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BOEING 106 AIRFOIL (boe106-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: BOEING 106 AIRFOIL (boe106-il)
Reynolds number: 200,000
Max Cl/Cd: 70.24 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-boe106-il-200000-n5.txt
Download as CSV file: xf-boe106-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.6377   0.05204   0.04802  -0.0750   1.0000   0.0266
 -11.000  -0.6734   0.04781   0.04362  -0.0738   1.0000   0.0265
 -10.750  -0.7093   0.04498   0.04061  -0.0684   1.0000   0.0266
 -10.500  -0.7145   0.04147   0.03680  -0.0681   0.9947   0.0271
 -10.250  -0.6903   0.04020   0.03547  -0.0697   0.9890   0.0276
 -10.000  -0.6672   0.03819   0.03328  -0.0718   0.9839   0.0284
  -9.750  -0.6485   0.03573   0.03053  -0.0730   0.9765   0.0293
  -9.500  -0.6296   0.03288   0.02723  -0.0741   0.9701   0.0307
  -9.250  -0.6121   0.03003   0.02372  -0.0744   0.9623   0.0321
  -9.000  -0.5857   0.02864   0.02227  -0.0753   0.9570   0.0329
  -8.750  -0.5607   0.02761   0.02113  -0.0756   0.9499   0.0338
  -8.500  -0.5323   0.02654   0.01989  -0.0765   0.9450   0.0350
  -8.250  -0.5094   0.02541   0.01853  -0.0762   0.9366   0.0364
  -8.000  -0.4828   0.02414   0.01695  -0.0764   0.9303   0.0376
  -7.750  -0.4587   0.02306   0.01560  -0.0760   0.9219   0.0386
  -7.500  -0.4326   0.02203   0.01454  -0.0761   0.9147   0.0397
  -7.250  -0.4076   0.02132   0.01376  -0.0757   0.9064   0.0409
  -7.000  -0.3817   0.02055   0.01287  -0.0755   0.8988   0.0421
  -6.750  -0.3566   0.01979   0.01198  -0.0750   0.8913   0.0432
  -6.500  -0.3311   0.01912   0.01117  -0.0746   0.8837   0.0445
  -6.250  -0.3052   0.01856   0.01046  -0.0741   0.8765   0.0458
  -6.000  -0.2809   0.01776   0.00963  -0.0735   0.8686   0.0471
  -5.750  -0.2556   0.01714   0.00897  -0.0731   0.8618   0.0483
  -5.500  -0.2309   0.01663   0.00842  -0.0725   0.8536   0.0497
  -5.250  -0.2052   0.01615   0.00787  -0.0720   0.8470   0.0513
  -5.000  -0.1802   0.01575   0.00740  -0.0714   0.8386   0.0533
  -4.500  -0.1300   0.01487   0.00643  -0.0703   0.8235   0.0579
  -4.250  -0.1041   0.01450   0.00601  -0.0698   0.8166   0.0607
  -4.000  -0.0788   0.01420   0.00566  -0.0693   0.8082   0.0641
  -3.750  -0.0529   0.01386   0.00530  -0.0688   0.8010   0.0692
  -3.500  -0.0274   0.01359   0.00503  -0.0684   0.7926   0.0776
  -3.250  -0.0014   0.01329   0.00478  -0.0679   0.7851   0.0928
  -3.000   0.0243   0.01305   0.00459  -0.0675   0.7766   0.1144
  -2.750   0.0505   0.01283   0.00436  -0.0671   0.7687   0.1364
  -2.500   0.0761   0.01258   0.00419  -0.0667   0.7597   0.1607
  -2.250   0.1016   0.01229   0.00399  -0.0662   0.7516   0.1950
  -2.000   0.1256   0.01190   0.00387  -0.0656   0.7415   0.2668
  -1.750   0.1491   0.01149   0.00374  -0.0648   0.7319   0.3571
  -1.500   0.1707   0.01098   0.00363  -0.0636   0.7213   0.4710
  -1.250   0.1897   0.01043   0.00364  -0.0617   0.7107   0.6212
  -1.000   0.2121   0.01016   0.00366  -0.0600   0.7010   0.7255
  -0.750   0.2377   0.01004   0.00369  -0.0590   0.6905   0.7885
  -0.500   0.2671   0.01002   0.00372  -0.0588   0.6806   0.8361
   0.000   0.3363   0.01015   0.00378  -0.0608   0.6599   0.9107
   0.250   0.3736   0.01025   0.00380  -0.0625   0.6491   0.9335
   0.500   0.4106   0.01035   0.00380  -0.0641   0.6385   0.9529
   0.750   0.4491   0.01046   0.00383  -0.0663   0.6272   0.9698
   1.000   0.4910   0.01055   0.00383  -0.0692   0.6158   0.9818
   1.250   0.5374   0.01063   0.00381  -0.0732   0.6041   0.9934
   1.500   0.5778   0.01070   0.00378  -0.0760   0.5925   1.0000
   1.750   0.6009   0.01079   0.00381  -0.0752   0.5821   1.0000
   2.000   0.6240   0.01090   0.00385  -0.0743   0.5725   1.0000
   2.250   0.6470   0.01102   0.00390  -0.0735   0.5623   1.0000
   2.500   0.6699   0.01115   0.00398  -0.0726   0.5522   1.0000
   2.750   0.6927   0.01130   0.00406  -0.0717   0.5427   1.0000
   3.000   0.7157   0.01145   0.00418  -0.0708   0.5328   1.0000
   3.250   0.7386   0.01161   0.00430  -0.0698   0.5241   1.0000
   3.500   0.7614   0.01178   0.00443  -0.0689   0.5151   1.0000
   3.750   0.7843   0.01196   0.00459  -0.0680   0.5061   1.0000
   4.250   0.8284   0.01235   0.00489  -0.0658   0.4831   1.0000
   4.500   0.8503   0.01255   0.00507  -0.0647   0.4711   1.0000
   4.750   0.8720   0.01277   0.00525  -0.0636   0.4600   1.0000
   5.000   0.8936   0.01300   0.00544  -0.0625   0.4487   1.0000
   5.250   0.9156   0.01321   0.00567  -0.0614   0.4375   1.0000
   5.500   0.9373   0.01345   0.00589  -0.0603   0.4264   1.0000
   5.750   0.9586   0.01371   0.00612  -0.0592   0.4149   1.0000
   6.000   0.9801   0.01397   0.00637  -0.0581   0.4031   1.0000
   6.250   1.0009   0.01425   0.00663  -0.0569   0.3892   1.0000
   6.500   1.0211   0.01457   0.00691  -0.0556   0.3739   1.0000
   6.750   1.0412   0.01490   0.00721  -0.0543   0.3592   1.0000
   7.000   1.0614   0.01524   0.00754  -0.0531   0.3458   1.0000
   7.250   1.0814   0.01560   0.00789  -0.0519   0.3331   1.0000
   7.500   1.1008   0.01598   0.00827  -0.0506   0.3195   1.0000
   7.750   1.1196   0.01640   0.00868  -0.0492   0.3041   1.0000
   8.000   1.1377   0.01684   0.00910  -0.0478   0.2864   1.0000
   8.250   1.1545   0.01734   0.00957  -0.0462   0.2655   1.0000
   8.500   1.1689   0.01795   0.01010  -0.0442   0.2390   1.0000
   8.750   1.1778   0.01876   0.01075  -0.0415   0.2060   1.0000
   9.000   1.1847   0.01971   0.01156  -0.0387   0.1805   1.0000
   9.250   1.1934   0.02066   0.01243  -0.0362   0.1641   1.0000
   9.500   1.2037   0.02158   0.01332  -0.0341   0.1520   1.0000
   9.750   1.2140   0.02253   0.01427  -0.0322   0.1425   1.0000
  10.000   1.2248   0.02348   0.01524  -0.0304   0.1338   1.0000
  10.250   1.2358   0.02447   0.01628  -0.0287   0.1266   1.0000
  10.500   1.2456   0.02556   0.01740  -0.0271   0.1194   1.0000
  10.750   1.2554   0.02669   0.01858  -0.0255   0.1133   1.0000
  11.000   1.2650   0.02789   0.01982  -0.0241   0.1073   1.0000
  11.250   1.2722   0.02929   0.02124  -0.0226   0.1025   1.0000
  11.500   1.2823   0.03053   0.02259  -0.0214   0.0977   1.0000
  11.750   1.2895   0.03203   0.02412  -0.0202   0.0931   1.0000
  12.000   1.2959   0.03365   0.02578  -0.0191   0.0892   1.0000
  12.250   1.3047   0.03512   0.02734  -0.0182   0.0847   1.0000
  12.500   1.3099   0.03692   0.02917  -0.0172   0.0805   1.0000
  12.750   1.3157   0.03873   0.03104  -0.0164   0.0770   1.0000
  13.000   1.3228   0.04047   0.03289  -0.0157   0.0732   1.0000
  13.250   1.3269   0.04252   0.03499  -0.0151   0.0700   1.0000
  13.500   1.3291   0.04479   0.03731  -0.0145   0.0671   1.0000
  13.750   1.3355   0.04671   0.03936  -0.0140   0.0642   1.0000
  14.000   1.3394   0.04894   0.04168  -0.0137   0.0616   1.0000
  14.250   1.3409   0.05148   0.04428  -0.0135   0.0592   1.0000
  14.500   1.3413   0.05422   0.04708  -0.0134   0.0570   1.0000
  14.750   1.3461   0.05653   0.04955  -0.0133   0.0545   1.0000
  15.000   1.3482   0.05919   0.05233  -0.0134   0.0519   1.0000
  15.250   1.3475   0.06227   0.05547  -0.0136   0.0496   1.0000
  15.500   1.3471   0.06538   0.05867  -0.0140   0.0474   1.0000
  15.750   1.3491   0.06823   0.06167  -0.0143   0.0445   1.0000
  16.000   1.3474   0.07164   0.06515  -0.0149   0.0419   1.0000
  16.250   1.3453   0.07513   0.06874  -0.0156   0.0393   1.0000
  16.500   1.3437   0.07863   0.07235  -0.0163   0.0362   1.0000
  16.750   1.3384   0.08273   0.07653  -0.0174   0.0339   1.0000
  17.000   1.3353   0.08654   0.08047  -0.0183   0.0310   1.0000
  17.250   1.3283   0.09098   0.08499  -0.0196   0.0289   1.0000
  17.500   1.3221   0.09539   0.08951  -0.0209   0.0270   1.0000
  17.750   1.3144   0.10011   0.09432  -0.0225   0.0253   1.0000
  18.000   1.3048   0.10523   0.09953  -0.0244   0.0240   1.0000
  18.250   1.2961   0.11025   0.10466  -0.0262   0.0229   1.0000
  18.500   1.2872   0.11539   0.10992  -0.0283   0.0219   1.0000
  18.750   1.2772   0.12083   0.11548  -0.0306   0.0210   1.0000
  19.000   1.2664   0.12655   0.12130  -0.0332   0.0203   1.0000
  19.250   1.2545   0.13255   0.12739  -0.0361   0.0198   1.0000
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