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BOEING 106 AIRFOIL (boe106-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: BOEING 106 AIRFOIL (boe106-il)
Reynolds number: 1,000,000
Max Cl/Cd: 118.84 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-boe106-il-1000000.txt
Download as CSV file: xf-boe106-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING 106 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.000  -0.9109   0.08032   0.07811  -0.0477   1.0000   0.0151
 -15.750  -1.0538   0.04863   0.04591  -0.0716   1.0000   0.0144
 -15.500  -1.0755   0.04074   0.03779  -0.0789   1.0000   0.0145
 -15.250  -1.0843   0.03645   0.03334  -0.0819   1.0000   0.0146
 -15.000  -1.0870   0.03361   0.03036  -0.0828   1.0000   0.0148
 -14.750  -1.0870   0.03148   0.02809  -0.0825   1.0000   0.0150
 -14.500  -1.0842   0.02984   0.02632  -0.0814   1.0000   0.0152
 -14.250  -1.0791   0.02855   0.02492  -0.0797   1.0000   0.0153
 -14.000  -1.0719   0.02755   0.02381  -0.0776   1.0000   0.0155
 -13.750  -1.0733   0.02579   0.02191  -0.0748   1.0000   0.0158
 -13.500  -1.0681   0.02472   0.02078  -0.0720   1.0000   0.0162
 -13.250  -1.0599   0.02411   0.02013  -0.0692   1.0000   0.0164
 -13.000  -1.0542   0.02366   0.01965  -0.0658   1.0000   0.0167
 -12.750  -1.0261   0.02308   0.01902  -0.0666   0.9984   0.0171
 -12.500  -0.9952   0.02249   0.01838  -0.0680   0.9964   0.0176
 -12.250  -0.9638   0.02187   0.01768  -0.0695   0.9945   0.0181
 -12.000  -0.9331   0.02127   0.01698  -0.0707   0.9924   0.0186
 -11.750  -0.9027   0.02071   0.01633  -0.0718   0.9894   0.0189
 -11.500  -0.8763   0.01926   0.01477  -0.0729   0.9862   0.0197
 -11.250  -0.8443   0.01879   0.01429  -0.0743   0.9837   0.0201
 -11.000  -0.8148   0.01840   0.01386  -0.0750   0.9792   0.0207
 -10.750  -0.7865   0.01795   0.01335  -0.0754   0.9735   0.0212
 -10.500  -0.7584   0.01749   0.01281  -0.0758   0.9679   0.0218
 -10.250  -0.7335   0.01716   0.01240  -0.0754   0.9596   0.0223
 -10.000  -0.7087   0.01679   0.01194  -0.0749   0.9517   0.0227
  -9.750  -0.6891   0.01580   0.01086  -0.0737   0.9416   0.0236
  -9.500  -0.6654   0.01547   0.01050  -0.0730   0.9316   0.0241
  -9.250  -0.6412   0.01517   0.01014  -0.0724   0.9224   0.0247
  -9.000  -0.6164   0.01485   0.00975  -0.0718   0.9130   0.0253
  -8.750  -0.5914   0.01453   0.00935  -0.0713   0.9051   0.0260
  -8.500  -0.5655   0.01430   0.00905  -0.0709   0.8966   0.0266
  -8.250  -0.5391   0.01416   0.00882  -0.0706   0.8890   0.0270
  -8.000  -0.5173   0.01312   0.00770  -0.0697   0.8804   0.0281
  -7.750  -0.4918   0.01278   0.00732  -0.0694   0.8729   0.0287
  -7.500  -0.4655   0.01252   0.00703  -0.0691   0.8649   0.0295
  -7.250  -0.4392   0.01228   0.00672  -0.0687   0.8576   0.0303
  -7.000  -0.4127   0.01201   0.00641  -0.0685   0.8498   0.0311
  -6.500  -0.3592   0.01158   0.00585  -0.0680   0.8351   0.0321
  -6.250  -0.3355   0.01088   0.00508  -0.0673   0.8276   0.0335
  -6.000  -0.3089   0.01060   0.00478  -0.0670   0.8205   0.0344
  -5.750  -0.2823   0.01037   0.00451  -0.0667   0.8131   0.0353
  -5.500  -0.2554   0.01015   0.00425  -0.0665   0.8061   0.0362
  -5.250  -0.2284   0.00996   0.00401  -0.0663   0.7986   0.0371
  -5.000  -0.2011   0.00982   0.00382  -0.0661   0.7918   0.0379
  -4.750  -0.1752   0.00944   0.00340  -0.0657   0.7842   0.0394
  -4.500  -0.1487   0.00922   0.00313  -0.0654   0.7770   0.0409
  -4.250  -0.1213   0.00904   0.00294  -0.0652   0.7694   0.0424
  -3.750  -0.0669   0.00876   0.00258  -0.0648   0.7524   0.0457
  -3.500  -0.0404   0.00856   0.00235  -0.0644   0.7429   0.0493
  -3.250  -0.0132   0.00843   0.00219  -0.0642   0.7332   0.0525
  -3.000   0.0138   0.00826   0.00201  -0.0640   0.7250   0.0591
  -2.750   0.0404   0.00806   0.00187  -0.0637   0.7164   0.0758
  -2.500   0.0669   0.00784   0.00178  -0.0634   0.7082   0.1121
  -2.250   0.0939   0.00773   0.00170  -0.0632   0.6990   0.1327
  -2.000   0.1212   0.00761   0.00162  -0.0631   0.6899   0.1507
  -1.750   0.1479   0.00750   0.00154  -0.0628   0.6807   0.1740
  -1.500   0.1738   0.00723   0.00147  -0.0625   0.6712   0.2368
  -1.250   0.1992   0.00697   0.00142  -0.0621   0.6615   0.3137
  -0.750   0.2490   0.00641   0.00134  -0.0611   0.6397   0.4875
  -0.500   0.2717   0.00603   0.00133  -0.0601   0.6292   0.6146
  -0.250   0.2956   0.00585   0.00135  -0.0593   0.6182   0.6975
   0.000   0.3202   0.00572   0.00137  -0.0585   0.6073   0.7581
   0.250   0.3441   0.00560   0.00141  -0.0574   0.5966   0.8182
   0.500   0.3686   0.00556   0.00147  -0.0565   0.5853   0.8694
   0.750   0.3954   0.00558   0.00154  -0.0560   0.5742   0.9029
   1.000   0.4240   0.00565   0.00161  -0.0560   0.5638   0.9294
   1.250   0.4540   0.00577   0.00169  -0.0563   0.5536   0.9465
   1.500   0.4856   0.00586   0.00175  -0.0570   0.5440   0.9588
   1.750   0.5168   0.00599   0.00184  -0.0577   0.5349   0.9703
   2.000   0.5532   0.00612   0.00192  -0.0595   0.5252   0.9767
   2.250   0.5893   0.00626   0.00201  -0.0613   0.5151   0.9832
   2.500   0.6325   0.00641   0.00209  -0.0647   0.5018   0.9870
   2.750   0.6717   0.00657   0.00217  -0.0672   0.4890   0.9915
   3.000   0.7157   0.00670   0.00225  -0.0708   0.4760   0.9954
   3.250   0.7577   0.00681   0.00230  -0.0740   0.4634   0.9984
   3.500   0.7922   0.00692   0.00236  -0.0756   0.4525   1.0000
   3.750   0.8157   0.00705   0.00244  -0.0748   0.4412   1.0000
   4.000   0.8394   0.00716   0.00252  -0.0741   0.4301   1.0000
   4.250   0.8626   0.00730   0.00261  -0.0732   0.4171   1.0000
   4.500   0.8849   0.00748   0.00273  -0.0722   0.4007   1.0000
   4.750   0.9072   0.00766   0.00285  -0.0712   0.3861   1.0000
   5.000   0.9296   0.00784   0.00297  -0.0702   0.3745   1.0000
   5.250   0.9515   0.00803   0.00312  -0.0691   0.3620   1.0000
   5.500   0.9734   0.00822   0.00326  -0.0680   0.3502   1.0000
   5.750   0.9959   0.00838   0.00341  -0.0670   0.3410   1.0000
   6.000   1.0177   0.00859   0.00357  -0.0659   0.3313   1.0000
   6.250   1.0398   0.00877   0.00373  -0.0648   0.3211   1.0000
   6.500   1.0617   0.00898   0.00391  -0.0637   0.3102   1.0000
   6.750   1.0831   0.00921   0.00410  -0.0626   0.2983   1.0000
   7.000   1.1042   0.00946   0.00431  -0.0614   0.2852   1.0000
   7.250   1.1250   0.00973   0.00452  -0.0602   0.2691   1.0000
   7.500   1.1445   0.01011   0.00479  -0.0588   0.2449   1.0000
   7.750   1.1592   0.01078   0.00522  -0.0566   0.2009   1.0000
   8.000   1.1738   0.01150   0.00574  -0.0545   0.1672   1.0000
   8.250   1.1926   0.01198   0.00614  -0.0531   0.1510   1.0000
   8.500   1.2120   0.01243   0.00653  -0.0519   0.1380   1.0000
   8.750   1.2312   0.01289   0.00693  -0.0506   0.1257   1.0000
   9.000   1.2505   0.01333   0.00731  -0.0494   0.1149   1.0000
   9.250   1.2701   0.01374   0.00770  -0.0482   0.1055   1.0000
   9.500   1.2879   0.01419   0.00811  -0.0467   0.0964   1.0000
   9.750   1.3038   0.01470   0.00857  -0.0450   0.0874   1.0000
  10.000   1.3212   0.01515   0.00901  -0.0435   0.0815   1.0000
  10.250   1.3371   0.01569   0.00953  -0.0419   0.0752   1.0000
  10.500   1.3536   0.01620   0.01004  -0.0404   0.0704   1.0000
  10.750   1.3684   0.01683   0.01066  -0.0388   0.0654   1.0000
  11.000   1.3858   0.01733   0.01119  -0.0376   0.0630   1.0000
  11.250   1.4011   0.01796   0.01183  -0.0362   0.0601   1.0000
  11.500   1.4147   0.01871   0.01258  -0.0346   0.0567   1.0000
  11.750   1.4308   0.01932   0.01325  -0.0335   0.0547   1.0000
  12.000   1.4459   0.02001   0.01397  -0.0323   0.0524   1.0000
  12.250   1.4586   0.02089   0.01485  -0.0309   0.0495   1.0000
  12.500   1.4714   0.02178   0.01577  -0.0296   0.0469   1.0000
  12.750   1.4858   0.02259   0.01662  -0.0286   0.0447   1.0000
  13.000   1.4969   0.02366   0.01770  -0.0273   0.0417   1.0000
  13.250   1.5081   0.02475   0.01882  -0.0262   0.0388   1.0000
  13.500   1.5175   0.02600   0.02008  -0.0250   0.0349   1.0000
  13.750   1.5250   0.02745   0.02153  -0.0238   0.0302   1.0000
  14.000   1.5284   0.02927   0.02334  -0.0224   0.0248   1.0000
  14.250   1.5304   0.03128   0.02536  -0.0211   0.0207   1.0000
  14.500   1.5325   0.03336   0.02746  -0.0200   0.0182   1.0000
  14.750   1.5335   0.03559   0.02974  -0.0190   0.0166   1.0000
  15.000   1.5357   0.03779   0.03200  -0.0182   0.0155   1.0000
  15.250   1.5380   0.04005   0.03433  -0.0176   0.0148   1.0000
  15.500   1.5384   0.04256   0.03691  -0.0170   0.0141   1.0000
  15.750   1.5366   0.04541   0.03983  -0.0166   0.0135   1.0000
  16.000   1.5337   0.04848   0.04299  -0.0164   0.0130   1.0000
  16.250   1.5345   0.05121   0.04581  -0.0163   0.0127   1.0000
  16.500   1.5338   0.05418   0.04886  -0.0163   0.0124   1.0000
  16.750   1.5321   0.05735   0.05213  -0.0165   0.0121   1.0000
  17.000   1.5289   0.06076   0.05562  -0.0168   0.0118   1.0000
  17.250   1.5240   0.06443   0.05938  -0.0172   0.0115   1.0000
  17.500   1.5175   0.06839   0.06343  -0.0178   0.0113   1.0000
  17.750   1.5087   0.07275   0.06789  -0.0186   0.0110   1.0000
  18.000   1.4976   0.07748   0.07272  -0.0196   0.0108   1.0000
  18.250   1.4838   0.08267   0.07802  -0.0208   0.0106   1.0000
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