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BOEING 106 AIRFOIL (boe106-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: BOEING 106 AIRFOIL (boe106-il)
Reynolds number: 50,000
Max Cl/Cd: 29.69 at α=10.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-boe106-il-50000.txt
Download as CSV file: xf-boe106-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3636   0.11880   0.11165  -0.0273   1.0000   0.2571
  -9.750  -0.3376   0.11336   0.10619  -0.0262   1.0000   0.2656
  -9.500  -0.3662   0.11346   0.10647  -0.0276   1.0000   0.2743
  -9.250  -0.3398   0.10857   0.10154  -0.0261   1.0000   0.2882
  -9.000  -0.3277   0.10494   0.09794  -0.0252   1.0000   0.3001
  -8.750  -0.3290   0.10235   0.09544  -0.0247   1.0000   0.3118
  -8.500  -0.3582   0.10254   0.09582  -0.0238   1.0000   0.3235
  -8.250  -0.3396   0.09858   0.09186  -0.0222   1.0000   0.3389
  -8.000  -0.3246   0.09491   0.08822  -0.0207   1.0000   0.3514
  -7.750  -0.3253   0.09254   0.08594  -0.0187   1.0000   0.3645
  -7.500  -0.3299   0.09058   0.08408  -0.0161   1.0000   0.3797
  -7.250  -0.3758   0.09166   0.08542  -0.0108   1.0000   0.3905
  -7.000  -0.3383   0.08696   0.08065  -0.0096   1.0000   0.4135
  -6.750  -0.3442   0.08530   0.07909  -0.0059   1.0000   0.4307
  -6.500  -0.3512   0.08372   0.07761  -0.0020   1.0000   0.4479
  -6.250  -0.3592   0.08218   0.07615   0.0020   1.0000   0.4650
  -6.000  -0.3673   0.08066   0.07471   0.0062   1.0000   0.4828
  -5.750  -0.3795   0.07944   0.07359   0.0109   1.0000   0.5027
  -5.500  -0.5246   0.05871   0.05191  -0.0244   1.0000   0.1948
  -5.250  -0.5133   0.05314   0.04563  -0.0262   1.0000   0.1760
  -5.000  -0.4992   0.04993   0.04224  -0.0257   1.0000   0.1738
  -4.750  -0.4826   0.04666   0.03863  -0.0258   1.0000   0.1701
  -4.500  -0.4630   0.04329   0.03468  -0.0261   1.0000   0.1657
  -4.250  -0.4428   0.04094   0.03189  -0.0260   1.0000   0.1659
  -4.000  -0.4225   0.03916   0.02978  -0.0257   1.0000   0.1692
  -3.750  -0.4008   0.03745   0.02766  -0.0255   1.0000   0.1718
  -3.500  -0.3783   0.03593   0.02571  -0.0253   1.0000   0.1743
  -3.250  -0.3564   0.03463   0.02417  -0.0250   1.0000   0.1796
  -3.000  -0.3354   0.03373   0.02318  -0.0247   1.0000   0.1879
  -2.750  -0.3130   0.03281   0.02204  -0.0244   1.0000   0.1959
  -2.500  -0.2911   0.03216   0.02128  -0.0240   1.0000   0.2080
  -2.250  -0.2689   0.03157   0.02070  -0.0237   1.0000   0.2256
  -2.000  -0.2216   0.03098   0.02037  -0.0277   0.9921   0.2693
  -1.750  -0.1728   0.02940   0.01995  -0.0317   0.9838   0.4259
  -1.500  -0.1158   0.02812   0.02036  -0.0338   0.9737   1.0000
  -1.250  -0.0743   0.02900   0.02072  -0.0376   0.9611   1.0000
  -1.000  -0.0347   0.02986   0.02118  -0.0411   0.9484   1.0000
  -0.750   0.0055   0.03075   0.02173  -0.0445   0.9358   1.0000
  -0.500   0.0504   0.03168   0.02235  -0.0486   0.9235   1.0000
  -0.250   0.0805   0.03239   0.02284  -0.0501   0.9097   1.0000
   0.000   0.1104   0.03313   0.02339  -0.0515   0.8961   1.0000
   0.250   0.1415   0.03392   0.02399  -0.0530   0.8828   1.0000
   0.500   0.1753   0.03471   0.02462  -0.0548   0.8700   1.0000
   0.750   0.2167   0.03548   0.02523  -0.0577   0.8580   1.0000
   1.000   0.2418   0.03623   0.02587  -0.0581   0.8446   1.0000
   1.250   0.2642   0.03705   0.02659  -0.0580   0.8313   1.0000
   1.500   0.2902   0.03789   0.02734  -0.0585   0.8185   1.0000
   1.750   0.3233   0.03867   0.02804  -0.0599   0.8070   1.0000
   2.000   0.3552   0.03942   0.02873  -0.0610   0.7952   1.0000
   2.250   0.3709   0.04045   0.02970  -0.0600   0.7822   1.0000
   2.500   0.3916   0.04147   0.03068  -0.0597   0.7702   1.0000
   2.750   0.4274   0.04220   0.03137  -0.0612   0.7599   1.0000
   3.000   0.4454   0.04330   0.03245  -0.0606   0.7480   1.0000
   3.250   0.4574   0.04465   0.03378  -0.0595   0.7362   1.0000
   3.500   0.4854   0.04562   0.03474  -0.0600   0.7263   1.0000
   3.750   0.5052   0.04683   0.03595  -0.0597   0.7159   1.0000
   4.000   0.5128   0.04855   0.03767  -0.0584   0.7053   1.0000
   4.250   0.5552   0.04907   0.03822  -0.0601   0.6973   1.0000
   4.500   0.5468   0.05149   0.04063  -0.0576   0.6865   1.0000
   4.750   0.5689   0.05289   0.04206  -0.0577   0.6784   1.0000
   5.000   0.5774   0.05479   0.04399  -0.0568   0.6693   1.0000
   5.250   0.5911   0.05663   0.04586  -0.0564   0.6614   1.0000
   5.500   0.6002   0.05867   0.04793  -0.0558   0.6535   1.0000
   5.750   0.6149   0.06055   0.04985  -0.0555   0.6457   1.0000
   6.000   0.6221   0.06274   0.05208  -0.0548   0.6378   1.0000
   6.250   0.6358   0.06466   0.05407  -0.0544   0.6291   1.0000
   6.500   0.6727   0.06518   0.05469  -0.0547   0.6167   1.0000
   6.750   0.6853   0.06665   0.05622  -0.0536   0.6031   1.0000
   7.000   0.6947   0.06832   0.05796  -0.0524   0.5892   1.0000
   7.250   0.7088   0.06979   0.05951  -0.0514   0.5750   1.0000
   7.500   0.7251   0.07115   0.06096  -0.0504   0.5608   1.0000
   7.750   0.7441   0.07228   0.06219  -0.0494   0.5458   1.0000
   8.000   0.7641   0.07325   0.06329  -0.0483   0.5300   1.0000
   8.250   0.7855   0.07398   0.06414  -0.0470   0.5131   1.0000
   8.500   0.8099   0.07431   0.06461  -0.0456   0.4956   1.0000
   8.750   0.8462   0.07320   0.06369  -0.0437   0.4772   1.0000
   9.000   0.9007   0.06959   0.06031  -0.0410   0.4594   1.0000
   9.250   1.0529   0.05346   0.04466  -0.0366   0.4404   1.0000
   9.500   0.9252   0.07105   0.06201  -0.0365   0.4189   1.0000
   9.750   1.1932   0.04321   0.03449  -0.0349   0.3741   1.0000
  10.000   1.2228   0.04246   0.03358  -0.0331   0.3446   1.0000
  10.250   1.2528   0.04220   0.03305  -0.0318   0.3171   1.0000
  10.500   1.2545   0.04392   0.03487  -0.0286   0.2985   1.0000
  10.750   1.2614   0.04545   0.03644  -0.0260   0.2812   1.0000
  11.000   1.2708   0.04702   0.03802  -0.0238   0.2657   1.0000
  11.250   1.2828   0.04870   0.03971  -0.0219   0.2522   1.0000
  11.500   1.2984   0.05027   0.04125  -0.0204   0.2393   1.0000
  11.750   1.3207   0.05185   0.04278  -0.0197   0.2267   1.0000
  12.000   1.2958   0.05535   0.04666  -0.0153   0.2228   1.0000
  12.250   1.3216   0.05701   0.04826  -0.0149   0.2116   1.0000
  12.500   1.2906   0.06115   0.05275  -0.0111   0.2095   1.0000
  12.750   1.2546   0.06636   0.05824  -0.0085   0.2082   1.0000
  13.000   1.2041   0.07385   0.06598  -0.0077   0.2092   1.0000
  13.250   1.1409   0.08476   0.07702  -0.0098   0.2116   1.0000
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