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USA 27 AIRFOIL (usa27-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: USA 27 AIRFOIL (usa27-il)
Reynolds number: 100,000
Max Cl/Cd: 52.81 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa27-il-100000-n5.txt
Download as CSV file: xf-usa27-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 27 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3236   0.10794   0.10333  -0.0314   1.0000   0.0613
  -8.500  -0.3459   0.10714   0.10265  -0.0309   1.0000   0.0622
  -8.250  -0.3658   0.10589   0.10151  -0.0314   0.9986   0.0625
  -8.000  -0.3570   0.10083   0.09646  -0.0361   0.9936   0.0634
  -7.750  -0.3334   0.09688   0.09249  -0.0332   0.9931   0.0653
  -7.500  -0.3196   0.09342   0.08903  -0.0357   0.9880   0.0674
  -7.250  -0.3064   0.08959   0.08519  -0.0405   0.9815   0.0702
  -7.000  -0.2918   0.08455   0.07997  -0.0578   0.9674   0.0750
  -6.750  -0.2774   0.07967   0.07516  -0.0570   0.9643   0.0764
  -6.500  -0.2582   0.07684   0.07233  -0.0561   0.9610   0.0794
  -6.250  -0.2425   0.07359   0.06904  -0.0587   0.9530   0.0835
  -6.000  -0.2236   0.06839   0.06358  -0.0683   0.9422   0.0896
  -5.500  -0.1816   0.06175   0.05691  -0.0703   0.9320   0.0932
  -5.000  -0.1371   0.04455   0.03851  -0.0787   0.9142   0.0530
  -4.750  -0.1116   0.04150   0.03523  -0.0797   0.9075   0.0511
  -4.500  -0.0832   0.03816   0.03159  -0.0811   0.9012   0.0500
  -4.250  -0.0573   0.03506   0.02808  -0.0815   0.8920   0.0491
  -4.000  -0.0287   0.03235   0.02490  -0.0819   0.8833   0.0492
  -3.750   0.0042   0.03005   0.02212  -0.0829   0.8757   0.0501
  -3.500   0.0314   0.02824   0.01995  -0.0826   0.8658   0.0500
  -3.250   0.0662   0.02643   0.01777  -0.0837   0.8593   0.0497
  -3.000   0.0927   0.02513   0.01618  -0.0831   0.8485   0.0495
  -2.750   0.1274   0.02378   0.01455  -0.0840   0.8411   0.0495
  -2.500   0.1560   0.02275   0.01331  -0.0837   0.8300   0.0496
  -2.250   0.1850   0.02184   0.01224  -0.0836   0.8187   0.0499
  -2.000   0.2176   0.02103   0.01126  -0.0841   0.8084   0.0511
  -1.750   0.2489   0.02031   0.01042  -0.0844   0.7968   0.0525
  -1.500   0.2765   0.01956   0.00966  -0.0841   0.7831   0.0535
  -1.250   0.3049   0.01895   0.00902  -0.0839   0.7689   0.0542
  -1.000   0.3334   0.01844   0.00844  -0.0837   0.7541   0.0550
  -0.750   0.3621   0.01801   0.00793  -0.0836   0.7387   0.0561
  -0.500   0.3912   0.01765   0.00746  -0.0835   0.7226   0.0576
  -0.250   0.4208   0.01735   0.00704  -0.0835   0.7063   0.0595
   0.000   0.4508   0.01713   0.00666  -0.0835   0.6901   0.0621
   0.250   0.4808   0.01688   0.00633  -0.0836   0.6741   0.0690
   0.500   0.5104   0.01668   0.00606  -0.0837   0.6583   0.0841
   0.750   0.5372   0.01626   0.00610  -0.0836   0.6430   0.2506
   1.000   0.5627   0.01613   0.00610  -0.0831   0.6281   0.3450
   1.250   0.5823   0.01539   0.00605  -0.0815   0.6145   0.5652
   1.750   0.7124   0.01543   0.00633  -0.0965   0.5793   1.0000
   2.250   0.7560   0.01587   0.00652  -0.0941   0.5514   1.0000
   2.500   0.7777   0.01610   0.00663  -0.0928   0.5386   1.0000
   2.750   0.7995   0.01634   0.00674  -0.0916   0.5266   1.0000
   3.000   0.8208   0.01659   0.00689  -0.0903   0.5142   1.0000
   3.250   0.8417   0.01684   0.00705  -0.0890   0.5017   1.0000
   3.500   0.8627   0.01710   0.00722  -0.0876   0.4901   1.0000
   3.750   0.8837   0.01737   0.00739  -0.0863   0.4796   1.0000
   4.000   0.9045   0.01766   0.00760  -0.0850   0.4690   1.0000
   4.250   0.9254   0.01795   0.00784  -0.0837   0.4592   1.0000
   4.500   0.9464   0.01827   0.00806  -0.0824   0.4503   1.0000
   4.750   0.9670   0.01858   0.00836  -0.0811   0.4407   1.0000
   5.000   0.9881   0.01892   0.00863  -0.0799   0.4326   1.0000
   5.250   1.0088   0.01925   0.00896  -0.0787   0.4241   1.0000
   5.500   1.0298   0.01961   0.00929  -0.0775   0.4164   1.0000
   5.750   1.0503   0.01996   0.00965  -0.0762   0.4084   1.0000
   6.000   1.0716   0.02034   0.01000  -0.0751   0.4017   1.0000
   6.250   1.0923   0.02070   0.01045  -0.0740   0.3946   1.0000
   6.500   1.1137   0.02109   0.01082  -0.0729   0.3885   1.0000
   6.750   1.1337   0.02148   0.01130  -0.0717   0.3815   1.0000
   7.000   1.1539   0.02187   0.01173  -0.0704   0.3746   1.0000
   7.250   1.1739   0.02229   0.01222  -0.0692   0.3679   1.0000
   7.500   1.1931   0.02270   0.01272  -0.0678   0.3607   1.0000
   7.750   1.2133   0.02313   0.01317  -0.0666   0.3546   1.0000
   8.000   1.2299   0.02355   0.01373  -0.0648   0.3458   1.0000
   8.250   1.2440   0.02395   0.01419  -0.0626   0.3347   1.0000
   8.500   1.2559   0.02435   0.01461  -0.0600   0.3222   1.0000
   8.750   1.2671   0.02479   0.01512  -0.0574   0.3099   1.0000
   9.000   1.2781   0.02527   0.01570  -0.0547   0.2982   1.0000
   9.250   1.2865   0.02580   0.01629  -0.0517   0.2839   1.0000
   9.500   1.2938   0.02642   0.01697  -0.0488   0.2673   1.0000
   9.750   1.3030   0.02712   0.01772  -0.0462   0.2525   1.0000
  10.000   1.3115   0.02792   0.01855  -0.0437   0.2372   1.0000
  10.250   1.3176   0.02888   0.01951  -0.0411   0.2199   1.0000
  10.500   1.3192   0.03018   0.02070  -0.0382   0.1980   1.0000
  10.750   1.3192   0.03171   0.02214  -0.0354   0.1813   1.0000
  11.000   1.3218   0.03324   0.02369  -0.0330   0.1693   1.0000
  11.250   1.3238   0.03489   0.02538  -0.0308   0.1582   1.0000
  11.500   1.3229   0.03688   0.02738  -0.0287   0.1419   1.0000
  11.750   1.3225   0.03895   0.02948  -0.0269   0.1225   1.0000
  12.250   1.2844   0.04696   0.03702  -0.0230   0.0443   1.0000
  12.500   1.2657   0.05149   0.04148  -0.0221   0.0348   1.0000
  12.750   1.2537   0.05563   0.04569  -0.0217   0.0313   1.0000
  13.000   1.2444   0.05969   0.04989  -0.0217   0.0294   1.0000
  13.250   1.2360   0.06380   0.05417  -0.0219   0.0282   1.0000
  13.500   1.2272   0.06815   0.05868  -0.0224   0.0274   1.0000
  13.750   1.2173   0.07278   0.06349  -0.0232   0.0268   1.0000
  14.000   1.2064   0.07770   0.06860  -0.0241   0.0263   1.0000
  14.250   1.1951   0.08285   0.07391  -0.0253   0.0258   1.0000
  14.500   1.1835   0.08816   0.07939  -0.0267   0.0255   1.0000
  14.750   1.1716   0.09364   0.08503  -0.0282   0.0251   1.0000
  15.000   1.1594   0.09927   0.09083  -0.0299   0.0248   1.0000
  15.250   1.1472   0.10502   0.09674  -0.0318   0.0245   1.0000
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