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Smoothed ATR airfoil coordinates obtained using AFSMO (Harry Morgan's NASA smoothing program) (atr72sm-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: Smoothed ATR airfoil coordinates obtained using AFSMO (Harry Morgan's NASA smoothing program) (atr72sm-il)
Reynolds number: 50,000
Max Cl/Cd: 20.51 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-atr72sm-il-50000.txt
Download as CSV file: xf-atr72sm-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Smoothed ATR airfoil coordinates obtained  using
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3010   0.10721   0.10030  -0.0136   1.0000   0.3145
  -9.000  -0.3101   0.10529   0.09849  -0.0133   1.0000   0.3278
  -8.750  -0.3188   0.10392   0.09721  -0.0125   1.0000   0.3427
  -8.500  -0.2994   0.10014   0.09346  -0.0112   1.0000   0.3587
  -8.250  -0.2973   0.09778   0.09119  -0.0098   1.0000   0.3765
  -8.000  -0.2992   0.09575   0.08926  -0.0081   1.0000   0.3946
  -7.750  -0.2997   0.09353   0.08715  -0.0062   1.0000   0.4130
  -6.750  -0.2562   0.08178   0.07564   0.0008   1.0000   0.4876
  -6.500  -0.5355   0.06232   0.05595  -0.0176   1.0000   0.1819
  -6.250  -0.5596   0.05733   0.05038  -0.0152   1.0000   0.1680
  -6.000  -0.5574   0.05421   0.04715  -0.0130   1.0000   0.1662
  -5.750  -0.5565   0.05121   0.04392  -0.0107   1.0000   0.1653
  -5.500  -0.5536   0.04840   0.04082  -0.0085   1.0000   0.1650
  -5.250  -0.5480   0.04571   0.03780  -0.0064   1.0000   0.1647
  -5.000  -0.5401   0.04323   0.03494  -0.0044   1.0000   0.1654
  -4.750  -0.5306   0.04118   0.03241  -0.0023   1.0000   0.1679
  -4.500  -0.5178   0.03916   0.03021  -0.0008   1.0000   0.1718
  -4.250  -0.5031   0.03766   0.02864   0.0006   1.0000   0.1768
  -4.000  -0.4884   0.03635   0.02700   0.0021   1.0000   0.1829
  -3.750  -0.4729   0.03494   0.02534   0.0034   1.0000   0.1889
  -3.500  -0.4574   0.03395   0.02434   0.0045   1.0000   0.1973
  -3.250  -0.4148   0.03280   0.02300   0.0010   0.9894   0.2106
  -3.000  -0.3464   0.03173   0.02182  -0.0064   0.9685   0.2348
  -2.750  -0.2826   0.03051   0.02077  -0.0127   0.9455   0.2669
  -2.500  -0.2082   0.02892   0.01974  -0.0204   0.9241   0.3353
  -2.250  -0.1767   0.02655   0.01944  -0.0194   0.9013   0.5759
  -2.000   0.2678   0.02637   0.01871  -0.0749   0.8815   1.0000
  -1.750   0.3189   0.02503   0.01710  -0.0781   0.8390   1.0000
  -1.500   0.3418   0.02432   0.01612  -0.0764   0.7918   1.0000
  -1.250   0.3611   0.02379   0.01526  -0.0739   0.7519   1.0000
  -1.000   0.3770   0.02363   0.01479  -0.0714   0.7154   1.0000
  -0.750   0.3936   0.02362   0.01447  -0.0693   0.6848   1.0000
  -0.500   0.4105   0.02378   0.01440  -0.0676   0.6579   1.0000
  -0.250   0.4283   0.02397   0.01435  -0.0660   0.6361   1.0000
   0.000   0.4463   0.02422   0.01439  -0.0645   0.6176   1.0000
   0.250   0.4640   0.02456   0.01455  -0.0631   0.6009   1.0000
   0.500   0.4815   0.02497   0.01482  -0.0617   0.5860   1.0000
   0.750   0.4994   0.02542   0.01513  -0.0603   0.5730   1.0000
   1.000   0.5186   0.02585   0.01537  -0.0589   0.5619   1.0000
   1.250   0.5340   0.02657   0.01608  -0.0575   0.5502   1.0000
   1.500   0.5526   0.02714   0.01650  -0.0561   0.5408   1.0000
   1.750   0.5682   0.02789   0.01723  -0.0546   0.5308   1.0000
   2.000   0.5854   0.02862   0.01787  -0.0531   0.5225   1.0000
   2.250   0.6002   0.02953   0.01880  -0.0515   0.5141   1.0000
   2.500   0.6197   0.03022   0.01934  -0.0502   0.5076   1.0000
   2.750   0.6286   0.03157   0.02081  -0.0482   0.4998   1.0000
   3.000   0.6481   0.03226   0.02139  -0.0468   0.4932   1.0000
   3.250   0.6565   0.03372   0.02294  -0.0447   0.4867   1.0000
   3.500   0.6657   0.03517   0.02443  -0.0427   0.4806   1.0000
   3.750   0.6861   0.03600   0.02516  -0.0414   0.4757   1.0000
   4.000   0.6866   0.03812   0.02741  -0.0388   0.4706   1.0000
   4.250   0.6828   0.04047   0.02987  -0.0359   0.4651   1.0000
   4.500   0.6973   0.04172   0.03109  -0.0343   0.4601   1.0000
   4.750   0.7060   0.04353   0.03289  -0.0324   0.4560   1.0000
   5.000   0.6637   0.04875   0.03830  -0.0278   0.4536   1.0000
   5.250   0.5986   0.05596   0.04558  -0.0236   0.4534   1.0000
   5.500   0.5444   0.06287   0.05245  -0.0214   0.4553   1.0000
   5.750   0.5133   0.06860   0.05816  -0.0212   0.4587   1.0000
   6.250   0.3225   0.08824   0.07798  -0.0284   0.6219   1.0000
   6.500   0.3573   0.09199   0.08170  -0.0302   0.6142   1.0000
   6.750   0.3505   0.09273   0.08240  -0.0281   0.6012   1.0000
   7.000   0.3816   0.09677   0.08640  -0.0297   0.5956   1.0000
   7.250   0.3743   0.09730   0.08691  -0.0278   0.5831   1.0000
   7.500   0.3972   0.10089   0.09048  -0.0287   0.5773   1.0000
   7.750   0.4007   0.10214   0.09171  -0.0277   0.5642   1.0000
   8.000   0.4041   0.10413   0.09367  -0.0270   0.5541   1.0000
   8.250   0.4311   0.10744   0.09698  -0.0278   0.5450   1.0000
   8.500   0.4254   0.10878   0.09830  -0.0267   0.5350   1.0000
   8.750   0.4533   0.11240   0.10193  -0.0277   0.5273   1.0000
   9.000   0.4468   0.11358   0.10309  -0.0266   0.5163   1.0000
   9.250   0.4830   0.11818   0.10771  -0.0279   0.5090   1.0000
   9.500   0.4702   0.11853   0.10804  -0.0266   0.4969   1.0000
   9.750   0.5070   0.12370   0.11325  -0.0281   0.4915   1.0000
  10.000   0.4896   0.12354   0.11307  -0.0268   0.4799   1.0000
  10.250   0.5278   0.12902   0.11858  -0.0281   0.4744   1.0000
  10.500   0.5104   0.12865   0.11820  -0.0270   0.4622   1.0000
  10.750   0.5380   0.13341   0.12298  -0.0279   0.4567   1.0000
  11.000   0.5285   0.13378   0.12336  -0.0274   0.4454   1.0000
  11.250   0.5629   0.13923   0.12886  -0.0284   0.4406   1.0000
  11.500   0.5442   0.13890   0.12852  -0.0279   0.4300   1.0000
  11.750   0.5762   0.14391   0.13357  -0.0287   0.4239   1.0000
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