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USA 27 AIRFOIL (usa27-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: USA 27 AIRFOIL (usa27-il)
Reynolds number: 50,000
Max Cl/Cd: 35.51 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa27-il-50000-n5.txt
Download as CSV file: xf-usa27-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3482   0.10415   0.09809  -0.0229   1.0000   0.1425
  -7.250  -0.3747   0.10384   0.09793  -0.0218   1.0000   0.1454
  -7.000  -0.4003   0.10354   0.09774  -0.0234   1.0000   0.1467
  -6.750  -0.3891   0.09880   0.09306  -0.0197   1.0000   0.1487
  -6.500  -0.3866   0.09597   0.09028  -0.0172   1.0000   0.1515
  -6.250  -0.3903   0.09372   0.08809  -0.0159   1.0000   0.1551
  -6.000  -0.3862   0.09112   0.08544  -0.0243   0.9938   0.1631
  -5.750  -0.3647   0.08668   0.08101  -0.0228   0.9892   0.1682
  -5.500  -0.3428   0.08309   0.07731  -0.0310   0.9791   0.1797
  -5.000  -0.2757   0.06673   0.06019  -0.0485   0.9629   0.0861
  -4.750  -0.2445   0.05949   0.05229  -0.0551   0.9531   0.0752
  -4.500  -0.2167   0.05596   0.04854  -0.0576   0.9455   0.0746
  -4.250  -0.1874   0.05224   0.04446  -0.0603   0.9369   0.0746
  -4.000  -0.1596   0.04905   0.04096  -0.0621   0.9278   0.0742
  -3.750  -0.1256   0.04588   0.03744  -0.0647   0.9202   0.0731
  -3.500  -0.0970   0.04310   0.03428  -0.0659   0.9095   0.0721
  -3.250  -0.0610   0.04034   0.03104  -0.0680   0.9010   0.0713
  -3.000  -0.0266   0.03801   0.02823  -0.0694   0.8909   0.0708
  -2.750   0.0054   0.03616   0.02592  -0.0702   0.8797   0.0717
  -2.500   0.0444   0.03445   0.02370  -0.0720   0.8712   0.0736
  -2.250   0.0787   0.03308   0.02194  -0.0728   0.8605   0.0745
  -2.000   0.1110   0.03192   0.02047  -0.0733   0.8491   0.0749
  -1.750   0.1550   0.03049   0.01882  -0.0756   0.8425   0.0758
  -1.500   0.1867   0.02958   0.01778  -0.0759   0.8302   0.0771
  -1.250   0.2215   0.02878   0.01682  -0.0766   0.8189   0.0790
  -1.000   0.2635   0.02786   0.01575  -0.0786   0.8108   0.0829
  -0.750   0.2937   0.02732   0.01506  -0.0785   0.7980   0.0881
  -0.500   0.3229   0.02674   0.01448  -0.0783   0.7850   0.0941
  -0.250   0.3529   0.02622   0.01391  -0.0782   0.7725   0.1016
   0.000   0.3841   0.02556   0.01341  -0.0783   0.7606   0.1198
   0.250   0.4150   0.02472   0.01316  -0.0785   0.7493   0.2685
   0.500   0.4398   0.02407   0.01286  -0.0777   0.7353   0.4002
   0.750   0.5206   0.02262   0.01245  -0.0871   0.7219   1.0000
   1.000   0.5488   0.02260   0.01216  -0.0866   0.7073   1.0000
   1.250   0.5773   0.02260   0.01190  -0.0863   0.6929   1.0000
   1.500   0.6060   0.02262   0.01168  -0.0860   0.6786   1.0000
   1.750   0.6346   0.02269   0.01151  -0.0857   0.6644   1.0000
   2.000   0.6630   0.02280   0.01141  -0.0855   0.6505   1.0000
   2.250   0.6913   0.02296   0.01136  -0.0853   0.6371   1.0000
   2.500   0.7201   0.02315   0.01134  -0.0851   0.6241   1.0000
   2.750   0.7440   0.02349   0.01156  -0.0843   0.6103   1.0000
   3.000   0.7672   0.02387   0.01183  -0.0834   0.5971   1.0000
   3.250   0.7911   0.02427   0.01214  -0.0827   0.5849   1.0000
   3.500   0.8168   0.02462   0.01238  -0.0822   0.5737   1.0000
   3.750   0.8395   0.02506   0.01276  -0.0813   0.5623   1.0000
   4.000   0.8605   0.02557   0.01325  -0.0802   0.5513   1.0000
   4.250   0.8858   0.02597   0.01358  -0.0797   0.5420   1.0000
   4.500   0.9066   0.02649   0.01411  -0.0786   0.5318   1.0000
   4.750   0.9280   0.02702   0.01465  -0.0776   0.5226   1.0000
   5.000   0.9523   0.02746   0.01506  -0.0769   0.5142   1.0000
   5.250   0.9709   0.02807   0.01572  -0.0755   0.5046   1.0000
   5.500   0.9957   0.02842   0.01602  -0.0749   0.4959   1.0000
   5.750   1.0133   0.02898   0.01665  -0.0733   0.4854   1.0000
   6.000   1.0322   0.02947   0.01716  -0.0718   0.4750   1.0000
   6.250   1.0555   0.02977   0.01740  -0.0708   0.4650   1.0000
   6.500   1.0718   0.03032   0.01805  -0.0690   0.4540   1.0000
   6.750   1.0899   0.03090   0.01868  -0.0675   0.4443   1.0000
   7.000   1.1132   0.03135   0.01914  -0.0667   0.4362   1.0000
   7.250   1.1281   0.03215   0.02008  -0.0649   0.4273   1.0000
   7.500   1.1533   0.03257   0.02052  -0.0644   0.4196   1.0000
   7.750   1.1647   0.03351   0.02165  -0.0621   0.4105   1.0000
   8.000   1.1894   0.03399   0.02215  -0.0616   0.4030   1.0000
   8.250   1.1990   0.03503   0.02341  -0.0592   0.3940   1.0000
   8.500   1.2208   0.03561   0.02407  -0.0583   0.3861   1.0000
   8.750   1.2303   0.03663   0.02530  -0.0559   0.3768   1.0000
   9.000   1.2468   0.03740   0.02617  -0.0543   0.3684   1.0000
   9.250   1.2583   0.03834   0.02728  -0.0522   0.3594   1.0000
   9.500   1.2696   0.03937   0.02846  -0.0501   0.3511   1.0000
   9.750   1.2825   0.04019   0.02944  -0.0481   0.3422   1.0000
  10.000   1.2826   0.04141   0.03084  -0.0446   0.3326   1.0000
  10.250   1.2919   0.04189   0.03134  -0.0419   0.3217   1.0000
  10.500   1.2892   0.04306   0.03264  -0.0383   0.3109   1.0000
  10.750   1.2832   0.04459   0.03432  -0.0348   0.3003   1.0000
  11.000   1.2837   0.04568   0.03548  -0.0321   0.2897   1.0000
  11.250   1.2798   0.04728   0.03719  -0.0294   0.2794   1.0000
  11.500   1.2697   0.04984   0.03996  -0.0270   0.2702   1.0000
  11.750   1.2726   0.05132   0.04152  -0.0253   0.2619   1.0000
  12.000   1.2604   0.05470   0.04513  -0.0238   0.2541   1.0000
  12.250   1.2569   0.05712   0.04766  -0.0226   0.2459   1.0000
  12.500   1.2472   0.06043   0.05113  -0.0218   0.2372   1.0000
  12.750   1.2337   0.06461   0.05547  -0.0216   0.2292   1.0000
  13.000   1.2310   0.06727   0.05818  -0.0212   0.2199   1.0000
  13.250   1.2108   0.07308   0.06422  -0.0220   0.2136   1.0000
  13.500   1.2148   0.07511   0.06631  -0.0217   0.2065   1.0000
  13.750   1.1903   0.08208   0.07349  -0.0233   0.2011   1.0000
  14.000   1.1937   0.08415   0.07558  -0.0232   0.1917   1.0000
  14.250   1.1717   0.09111   0.08273  -0.0251   0.1863   1.0000
  14.500   1.1735   0.09353   0.08520  -0.0253   0.1758   1.0000
  14.750   1.1575   0.09965   0.09149  -0.0272   0.1699   1.0000
  15.000   1.1563   0.10290   0.09480  -0.0279   0.1607   1.0000
  15.250   1.1424   0.10879   0.10083  -0.0299   0.1527   1.0000
  15.500   1.1295   0.11465   0.10680  -0.0320   0.1446   1.0000
  15.750   1.1190   0.12021   0.11250  -0.0341   0.1361   1.0000
  16.000   1.0989   0.12810   0.12053  -0.0375   0.1302   1.0000
  16.250   1.0873   0.13426   0.12680  -0.0402   0.1205   1.0000
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