  -2.000   0.1842   0.01166   0.00574  -0.0839   0.8546   0.5346
  -1.750   0.2075   0.01114   0.00566  -0.0822   0.8455   0.6694
  -1.500   0.2310   0.01078   0.00557  -0.0803   0.8348   0.7625
  -1.250   0.2549   0.01062   0.00555  -0.0783   0.8228   0.8363
  -1.000   0.2882   0.01057   0.00552  -0.0780   0.8135   0.9041
  -0.750   0.3324   0.01063   0.00550  -0.0803   0.8038   0.9492
  -0.500   0.3853   0.01066   0.00542  -0.0849   0.7946   0.9735
  -0.250   0.4446   0.01061   0.00521  -0.0911   0.7855   0.9909
   0.000   0.4898   0.01056   0.00506  -0.0948   0.7740   1.0000
   0.250   0.5126   0.01055   0.00495  -0.0939   0.7632   1.0000
   0.500   0.5362   0.01056   0.00483  -0.0931   0.7526   1.0000
   0.750   0.5582   0.01060   0.00481  -0.0919   0.7405   1.0000
   1.000   0.5813   0.01065   0.00478  -0.0910   0.7293   1.0000
   1.250   0.6058   0.01070   0.00471  -0.0902   0.7188   1.0000
   1.500   0.6281   0.01078   0.00474  -0.0890   0.7065   1.0000
   1.750   0.6510   0.01087   0.00475  -0.0879   0.6941   1.0000
   2.000   0.6743   0.01095   0.00476  -0.0868   0.6814   1.0000
   2.250   0.6975   0.01105   0.00476  -0.0857   0.6677   1.0000
   2.500   0.7203   0.01115   0.00477  -0.0845   0.6528   1.0000
   2.750   0.7427   0.01126   0.00480  -0.0832   0.6374   1.0000
   3.000   0.7651   0.01140   0.00485  -0.0820   0.6217   1.0000
   3.250   0.7874   0.01154   0.00492  -0.0807   0.6060   1.0000
   3.500   0.8089   0.01169   0.00501  -0.0793   0.5883   1.0000
   3.750   0.8301   0.01184   0.00511  -0.0778   0.5685   1.0000
   4.000   0.8512   0.01202   0.00520  -0.0764   0.5474   1.0000
   4.250   0.8723   0.01223   0.00530  -0.0749   0.5267   1.0000
   4.500   0.8935   0.01244   0.00546  -0.0736   0.5054   1.0000
   4.750   0.9145   0.01270   0.00563  -0.0722   0.4834   1.0000
   5.000   0.9352   0.01300   0.00582  -0.0708   0.4619   1.0000
   5.250   0.9560   0.01330   0.00607  -0.0694   0.4400   1.0000
   5.500   0.9764   0.01365   0.00632  -0.0680   0.4190   1.0000
   5.750   0.9966   0.01404   0.00660  -0.0667   0.3996   1.0000
   6.000   1.0168   0.01445   0.00693  -0.0653   0.3814   1.0000
   6.250   1.0371   0.01487   0.00728  -0.0640   0.3641   1.0000
   6.500   1.0570   0.01530   0.00765  -0.0627   0.3471   1.0000
   6.750   1.0765   0.01575   0.00805  -0.0613   0.3299   1.0000
   7.000   1.0955   0.01622   0.00848  -0.0599   0.3122   1.0000
   7.250   1.1136   0.01670   0.00891  -0.0583   0.2933   1.0000
   7.500   1.1302   0.01724   0.00938  -0.0565   0.2727   1.0000
   7.750   1.1461   0.01780   0.00987  -0.0547   0.2478   1.0000
   8.000   1.1589   0.01852   0.01047  -0.0524   0.2211   1.0000
   8.250   1.1692   0.01932   0.01112  -0.0497   0.1984   1.0000
   8.500   1.1797   0.02020   0.01188  -0.0471   0.1826   1.0000
   8.750   1.1924   0.02102   0.01265  -0.0450   0.1713   1.0000
   9.000   1.2047   0.02191   0.01350  -0.0429   0.1635   1.0000
   9.250   1.2189   0.02271   0.01430  -0.0411   0.1570   1.0000
   9.500   1.2307   0.02373   0.01524  -0.0391   0.1520   1.0000
   9.750   1.2471   0.02447   0.01607  -0.0377   0.1478   1.0000
  10.000   1.2620   0.02528   0.01693  -0.0362   0.1436   1.0000
  10.250   1.2750   0.02631   0.01789  -0.0346   0.1394   1.0000
  10.500   1.2900   0.02717   0.01883  -0.0333   0.1356   1.0000
  10.750   1.3045   0.02801   0.01976  -0.0319   0.1318   1.0000
  11.000   1.3173   0.02895   0.02073  -0.0305   0.1279   1.0000
  11.250   1.3309   0.03012   0.02183  -0.0292   0.1241   1.0000
  11.500   1.3437   0.03103   0.02290  -0.0279   0.1211   1.0000
  11.750   1.3562   0.03203   0.02400  -0.0266   0.1179   1.0000
  12.000   1.3676   0.03313   0.02514  -0.0254   0.1148   1.0000
  12.250   1.3812   0.03439   0.02634  -0.0242   0.1115   1.0000
  12.500   1.3909   0.03557   0.02770  -0.0230   0.1090   1.0000
  12.750   1.3997   0.03683   0.02910  -0.0218   0.1059   1.0000
  13.000   1.4083   0.03816   0.03051  -0.0207   0.1030   1.0000
  13.250   1.4171   0.03958   0.03194  -0.0196   0.1003   1.0000
  13.500   1.4278   0.04104   0.03343  -0.0186   0.0977   1.0000
  13.750   1.4334   0.04266   0.03526  -0.0176   0.0955   1.0000
  14.000   1.4391   0.04435   0.03710  -0.0168   0.0930   1.0000
  14.250   1.4444   0.04610   0.03894  -0.0160   0.0906   1.0000
  14.500   1.4492   0.04795   0.04084  -0.0154   0.0883   1.0000
  14.750   1.4567   0.04970   0.04259  -0.0145   0.0859   1.0000
  15.000   1.4581   0.05198   0.04509  -0.0142   0.0842   1.0000
  15.250   1.4601   0.05428   0.04758  -0.0139   0.0823   1.0000
  15.500   1.4620   0.05665   0.05010  -0.0137   0.0803   1.0000
  15.750   1.4629   0.05921   0.05276  -0.0139   0.0781   1.0000
  16.000   1.4639   0.06182   0.05543  -0.0140   0.0763   1.0000
  16.250   1.4649   0.06448   0.05814  -0.0141   0.0744   1.0000
  16.500   1.4626   0.06781   0.06172  -0.0148   0.0726   1.0000
  16.750   1.4606   0.07119   0.06529  -0.0157   0.0705   1.0000
  17.000   1.4585   0.07467   0.06892  -0.0167   0.0684   1.0000
  17.250   1.4555   0.07836   0.07273  -0.0179   0.0665   1.0000
  17.500   1.4515   0.08220   0.07662  -0.0191   0.0648   1.0000
  17.750   1.4470   0.08631   0.08095  -0.0205   0.0629   1.0000
  18.000   1.4419   0.09060   0.08545  -0.0221   0.0606   1.0000
  18.250   1.4351   0.09530   0.09030  -0.0241   0.0581   1.0000
  18.500   1.4263   0.10038   0.09548  -0.0264   0.0561   1.0000
  18.750   1.4177   0.10544   0.10071  -0.0285   0.0537   1.0000
  19.000   1.4070   0.11099   0.10642  -0.0311   0.0511   1.0000
  19.250   1.3940   0.11703   0.11256  -0.0340   0.0489   1.0000
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