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BOEING 106 AIRFOIL (boe106-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: BOEING 106 AIRFOIL (boe106-il)
Reynolds number: 50,000
Max Cl/Cd: 32.53 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-boe106-il-50000-n5.txt
Download as CSV file: xf-boe106-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3919   0.09940   0.09213  -0.0456   1.0000   0.0749
  -9.750  -0.3975   0.09507   0.08788  -0.0475   1.0000   0.0750
  -9.500  -0.4059   0.09065   0.08355  -0.0493   1.0000   0.0751
  -9.250  -0.4177   0.08624   0.07925  -0.0510   1.0000   0.0750
  -9.000  -0.4355   0.08204   0.07516  -0.0521   1.0000   0.0746
  -8.750  -0.4590   0.07864   0.07188  -0.0512   1.0000   0.0741
  -8.500  -0.4814   0.07527   0.06856  -0.0497   1.0000   0.0738
  -8.250  -0.5034   0.07202   0.06532  -0.0477   1.0000   0.0735
  -8.000  -0.5233   0.06874   0.06200  -0.0456   1.0000   0.0733
  -7.750  -0.5399   0.06534   0.05850  -0.0435   1.0000   0.0731
  -7.500  -0.5525   0.06184   0.05483  -0.0414   1.0000   0.0730
  -7.250  -0.5607   0.05830   0.05104  -0.0396   1.0000   0.0731
  -7.000  -0.5554   0.05397   0.04629  -0.0401   0.9965   0.0738
  -6.750  -0.5360   0.04906   0.04064  -0.0429   0.9885   0.0761
  -6.500  -0.5109   0.04560   0.03671  -0.0450   0.9816   0.0780
  -6.250  -0.4825   0.04308   0.03389  -0.0467   0.9746   0.0795
  -6.000  -0.4540   0.04082   0.03130  -0.0482   0.9674   0.0816
  -5.750  -0.4223   0.03875   0.02881  -0.0501   0.9607   0.0854
  -5.500  -0.3934   0.03669   0.02617  -0.0510   0.9530   0.0885
  -5.250  -0.3594   0.03489   0.02409  -0.0527   0.9467   0.0910
  -5.000  -0.3288   0.03365   0.02273  -0.0537   0.9392   0.0943
  -4.750  -0.2949   0.03252   0.02133  -0.0551   0.9322   0.1001
  -4.500  -0.2606   0.03138   0.01998  -0.0564   0.9257   0.1054
  -4.250  -0.2294   0.03046   0.01901  -0.0572   0.9178   0.1107
  -4.000  -0.1895   0.02954   0.01793  -0.0594   0.9126   0.1205
  -3.750  -0.1628   0.02888   0.01722  -0.0593   0.9033   0.1310
  -3.500  -0.1237   0.02802   0.01631  -0.0615   0.8976   0.1480
  -3.250  -0.0958   0.02728   0.01566  -0.0618   0.8887   0.1706
  -3.000  -0.0619   0.02639   0.01498  -0.0632   0.8821   0.2116
  -2.750  -0.0376   0.02565   0.01463  -0.0630   0.8727   0.2767
  -2.500  -0.0101   0.02450   0.01431  -0.0631   0.8658   0.4281
  -2.250   0.0055   0.02364   0.01459  -0.0594   0.8566   0.6624
  -2.000   0.0542   0.02350   0.01474  -0.0607   0.8516   0.8449
  -1.750   0.1283   0.02353   0.01447  -0.0680   0.8485   0.9348
  -1.500   0.2281   0.02337   0.01393  -0.0817   0.8453   1.0000
  -1.250   0.2503   0.02334   0.01370  -0.0810   0.8342   1.0000
  -1.000   0.2684   0.02343   0.01361  -0.0796   0.8220   1.0000
  -0.750   0.2918   0.02344   0.01343  -0.0790   0.8117   1.0000
  -0.500   0.3167   0.02342   0.01325  -0.0784   0.8016   1.0000
  -0.250   0.3348   0.02358   0.01326  -0.0768   0.7893   1.0000
   0.000   0.3580   0.02363   0.01317  -0.0759   0.7789   1.0000
   0.250   0.3837   0.02362   0.01301  -0.0753   0.7691   1.0000
   0.500   0.4020   0.02383   0.01311  -0.0737   0.7569   1.0000
   0.750   0.4252   0.02391   0.01308  -0.0727   0.7465   1.0000
   1.000   0.4507   0.02393   0.01299  -0.0720   0.7368   1.0000
   1.250   0.4692   0.02420   0.01317  -0.0703   0.7249   1.0000
   1.500   0.4935   0.02429   0.01318  -0.0695   0.7152   1.0000
   1.750   0.5176   0.02440   0.01321  -0.0686   0.7052   1.0000
   2.000   0.5369   0.02471   0.01347  -0.0671   0.6937   1.0000
   2.250   0.5645   0.02474   0.01342  -0.0667   0.6854   1.0000
   2.500   0.5847   0.02504   0.01369  -0.0653   0.6742   1.0000
   2.750   0.6055   0.02536   0.01399  -0.0641   0.6635   1.0000
   3.000   0.6344   0.02537   0.01395  -0.0638   0.6556   1.0000
   3.250   0.6524   0.02584   0.01442  -0.0623   0.6440   1.0000
   3.500   0.6759   0.02611   0.01468  -0.0615   0.6344   1.0000
   3.750   0.7012   0.02630   0.01487  -0.0608   0.6253   1.0000
   4.000   0.7207   0.02679   0.01538  -0.0596   0.6147   1.0000
   4.250   0.7510   0.02680   0.01537  -0.0595   0.6074   1.0000
   4.500   0.7678   0.02744   0.01608  -0.0580   0.5961   1.0000
   4.750   0.7912   0.02782   0.01648  -0.0572   0.5871   1.0000
   5.000   0.8156   0.02815   0.01686  -0.0565   0.5782   1.0000
   5.250   0.8350   0.02876   0.01753  -0.0554   0.5684   1.0000
   5.500   0.8634   0.02894   0.01774  -0.0551   0.5609   1.0000
   5.750   0.8796   0.02975   0.01866  -0.0537   0.5505   1.0000
   6.000   0.9111   0.02980   0.01874  -0.0537   0.5437   1.0000
   6.250   0.9247   0.03070   0.01976  -0.0520   0.5323   1.0000
   6.500   0.9456   0.03111   0.02027  -0.0508   0.5213   1.0000
   6.750   0.9717   0.03107   0.02025  -0.0499   0.5091   1.0000
   7.000   0.9964   0.03101   0.02021  -0.0488   0.4956   1.0000
   7.250   1.0123   0.03144   0.02072  -0.0468   0.4812   1.0000
   7.500   1.0274   0.03203   0.02143  -0.0450   0.4680   1.0000
   7.750   1.0440   0.03254   0.02204  -0.0433   0.4553   1.0000
   8.000   1.0620   0.03294   0.02253  -0.0417   0.4425   1.0000
   8.250   1.0797   0.03329   0.02297  -0.0400   0.4289   1.0000
   8.500   1.0956   0.03368   0.02344  -0.0381   0.4146   1.0000
   8.750   1.1081   0.03420   0.02404  -0.0359   0.3993   1.0000
   9.000   1.1177   0.03483   0.02475  -0.0334   0.3833   1.0000
   9.250   1.1236   0.03559   0.02557  -0.0305   0.3666   1.0000
   9.500   1.1284   0.03651   0.02658  -0.0278   0.3491   1.0000
   9.750   1.1324   0.03757   0.02770  -0.0252   0.3305   1.0000
  10.000   1.1364   0.03874   0.02889  -0.0229   0.3113   1.0000
  10.250   1.1403   0.04001   0.03013  -0.0207   0.2918   1.0000
  10.500   1.1404   0.04177   0.03195  -0.0187   0.2718   1.0000
  10.750   1.1413   0.04362   0.03381  -0.0169   0.2529   1.0000
  11.000   1.1428   0.04553   0.03568  -0.0154   0.2357   1.0000
  11.250   1.1442   0.04757   0.03770  -0.0140   0.2206   1.0000
  11.500   1.1459   0.04972   0.03982  -0.0128   0.2075   1.0000
  11.750   1.1483   0.05191   0.04197  -0.0117   0.1963   1.0000
  12.000   1.1518   0.05402   0.04401  -0.0106   0.1865   1.0000
  12.250   1.1555   0.05625   0.04624  -0.0097   0.1773   1.0000
  12.500   1.1602   0.05850   0.04854  -0.0089   0.1693   1.0000
  12.750   1.1681   0.06039   0.05044  -0.0079   0.1620   1.0000
  13.000   1.1735   0.06276   0.05294  -0.0072   0.1555   1.0000
  13.250   1.1800   0.06497   0.05523  -0.0065   0.1490   1.0000
  13.500   1.1894   0.06693   0.05723  -0.0057   0.1433   1.0000
  13.750   1.1891   0.07013   0.06070  -0.0055   0.1385   1.0000
  14.000   1.1979   0.07221   0.06286  -0.0049   0.1335   1.0000
  14.250   1.2046   0.07464   0.06539  -0.0044   0.1291   1.0000
  14.500   1.1932   0.07927   0.07036  -0.0050   0.1257   1.0000
  14.750   1.1865   0.08341   0.07471  -0.0055   0.1221   1.0000
  15.000   1.2025   0.08456   0.07584  -0.0046   0.1176   1.0000
  15.250   1.1877   0.08993   0.08145  -0.0058   0.1152   1.0000
  15.500   1.1579   0.09787   0.08971  -0.0089   0.1137   1.0000
  15.750   1.1185   0.10825   0.10036  -0.0136   0.1127   1.0000
  16.000   1.0393   0.12858   0.12088  -0.0249   0.1131   1.0000
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