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BOEING 103 AIRFOIL (boe103-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: BOEING 103 AIRFOIL (boe103-il)
Reynolds number: 500,000
Max Cl/Cd: 81.07 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-boe103-il-500000-n5.txt
Download as CSV file: xf-boe103-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.7897   0.04313   0.04006  -0.0837   1.0000   0.0158
 -12.500  -0.8271   0.03932   0.03609  -0.0816   1.0000   0.0158
 -12.250  -0.8522   0.03747   0.03413  -0.0763   1.0000   0.0159
 -12.000  -0.8413   0.03493   0.03137  -0.0775   0.9972   0.0163
 -11.750  -0.8241   0.03214   0.02827  -0.0796   0.9940   0.0169
 -11.500  -0.8094   0.02920   0.02493  -0.0806   0.9891   0.0176
 -11.250  -0.7858   0.02737   0.02284  -0.0820   0.9859   0.0181
 -11.000  -0.7569   0.02666   0.02209  -0.0832   0.9830   0.0184
 -10.750  -0.7298   0.02604   0.02142  -0.0839   0.9783   0.0187
 -10.500  -0.7000   0.02529   0.02059  -0.0852   0.9751   0.0191
 -10.250  -0.6730   0.02442   0.01961  -0.0859   0.9710   0.0195
 -10.000  -0.6475   0.02353   0.01859  -0.0863   0.9655   0.0200
  -9.750  -0.6191   0.02254   0.01741  -0.0872   0.9619   0.0207
  -9.500  -0.5951   0.02164   0.01632  -0.0870   0.9547   0.0213
  -9.250  -0.5664   0.02083   0.01532  -0.0877   0.9499   0.0218
  -9.000  -0.5401   0.01971   0.01408  -0.0880   0.9440   0.0223
  -8.750  -0.5120   0.01899   0.01332  -0.0885   0.9376   0.0227
  -8.500  -0.4817   0.01841   0.01268  -0.0894   0.9323   0.0232
  -8.250  -0.4543   0.01785   0.01205  -0.0895   0.9245   0.0238
  -8.000  -0.4250   0.01722   0.01130  -0.0901   0.9178   0.0243
  -7.750  -0.3983   0.01661   0.01059  -0.0900   0.9095   0.0248
  -7.500  -0.3703   0.01608   0.00994  -0.0901   0.9018   0.0254
  -7.250  -0.3439   0.01563   0.00939  -0.0899   0.8933   0.0260
  -7.000  -0.3166   0.01520   0.00885  -0.0898   0.8853   0.0264
  -6.750  -0.2905   0.01481   0.00835  -0.0894   0.8767   0.0266
  -6.250  -0.2402   0.01348   0.00692  -0.0886   0.8601   0.0277
  -5.750  -0.1881   0.01273   0.00608  -0.0879   0.8437   0.0289
  -5.250  -0.1357   0.01206   0.00529  -0.0871   0.8267   0.0298
  -5.000  -0.1093   0.01177   0.00493  -0.0868   0.8186   0.0302
  -4.750  -0.0829   0.01148   0.00461  -0.0864   0.8097   0.0307
  -4.500  -0.0564   0.01124   0.00430  -0.0860   0.8011   0.0312
  -4.250  -0.0298   0.01101   0.00403  -0.0857   0.7917   0.0317
  -4.000  -0.0030   0.01084   0.00379  -0.0854   0.7832   0.0322
  -3.750   0.0233   0.01057   0.00348  -0.0850   0.7735   0.0331
  -3.500   0.0499   0.01036   0.00323  -0.0847   0.7638   0.0339
  -3.250   0.0764   0.01021   0.00301  -0.0843   0.7527   0.0347
  -3.000   0.1029   0.01008   0.00282  -0.0839   0.7397   0.0356
  -2.750   0.1294   0.00998   0.00266  -0.0835   0.7257   0.0367
  -2.500   0.1560   0.00990   0.00250  -0.0831   0.7120   0.0379
  -2.250   0.1825   0.00983   0.00237  -0.0826   0.6981   0.0396
  -2.000   0.2087   0.00975   0.00225  -0.0822   0.6834   0.0443
  -1.750   0.2341   0.00950   0.00213  -0.0817   0.6700   0.0884
  -1.500   0.2602   0.00935   0.00208  -0.0814   0.6588   0.1255
  -1.250   0.2871   0.00927   0.00203  -0.0811   0.6487   0.1484
  -1.000   0.3136   0.00921   0.00200  -0.0808   0.6384   0.1716
  -0.750   0.3401   0.00910   0.00196  -0.0805   0.6282   0.2049
  -0.500   0.3663   0.00894   0.00193  -0.0802   0.6192   0.2573
  -0.250   0.3910   0.00860   0.00193  -0.0798   0.6093   0.3791
   0.000   0.4159   0.00830   0.00195  -0.0793   0.5994   0.4906
   0.250   0.4395   0.00802   0.00200  -0.0785   0.5883   0.6082
   0.500   0.4633   0.00786   0.00207  -0.0775   0.5757   0.6926
   0.750   0.4870   0.00775   0.00213  -0.0765   0.5613   0.7609
   1.000   0.5090   0.00764   0.00224  -0.0749   0.5463   0.8444
   1.250   0.5339   0.00766   0.00235  -0.0738   0.5314   0.9125
   1.500   0.5660   0.00779   0.00244  -0.0745   0.5155   0.9465
   1.750   0.6009   0.00795   0.00251  -0.0760   0.4979   0.9675
   2.250   0.6759   0.00839   0.00270  -0.0803   0.4491   0.9943
   2.500   0.7094   0.00875   0.00284  -0.0818   0.4090   1.0000
   2.750   0.7279   0.00911   0.00299  -0.0800   0.3725   1.0000
   3.000   0.7471   0.00945   0.00315  -0.0784   0.3432   1.0000
   3.250   0.7674   0.00976   0.00332  -0.0769   0.3208   1.0000
   3.750   0.8106   0.01030   0.00365  -0.0746   0.2860   1.0000
   4.000   0.8338   0.01052   0.00381  -0.0737   0.2730   1.0000
   4.250   0.8570   0.01075   0.00398  -0.0729   0.2607   1.0000
   4.500   0.8802   0.01100   0.00416  -0.0720   0.2474   1.0000
   4.750   0.9031   0.01127   0.00436  -0.0712   0.2327   1.0000
   5.000   0.9257   0.01158   0.00458  -0.0703   0.2158   1.0000
   5.250   0.9478   0.01193   0.00483  -0.0693   0.1969   1.0000
   5.500   0.9693   0.01233   0.00511  -0.0683   0.1774   1.0000
   5.750   0.9905   0.01274   0.00542  -0.0672   0.1583   1.0000
   6.000   1.0111   0.01320   0.00576  -0.0661   0.1387   1.0000
   6.250   1.0315   0.01366   0.00613  -0.0649   0.1223   1.0000
   6.500   1.0530   0.01404   0.00646  -0.0640   0.1122   1.0000
   6.750   1.0747   0.01440   0.00679  -0.0630   0.1060   1.0000
   7.000   1.0967   0.01474   0.00711  -0.0621   0.1016   1.0000
   7.250   1.1180   0.01510   0.00746  -0.0611   0.0978   1.0000
   7.500   1.1393   0.01545   0.00781  -0.0602   0.0949   1.0000
   7.750   1.1604   0.01576   0.00815  -0.0591   0.0932   1.0000
   8.000   1.1805   0.01609   0.00851  -0.0579   0.0915   1.0000
   8.250   1.2002   0.01645   0.00889  -0.0567   0.0896   1.0000
   8.500   1.2189   0.01687   0.00931  -0.0553   0.0869   1.0000
   8.750   1.2368   0.01735   0.00979  -0.0539   0.0837   1.0000
   9.000   1.2558   0.01776   0.01023  -0.0526   0.0816   1.0000
   9.250   1.2749   0.01816   0.01067  -0.0514   0.0791   1.0000
   9.500   1.2930   0.01863   0.01116  -0.0502   0.0762   1.0000
   9.750   1.3098   0.01918   0.01171  -0.0488   0.0732   1.0000
  10.000   1.3264   0.01975   0.01230  -0.0474   0.0707   1.0000
  10.250   1.3445   0.02023   0.01283  -0.0462   0.0686   1.0000
  10.500   1.3613   0.02079   0.01342  -0.0450   0.0648   1.0000
  10.750   1.3765   0.02148   0.01410  -0.0436   0.0601   1.0000
  11.000   1.3901   0.02228   0.01488  -0.0421   0.0514   1.0000
  11.250   1.3982   0.02347   0.01597  -0.0401   0.0408   1.0000
  11.500   1.4087   0.02454   0.01705  -0.0384   0.0369   1.0000
  11.750   1.4189   0.02564   0.01818  -0.0369   0.0341   1.0000
  12.000   1.4291   0.02680   0.01937  -0.0354   0.0316   1.0000
  12.250   1.4390   0.02801   0.02063  -0.0340   0.0290   1.0000
  12.500   1.4467   0.02942   0.02208  -0.0326   0.0265   1.0000
  12.750   1.4569   0.03067   0.02339  -0.0315   0.0162   1.0000
  13.000   1.4564   0.03287   0.02557  -0.0298   0.0132   1.0000
  13.250   1.4607   0.03473   0.02752  -0.0285   0.0122   1.0000
  13.500   1.4642   0.03674   0.02963  -0.0274   0.0114   1.0000
  13.750   1.4698   0.03860   0.03159  -0.0266   0.0109   1.0000
  14.000   1.4741   0.04063   0.03372  -0.0258   0.0104   1.0000
  14.250   1.4768   0.04290   0.03609  -0.0251   0.0099   1.0000
  14.500   1.4778   0.04541   0.03871  -0.0245   0.0095   1.0000
  14.750   1.4769   0.04821   0.04162  -0.0241   0.0092   1.0000
  15.000   1.4779   0.05089   0.04441  -0.0239   0.0090   1.0000
  15.250   1.4786   0.05369   0.04732  -0.0238   0.0087   1.0000
  15.500   1.4780   0.05672   0.05046  -0.0239   0.0085   1.0000
  15.750   1.4758   0.06001   0.05387  -0.0242   0.0083   1.0000
  16.000   1.4725   0.06355   0.05753  -0.0246   0.0081   1.0000
  16.250   1.4679   0.06736   0.06145  -0.0252   0.0080   1.0000
  16.500   1.4617   0.07144   0.06566  -0.0259   0.0078   1.0000
  16.750   1.4538   0.07587   0.07021  -0.0269   0.0077   1.0000
  17.000   1.4445   0.08063   0.07510  -0.0282   0.0076   1.0000
  17.250   1.4335   0.08575   0.08035  -0.0296   0.0075   1.0000
  17.500   1.4208   0.09124   0.08598  -0.0314   0.0074   1.0000
  17.750   1.4066   0.09710   0.09198  -0.0334   0.0073   1.0000
  18.000   1.3908   0.10337   0.09838  -0.0357   0.0073   1.0000
  18.250   1.3740   0.10994   0.10509  -0.0383   0.0072   1.0000
  18.500   1.3562   0.11674   0.11203  -0.0411   0.0072   1.0000
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