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BOEING 103 AIRFOIL (boe103-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: BOEING 103 AIRFOIL (boe103-il)
Reynolds number: 100,000
Max Cl/Cd: 52.05 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-boe103-il-100000-n5.txt
Download as CSV file: xf-boe103-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3858   0.09270   0.08757  -0.0457   1.0000   0.0446
  -9.500  -0.3950   0.08856   0.08350  -0.0465   1.0000   0.0443
  -9.250  -0.4082   0.08434   0.07937  -0.0471   1.0000   0.0439
  -9.000  -0.4275   0.08014   0.07528  -0.0473   1.0000   0.0434
  -8.750  -0.4576   0.07613   0.07140  -0.0468   1.0000   0.0429
  -8.500  -0.4945   0.07090   0.06624  -0.0470   1.0000   0.0423
  -8.250  -0.5166   0.05999   0.05504  -0.0544   0.9937   0.0415
  -8.000  -0.5119   0.05163   0.04618  -0.0605   0.9849   0.0418
  -7.750  -0.4981   0.04656   0.04067  -0.0634   0.9768   0.0430
  -7.500  -0.4816   0.04168   0.03521  -0.0656   0.9695   0.0441
  -7.250  -0.4601   0.03752   0.03043  -0.0673   0.9631   0.0448
  -7.000  -0.4374   0.03441   0.02675  -0.0680   0.9563   0.0455
  -6.750  -0.4097   0.03193   0.02367  -0.0691   0.9506   0.0470
  -6.500  -0.3796   0.03024   0.02186  -0.0704   0.9457   0.0483
  -6.250  -0.3521   0.02876   0.02017  -0.0708   0.9389   0.0492
  -6.000  -0.3183   0.02726   0.01844  -0.0723   0.9348   0.0502
  -5.750  -0.2889   0.02602   0.01700  -0.0728   0.9286   0.0513
  -5.500  -0.2576   0.02496   0.01575  -0.0736   0.9227   0.0533
  -5.250  -0.2214   0.02391   0.01448  -0.0752   0.9190   0.0552
  -5.000  -0.1927   0.02295   0.01348  -0.0755   0.9122   0.0565
  -4.750  -0.1615   0.02211   0.01264  -0.0762   0.9062   0.0580
  -4.500  -0.1263   0.02131   0.01180  -0.0776   0.9021   0.0600
  -4.250  -0.1002   0.02074   0.01117  -0.0773   0.8936   0.0623
  -4.000  -0.0675   0.02011   0.01049  -0.0781   0.8880   0.0661
  -3.750  -0.0375   0.01957   0.00996  -0.0785   0.8814   0.0713
  -3.500  -0.0087   0.01908   0.00943  -0.0786   0.8736   0.0777
  -3.250   0.0252   0.01846   0.00888  -0.0796   0.8687   0.0915
  -3.000   0.0496   0.01806   0.00860  -0.0789   0.8590   0.1193
  -2.750   0.0821   0.01758   0.00823  -0.0797   0.8532   0.1615
  -2.500   0.1075   0.01726   0.00804  -0.0793   0.8438   0.2014
  -2.250   0.1377   0.01667   0.00773  -0.0798   0.8373   0.2651
  -2.000   0.1616   0.01607   0.00763  -0.0792   0.8281   0.3827
  -1.750   0.1880   0.01538   0.00755  -0.0786   0.8211   0.5521
  -1.500   0.2095   0.01500   0.00764  -0.0765   0.8120   0.6895
  -1.250   0.2378   0.01472   0.00764  -0.0752   0.8049   0.7961
  -1.000   0.2721   0.01467   0.00763  -0.0755   0.7959   0.8672
  -0.750   0.3179   0.01453   0.00738  -0.0781   0.7869   0.9224
  -0.500   0.3670   0.01446   0.00717  -0.0819   0.7734   0.9668
  -0.250   0.4244   0.01434   0.00690  -0.0877   0.7604   0.9969
   0.000   0.4522   0.01433   0.00674  -0.0877   0.7496   1.0000
   0.250   0.4760   0.01434   0.00662  -0.0868   0.7389   1.0000
   0.500   0.4978   0.01441   0.00659  -0.0857   0.7270   1.0000
   0.750   0.5213   0.01447   0.00654  -0.0847   0.7162   1.0000
   1.000   0.5462   0.01451   0.00646  -0.0840   0.7057   1.0000
   1.250   0.5683   0.01462   0.00650  -0.0828   0.6935   1.0000
   1.500   0.5919   0.01473   0.00652  -0.0819   0.6821   1.0000
   1.750   0.6168   0.01482   0.00651  -0.0811   0.6710   1.0000
   2.000   0.6404   0.01494   0.00656  -0.0802   0.6589   1.0000
   2.250   0.6637   0.01509   0.00665  -0.0792   0.6464   1.0000
   2.500   0.6878   0.01523   0.00673  -0.0783   0.6340   1.0000
   2.750   0.7122   0.01538   0.00679  -0.0775   0.6215   1.0000
   3.000   0.7364   0.01554   0.00689  -0.0766   0.6084   1.0000
   3.250   0.7594   0.01573   0.00704  -0.0756   0.5938   1.0000
   3.500   0.7824   0.01592   0.00717  -0.0745   0.5782   1.0000
   3.750   0.8052   0.01611   0.00730  -0.0734   0.5611   1.0000
   4.000   0.8275   0.01632   0.00744  -0.0722   0.5427   1.0000
   4.250   0.8485   0.01656   0.00762  -0.0708   0.5213   1.0000
   4.500   0.8691   0.01681   0.00777  -0.0693   0.4977   1.0000
   4.750   0.8889   0.01711   0.00796  -0.0678   0.4716   1.0000
   5.000   0.9083   0.01745   0.00816  -0.0662   0.4455   1.0000
   5.250   0.9279   0.01783   0.00844  -0.0647   0.4207   1.0000
   5.500   0.9476   0.01825   0.00875  -0.0633   0.4000   1.0000
   5.750   0.9674   0.01869   0.00910  -0.0619   0.3817   1.0000
   6.000   0.9871   0.01915   0.00949  -0.0606   0.3648   1.0000
   6.250   1.0065   0.01963   0.00992  -0.0592   0.3491   1.0000
   6.750   1.0444   0.02066   0.01088  -0.0565   0.3191   1.0000
   7.000   1.0628   0.02119   0.01141  -0.0551   0.3044   1.0000
   7.250   1.0806   0.02175   0.01197  -0.0536   0.2894   1.0000
   7.500   1.0975   0.02234   0.01255  -0.0520   0.2737   1.0000
   7.750   1.1133   0.02297   0.01317  -0.0503   0.2573   1.0000
   8.000   1.1274   0.02363   0.01381  -0.0483   0.2404   1.0000
   8.250   1.1398   0.02436   0.01451  -0.0461   0.2239   1.0000
   8.500   1.1517   0.02516   0.01527  -0.0439   0.2083   1.0000
   8.750   1.1634   0.02602   0.01610  -0.0419   0.1944   1.0000
   9.000   1.1753   0.02693   0.01700  -0.0399   0.1829   1.0000
   9.250   1.1865   0.02792   0.01797  -0.0379   0.1738   1.0000
   9.500   1.1972   0.02896   0.01902  -0.0360   0.1663   1.0000
   9.750   1.2085   0.03002   0.02010  -0.0343   0.1601   1.0000
  10.000   1.2201   0.03109   0.02122  -0.0326   0.1544   1.0000
  10.250   1.2293   0.03232   0.02242  -0.0309   0.1498   1.0000
  10.500   1.2417   0.03342   0.02361  -0.0295   0.1449   1.0000
  10.750   1.2527   0.03460   0.02488  -0.0281   0.1403   1.0000
  11.000   1.2618   0.03592   0.02620  -0.0266   0.1364   1.0000
  11.250   1.2727   0.03719   0.02754  -0.0253   0.1328   1.0000
  11.500   1.2838   0.03846   0.02893  -0.0241   0.1291   1.0000
  11.750   1.2933   0.03984   0.03039  -0.0229   0.1257   1.0000
  12.000   1.3017   0.04131   0.03190  -0.0217   0.1227   1.0000
  12.250   1.3111   0.04280   0.03347  -0.0206   0.1197   1.0000
  12.500   1.3195   0.04435   0.03519  -0.0196   0.1164   1.0000
  12.750   1.3262   0.04603   0.03698  -0.0187   0.1132   1.0000
  13.000   1.3311   0.04785   0.03885  -0.0178   0.1100   1.0000
  13.250   1.3357   0.04977   0.04086  -0.0170   0.1069   1.0000
  13.500   1.3391   0.05189   0.04319  -0.0164   0.1036   1.0000
  13.750   1.3414   0.05412   0.04555  -0.0159   0.1004   1.0000
  14.000   1.3433   0.05642   0.04795  -0.0155   0.0978   1.0000
  14.250   1.3461   0.05867   0.05021  -0.0150   0.0956   1.0000
  14.500   1.3476   0.06123   0.05298  -0.0148   0.0935   1.0000
  14.750   1.3479   0.06401   0.05598  -0.0148   0.0912   1.0000
  15.000   1.3471   0.06695   0.05910  -0.0150   0.0890   1.0000
  15.250   1.3454   0.07006   0.06238  -0.0153   0.0869   1.0000
  15.500   1.3427   0.07337   0.06579  -0.0159   0.0849   1.0000
  15.750   1.3406   0.07661   0.06907  -0.0165   0.0829   1.0000
  16.000   1.3351   0.08060   0.07328  -0.0175   0.0811   1.0000
  16.250   1.3279   0.08499   0.07792  -0.0188   0.0792   1.0000
  16.500   1.3202   0.08957   0.08271  -0.0203   0.0775   1.0000
  16.750   1.3116   0.09439   0.08773  -0.0221   0.0758   1.0000
  17.000   1.3025   0.09940   0.09290  -0.0241   0.0743   1.0000
  17.250   1.2932   0.10454   0.09818  -0.0263   0.0729   1.0000
  17.500   1.2850   0.10958   0.10333  -0.0286   0.0715   1.0000
  17.750   1.2721   0.11567   0.10958  -0.0316   0.0703   1.0000
  18.000   1.2492   0.12402   0.11819  -0.0359   0.0692   1.0000
  18.250   1.2178   0.13444   0.12885  -0.0416   0.0684   1.0000
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