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AS5045 (15%) (as5045-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: AS5045 (15%) (as5045-il)
Reynolds number: 1,000,000
Max Cl/Cd: 92.52 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-as5045-il-1000000.txt
Download as CSV file: xf-as5045-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AS5045 (15%)                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.5803   0.13008   0.12752  -0.0045   0.7394   0.0113
 -13.000  -0.5834   0.12411   0.12155  -0.0073   0.7378   0.0115
  -9.250  -0.7769   0.02651   0.02103  -0.0408   0.7181   0.0096
  -9.000  -0.7581   0.02369   0.01795  -0.0399   0.7170   0.0092
  -8.750  -0.7361   0.02203   0.01613  -0.0394   0.7158   0.0093
  -8.500  -0.7131   0.02079   0.01477  -0.0390   0.7145   0.0094
  -8.250  -0.6896   0.01973   0.01361  -0.0387   0.7131   0.0095
  -8.000  -0.6657   0.01881   0.01261  -0.0384   0.7117   0.0096
  -7.750  -0.6416   0.01796   0.01169  -0.0382   0.7102   0.0097
  -7.500  -0.6173   0.01719   0.01086  -0.0381   0.7089   0.0098
  -7.250  -0.5927   0.01645   0.01007  -0.0379   0.7076   0.0099
  -7.000  -0.5677   0.01580   0.00936  -0.0379   0.7063   0.0100
  -6.750  -0.5422   0.01519   0.00870  -0.0380   0.7048   0.0101
  -6.500  -0.5162   0.01464   0.00811  -0.0382   0.7034   0.0102
  -6.250  -0.4896   0.01409   0.00754  -0.0385   0.7025   0.0103
  -6.000  -0.4642   0.01315   0.00656  -0.0388   0.7013   0.0107
  -5.750  -0.4367   0.01263   0.00602  -0.0392   0.7000   0.0111
  -5.500  -0.4086   0.01221   0.00557  -0.0397   0.6988   0.0115
  -5.250  -0.3801   0.01183   0.00517  -0.0401   0.6976   0.0119
  -5.000  -0.3513   0.01150   0.00482  -0.0406   0.6963   0.0126
  -4.750  -0.3223   0.01123   0.00452  -0.0410   0.6949   0.0132
  -4.500  -0.2933   0.01086   0.00413  -0.0416   0.6935   0.0145
  -4.250  -0.2639   0.01064   0.00388  -0.0421   0.6922   0.0161
  -4.000  -0.2345   0.01037   0.00361  -0.0426   0.6909   0.0213
  -3.750  -0.2046   0.00877   0.00288  -0.0447   0.6894   0.2307
  -3.500  -0.1723   0.00716   0.00227  -0.0476   0.6876   0.4871
  -3.250  -0.1414   0.00687   0.00225  -0.0484   0.6865   0.5682
  -3.000  -0.1112   0.00688   0.00230  -0.0489   0.6850   0.5918
  -2.750  -0.0811   0.00697   0.00240  -0.0492   0.6832   0.6095
  -2.500  -0.0509   0.00705   0.00242  -0.0497   0.6811   0.6178
  -2.250  -0.0211   0.00711   0.00251  -0.0499   0.6789   0.6249
  -2.000   0.0089   0.00718   0.00253  -0.0503   0.6767   0.6298
  -1.750   0.0390   0.00724   0.00252  -0.0507   0.6745   0.6333
  -1.250   0.0985   0.00730   0.00259  -0.0515   0.6697   0.6393
  -1.000   0.1285   0.00728   0.00257  -0.0519   0.6672   0.6416
  -0.750   0.1585   0.00728   0.00255  -0.0523   0.6644   0.6439
  -0.500   0.1885   0.00729   0.00253  -0.0527   0.6617   0.6462
  -0.250   0.2186   0.00731   0.00251  -0.0532   0.6589   0.6479
   0.000   0.2483   0.00732   0.00249  -0.0536   0.6557   0.6500
   0.250   0.2782   0.00726   0.00247  -0.0540   0.6531   0.6522
   0.500   0.3080   0.00722   0.00246  -0.0543   0.6495   0.6542
   0.750   0.3378   0.00719   0.00243  -0.0547   0.6455   0.6559
   1.000   0.3676   0.00718   0.00240  -0.0551   0.6417   0.6574
   1.250   0.3975   0.00716   0.00239  -0.0555   0.6377   0.6589
   1.500   0.4275   0.00711   0.00237  -0.0560   0.6327   0.6603
   1.750   0.4573   0.00709   0.00233  -0.0564   0.6276   0.6617
   2.000   0.4872   0.00709   0.00233  -0.0568   0.6222   0.6629
   2.250   0.5171   0.00707   0.00233  -0.0572   0.6152   0.6639
   2.500   0.5468   0.00703   0.00228  -0.0576   0.6076   0.6653
   2.750   0.5764   0.00698   0.00225  -0.0580   0.5972   0.6667
   3.000   0.6057   0.00699   0.00224  -0.0583   0.5825   0.6680
   3.250   0.6344   0.00706   0.00227  -0.0585   0.5606   0.6694
   3.500   0.6626   0.00721   0.00233  -0.0587   0.5314   0.6707
   3.750   0.6902   0.00746   0.00244  -0.0588   0.4949   0.6719
   4.000   0.7171   0.00780   0.00263  -0.0588   0.4543   0.6732
   4.250   0.7442   0.00813   0.00282  -0.0589   0.4181   0.6744
   4.500   0.7712   0.00846   0.00302  -0.0589   0.3847   0.6758
   4.750   0.7973   0.00888   0.00327  -0.0589   0.3443   0.6772
   5.000   0.8237   0.00927   0.00350  -0.0589   0.3084   0.6785
   5.250   0.8502   0.00963   0.00374  -0.0589   0.2808   0.6795
   5.500   0.8766   0.00998   0.00398  -0.0589   0.2534   0.6804
   5.750   0.9030   0.01028   0.00419  -0.0589   0.2295   0.6820
   6.000   0.9291   0.01061   0.00444  -0.0589   0.2079   0.6835
   6.250   0.9551   0.01096   0.00472  -0.0588   0.1879   0.6850
   6.500   0.9811   0.01129   0.00499  -0.0587   0.1706   0.6864
   6.750   1.0070   0.01163   0.00527  -0.0586   0.1548   0.6877
   7.000   1.0325   0.01198   0.00558  -0.0585   0.1398   0.6891
   7.250   1.0580   0.01234   0.00589  -0.0584   0.1263   0.6905
   7.500   1.0831   0.01272   0.00621  -0.0582   0.1137   0.6919
   7.750   1.1080   0.01311   0.00656  -0.0579   0.1024   0.6934
   8.000   1.1324   0.01354   0.00692  -0.0577   0.0916   0.6947
   8.250   1.1571   0.01392   0.00728  -0.0574   0.0832   0.6959
   8.500   1.1814   0.01429   0.00765  -0.0571   0.0756   0.6976
   8.750   1.2046   0.01476   0.00809  -0.0567   0.0674   0.6993
   9.000   1.2286   0.01513   0.00848  -0.0563   0.0622   0.7008
   9.250   1.2512   0.01562   0.00895  -0.0558   0.0560   0.7024
   9.500   1.2741   0.01605   0.00940  -0.0553   0.0519   0.7040
   9.750   1.2953   0.01661   0.00995  -0.0546   0.0474   0.7056
  10.000   1.3179   0.01702   0.01041  -0.0540   0.0449   0.7073
  10.250   1.3382   0.01759   0.01097  -0.0532   0.0418   0.7091
  10.500   1.3577   0.01820   0.01160  -0.0523   0.0391   0.7107
  10.750   1.3784   0.01866   0.01212  -0.0515   0.0375   0.7123
  11.000   1.3969   0.01924   0.01273  -0.0505   0.0353   0.7145
  11.250   1.4105   0.02005   0.01357  -0.0488   0.0326   0.7165
  11.500   1.4259   0.02050   0.01408  -0.0472   0.0316   0.7185
  11.750   1.4411   0.02113   0.01477  -0.0458   0.0302   0.7206
  12.000   1.4545   0.02196   0.01564  -0.0444   0.0288   0.7227
  12.250   1.4642   0.02312   0.01684  -0.0430   0.0272   0.7248
  12.500   1.4774   0.02414   0.01793  -0.0421   0.0263   0.7268
  12.750   1.4917   0.02515   0.01902  -0.0415   0.0255   0.7292
  13.000   1.5051   0.02631   0.02025  -0.0411   0.0246   0.7319
  13.250   1.5168   0.02764   0.02163  -0.0406   0.0236   0.7346
  13.500   1.5252   0.02928   0.02333  -0.0400   0.0225   0.7373
  13.750   1.5335   0.03095   0.02508  -0.0393   0.0217   0.7402
  14.000   1.5454   0.03226   0.02646  -0.0389   0.0211   0.7431
  14.250   1.5560   0.03368   0.02797  -0.0384   0.0203   0.7469
  14.500   1.5647   0.03529   0.02965  -0.0379   0.0196   0.7508
  14.750   1.5707   0.03712   0.03154  -0.0373   0.0188   0.7550
  15.000   1.5717   0.03946   0.03395  -0.0366   0.0179   0.7590
  15.250   1.5768   0.04144   0.03604  -0.0361   0.0175   0.7643
  15.500   1.5831   0.04329   0.03799  -0.0356   0.0170   0.7706
  15.750   1.5882   0.04529   0.04009  -0.0352   0.0164   0.7780
  16.000   1.5911   0.04754   0.04246  -0.0349   0.0159   0.7882
  16.250   1.5918   0.05004   0.04508  -0.0346   0.0153   0.8031
  16.500   1.5895   0.05299   0.04818  -0.0345   0.0147   0.8323
  16.750   1.5776   0.05612   0.05167  -0.0332   0.0142   1.0000
  17.000   1.5796   0.05886   0.05450  -0.0334   0.0139   1.0000
  17.250   1.5800   0.06187   0.05761  -0.0338   0.0135   1.0000
  17.500   1.5788   0.06519   0.06102  -0.0343   0.0131   1.0000
  17.750   1.5753   0.06891   0.06482  -0.0351   0.0126   1.0000
  18.000   1.5689   0.07310   0.06909  -0.0361   0.0122   1.0000
  18.250   1.5592   0.07785   0.07394  -0.0374   0.0119   1.0000
  18.500   1.5442   0.08357   0.07977  -0.0392   0.0115   1.0000
  18.750   1.5254   0.09003   0.08636  -0.0415   0.0112   1.0000
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