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BOEING 103 AIRFOIL (boe103-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: BOEING 103 AIRFOIL (boe103-il)
Reynolds number: 200,000
Max Cl/Cd: 66.6 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-boe103-il-200000-n5.txt
Download as CSV file: xf-boe103-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5578   0.05790   0.05422  -0.0646   1.0000   0.0262
  -9.750  -0.5955   0.05033   0.04631  -0.0680   0.9944   0.0262
  -9.500  -0.6053   0.04111   0.03616  -0.0740   0.9838   0.0267
  -9.250  -0.5875   0.03834   0.03324  -0.0753   0.9773   0.0272
  -9.000  -0.5608   0.03661   0.03140  -0.0772   0.9736   0.0280
  -8.750  -0.5398   0.03488   0.02951  -0.0778   0.9667   0.0288
  -8.250  -0.4953   0.03002   0.02389  -0.0794   0.9552   0.0306
  -8.000  -0.4691   0.02789   0.02132  -0.0803   0.9504   0.0314
  -7.750  -0.4404   0.02647   0.01944  -0.0812   0.9463   0.0323
  -7.500  -0.4167   0.02468   0.01755  -0.0812   0.9395   0.0332
  -7.250  -0.3864   0.02341   0.01617  -0.0822   0.9354   0.0339
  -7.000  -0.3568   0.02229   0.01490  -0.0829   0.9307   0.0346
  -6.750  -0.3296   0.02133   0.01381  -0.0830   0.9240   0.0354
  -6.500  -0.2979   0.02042   0.01276  -0.0839   0.9196   0.0366
  -6.250  -0.2682   0.01960   0.01180  -0.0844   0.9139   0.0376
  -6.000  -0.2396   0.01881   0.01089  -0.0845   0.9071   0.0382
  -5.750  -0.2072   0.01805   0.01002  -0.0854   0.9024   0.0388
  -5.500  -0.1803   0.01736   0.00927  -0.0852   0.8947   0.0393
  -5.250  -0.1514   0.01657   0.00847  -0.0855   0.8881   0.0403
  -5.000  -0.1231   0.01600   0.00789  -0.0857   0.8811   0.0416
  -4.750  -0.0955   0.01553   0.00739  -0.0856   0.8731   0.0429
  -4.500  -0.0667   0.01507   0.00687  -0.0857   0.8660   0.0440
  -4.250  -0.0401   0.01469   0.00643  -0.0854   0.8573   0.0451
  -4.000  -0.0115   0.01434   0.00600  -0.0854   0.8498   0.0462
  -3.750   0.0149   0.01401   0.00563  -0.0850   0.8407   0.0477
  -3.500   0.0428   0.01369   0.00527  -0.0849   0.8328   0.0500
  -3.250   0.0695   0.01343   0.00498  -0.0845   0.8236   0.0537
  -3.000   0.0966   0.01314   0.00472  -0.0843   0.8151   0.0618
  -2.750   0.1231   0.01281   0.00450  -0.0839   0.8060   0.0876
  -2.500   0.1495   0.01254   0.00435  -0.0836   0.7969   0.1248
  -2.250   0.1767   0.01233   0.00419  -0.0834   0.7880   0.1563
  -2.000   0.2029   0.01214   0.00406  -0.0830   0.7773   0.1853
  -1.750   0.2293   0.01193   0.00390  -0.0826   0.7660   0.2181
  -1.500   0.2541   0.01151   0.00375  -0.0821   0.7535   0.3004
  -1.250   0.2763   0.01095   0.00369  -0.0810   0.7394   0.4532
  -1.000   0.2995   0.01063   0.00366  -0.0799   0.7261   0.5514
  -0.750   0.3224   0.01035   0.00368  -0.0786   0.7145   0.6501
  -0.500   0.3454   0.01013   0.00371  -0.0770   0.7044   0.7413
  -0.250   0.3699   0.01000   0.00381  -0.0755   0.6937   0.8314
   0.000   0.4040   0.01002   0.00388  -0.0761   0.6831   0.9012
   0.250   0.4419   0.01010   0.00387  -0.0778   0.6725   0.9394
   0.500   0.4818   0.01019   0.00388  -0.0801   0.6608   0.9647
   0.750   0.5231   0.01028   0.00387  -0.0829   0.6495   0.9844
   1.000   0.5721   0.01036   0.00384  -0.0874   0.6375   0.9997
   1.250   0.5953   0.01046   0.00385  -0.0865   0.6262   1.0000
   1.500   0.6182   0.01056   0.00388  -0.0855   0.6150   1.0000
   1.750   0.6410   0.01069   0.00392  -0.0844   0.6031   1.0000
   2.000   0.6632   0.01083   0.00396  -0.0833   0.5886   1.0000
   2.250   0.6852   0.01098   0.00402  -0.0820   0.5724   1.0000
   2.500   0.7069   0.01114   0.00409  -0.0807   0.5551   1.0000
   2.750   0.7286   0.01131   0.00417  -0.0795   0.5368   1.0000
   3.000   0.7505   0.01150   0.00427  -0.0782   0.5187   1.0000
   3.250   0.7720   0.01171   0.00438  -0.0770   0.4983   1.0000
   3.500   0.7931   0.01195   0.00450  -0.0756   0.4759   1.0000
   3.750   0.8139   0.01222   0.00465  -0.0742   0.4505   1.0000
   4.000   0.8341   0.01254   0.00483  -0.0728   0.4239   1.0000
   4.250   0.8538   0.01290   0.00503  -0.0713   0.3973   1.0000
   4.500   0.8744   0.01325   0.00527  -0.0700   0.3754   1.0000
   4.750   0.8956   0.01360   0.00553  -0.0688   0.3583   1.0000
   5.000   0.9168   0.01395   0.00580  -0.0677   0.3429   1.0000
   5.250   0.9379   0.01432   0.00610  -0.0665   0.3280   1.0000
   5.500   0.9589   0.01470   0.00642  -0.0654   0.3130   1.0000
   5.750   0.9796   0.01509   0.00675  -0.0642   0.2978   1.0000
   6.000   1.0003   0.01549   0.00708  -0.0631   0.2820   1.0000
   6.250   1.0207   0.01590   0.00744  -0.0619   0.2655   1.0000
   6.500   1.0408   0.01632   0.00781  -0.0607   0.2482   1.0000
   6.750   1.0602   0.01678   0.00820  -0.0594   0.2300   1.0000
   7.000   1.0787   0.01729   0.00863  -0.0580   0.2109   1.0000
   7.250   1.0961   0.01785   0.00911  -0.0565   0.1918   1.0000
   7.500   1.1126   0.01844   0.00962  -0.0548   0.1737   1.0000
   7.750   1.1278   0.01905   0.01016  -0.0530   0.1587   1.0000
   8.000   1.1429   0.01969   0.01075  -0.0511   0.1467   1.0000
   8.250   1.1582   0.02034   0.01137  -0.0493   0.1371   1.0000
   8.500   1.1739   0.02096   0.01201  -0.0477   0.1304   1.0000
   8.750   1.1892   0.02162   0.01268  -0.0460   0.1250   1.0000
   9.000   1.2035   0.02234   0.01341  -0.0443   0.1209   1.0000
   9.250   1.2191   0.02300   0.01414  -0.0428   0.1178   1.0000
   9.500   1.2339   0.02372   0.01491  -0.0413   0.1148   1.0000
   9.750   1.2474   0.02454   0.01576  -0.0397   0.1118   1.0000
  10.000   1.2591   0.02548   0.01672  -0.0380   0.1088   1.0000
  10.250   1.2732   0.02630   0.01762  -0.0366   0.1058   1.0000
  10.500   1.2869   0.02716   0.01856  -0.0353   0.1026   1.0000
  10.750   1.2988   0.02816   0.01960  -0.0339   0.0992   1.0000
  11.000   1.3081   0.02937   0.02082  -0.0323   0.0960   1.0000
  11.250   1.3208   0.03038   0.02191  -0.0312   0.0932   1.0000
  11.500   1.3335   0.03140   0.02304  -0.0301   0.0902   1.0000
  11.750   1.3443   0.03259   0.02429  -0.0289   0.0873   1.0000
  12.000   1.3533   0.03395   0.02570  -0.0278   0.0849   1.0000
  12.250   1.3599   0.03554   0.02734  -0.0266   0.0827   1.0000
  12.500   1.3716   0.03675   0.02866  -0.0257   0.0806   1.0000
  12.750   1.3825   0.03806   0.03011  -0.0249   0.0782   1.0000
  13.000   1.3917   0.03953   0.03169  -0.0241   0.0757   1.0000
  13.250   1.3989   0.04122   0.03344  -0.0234   0.0731   1.0000
  13.500   1.4046   0.04310   0.03538  -0.0227   0.0703   1.0000
  13.750   1.4149   0.04457   0.03700  -0.0222   0.0670   1.0000
  14.000   1.4220   0.04638   0.03891  -0.0217   0.0634   1.0000
  14.250   1.4277   0.04837   0.04100  -0.0213   0.0602   1.0000
  14.500   1.4339   0.05037   0.04310  -0.0210   0.0555   1.0000
  14.750   1.4370   0.05276   0.04554  -0.0208   0.0500   1.0000
  15.000   1.4368   0.05560   0.04839  -0.0208   0.0446   1.0000
  15.250   1.4339   0.05881   0.05162  -0.0208   0.0403   1.0000
  15.500   1.4303   0.06222   0.05509  -0.0211   0.0370   1.0000
  15.750   1.4254   0.06590   0.05884  -0.0215   0.0340   1.0000
  16.000   1.4194   0.06980   0.06283  -0.0221   0.0318   1.0000
  16.250   1.4152   0.07357   0.06672  -0.0228   0.0293   1.0000
  16.500   1.4081   0.07785   0.07112  -0.0237   0.0271   1.0000
  16.750   1.4061   0.08149   0.07492  -0.0246   0.0180   1.0000
  17.000   1.3875   0.08766   0.08115  -0.0265   0.0167   1.0000
  17.250   1.3719   0.09360   0.08719  -0.0285   0.0158   1.0000
  17.500   1.3570   0.09963   0.09335  -0.0308   0.0154   1.0000
  17.750   1.3417   0.10589   0.09975  -0.0333   0.0151   1.0000
  18.000   1.3256   0.11242   0.10643  -0.0360   0.0148   1.0000
  18.250   1.3091   0.11921   0.11338  -0.0391   0.0147   1.0000
  18.500   1.2916   0.12635   0.12069  -0.0425   0.0146   1.0000
  18.750   1.2734   0.13380   0.12831  -0.0463   0.0145   1.0000
  19.000   1.2544   0.14163   0.13630  -0.0504   0.0145   1.0000
  19.250   1.2348   0.14983   0.14468  -0.0549   0.0146   1.0000
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