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USA 27 AIRFOIL (usa27-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: USA 27 AIRFOIL (usa27-il)
Reynolds number: 100,000
Max Cl/Cd: 50.46 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa27-il-100000.txt
Download as CSV file: xf-usa27-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.750  -0.3966   0.09458   0.09054  -0.0161   1.0000   0.0968
  -6.500  -0.4091   0.09274   0.08874  -0.0171   1.0000   0.0997
  -6.250  -0.4262   0.09175   0.08766  -0.0245   1.0000   0.1019
  -6.000  -0.4228   0.08724   0.08330  -0.0189   1.0000   0.1033
  -5.750  -0.4209   0.08490   0.08102  -0.0153   1.0000   0.1056
  -5.500  -0.3875   0.08087   0.07675  -0.0286   0.9917   0.1168
  -5.250  -0.3648   0.07686   0.07285  -0.0269   0.9863   0.1210
  -5.000  -0.3260   0.07242   0.06819  -0.0370   0.9754   0.1327
  -4.750  -0.2893   0.06938   0.06503  -0.0420   0.9653   0.1445
  -4.500  -0.2548   0.06477   0.06040  -0.0460   0.9582   0.1512
  -4.250  -0.2213   0.06133   0.05679  -0.0511   0.9464   0.1646
  -4.000  -0.1893   0.05835   0.05369  -0.0546   0.9356   0.1799
  -3.750  -0.1483   0.05502   0.05025  -0.0591   0.9294   0.1966
  -3.500  -0.1201   0.05241   0.04751  -0.0611   0.9176   0.2122
  -3.250  -0.0900   0.04978   0.04479  -0.0630   0.9073   0.2288
  -3.000  -0.0505   0.04681   0.04174  -0.0662   0.9008   0.2480
  -2.750  -0.0202   0.04521   0.03990  -0.0679   0.8890   0.2744
  -2.500   0.0514   0.03457   0.02759  -0.0766   0.8859   0.1243
  -2.250   0.0883   0.03098   0.02284  -0.0766   0.8763   0.1011
  -2.000   0.1346   0.02841   0.02001  -0.0794   0.8711   0.0966
  -1.750   0.1695   0.02684   0.01809  -0.0799   0.8610   0.0932
  -1.500   0.2182   0.02517   0.01611  -0.0827   0.8559   0.0913
  -1.250   0.2535   0.02408   0.01494  -0.0834   0.8457   0.0928
  -1.000   0.3001   0.02275   0.01357  -0.0860   0.8401   0.0963
  -0.750   0.3323   0.02188   0.01267  -0.0860   0.8285   0.0979
  -0.500   0.3787   0.02066   0.01140  -0.0883   0.8228   0.1012
  -0.250   0.4085   0.01995   0.01073  -0.0879   0.8096   0.1066
   0.000   0.4412   0.01932   0.01012  -0.0880   0.7967   0.1190
   0.250   0.4749   0.01836   0.00976  -0.0884   0.7839   0.2666
   0.500   0.6026   0.01597   0.00890  -0.1072   0.7726   1.0000
   0.750   0.6299   0.01586   0.00857  -0.1065   0.7545   1.0000
   1.000   0.6576   0.01579   0.00826  -0.1059   0.7360   1.0000
   1.250   0.6859   0.01574   0.00798  -0.1054   0.7175   1.0000
   1.500   0.7144   0.01575   0.00774  -0.1050   0.6991   1.0000
   1.750   0.7380   0.01593   0.00773  -0.1039   0.6791   1.0000
   2.000   0.7631   0.01617   0.00776  -0.1031   0.6606   1.0000
   2.250   0.7881   0.01647   0.00787  -0.1023   0.6435   1.0000
   2.500   0.8123   0.01684   0.00807  -0.1015   0.6275   1.0000
   2.750   0.8358   0.01724   0.00833  -0.1005   0.6124   1.0000
   3.000   0.8589   0.01765   0.00860  -0.0995   0.5983   1.0000
   3.250   0.8825   0.01805   0.00888  -0.0986   0.5855   1.0000
   3.500   0.9062   0.01843   0.00915  -0.0978   0.5737   1.0000
   3.750   0.9257   0.01883   0.00953  -0.0962   0.5613   1.0000
   4.000   0.9467   0.01920   0.00985  -0.0948   0.5497   1.0000
   4.250   0.9704   0.01953   0.01007  -0.0939   0.5395   1.0000
   4.500   0.9904   0.01989   0.01043  -0.0925   0.5289   1.0000
   4.750   1.0111   0.02027   0.01081  -0.0911   0.5191   1.0000
   5.000   1.0361   0.02056   0.01099  -0.0905   0.5102   1.0000
   5.250   1.0536   0.02098   0.01150  -0.0886   0.5003   1.0000
   5.500   1.0778   0.02136   0.01182  -0.0880   0.4927   1.0000
   5.750   1.0972   0.02181   0.01234  -0.0864   0.4840   1.0000
   6.000   1.1204   0.02223   0.01276  -0.0856   0.4763   1.0000
   6.250   1.1404   0.02267   0.01324  -0.0842   0.4676   1.0000
   6.500   1.1622   0.02314   0.01373  -0.0832   0.4595   1.0000
   6.750   1.1838   0.02357   0.01421  -0.0821   0.4510   1.0000
   7.000   1.2037   0.02412   0.01484  -0.0808   0.4428   1.0000
   7.250   1.2271   0.02457   0.01529  -0.0800   0.4344   1.0000
   7.500   1.2444   0.02518   0.01603  -0.0783   0.4255   1.0000
   7.750   1.2709   0.02561   0.01639  -0.0780   0.4164   1.0000
   8.000   1.2848   0.02602   0.01693  -0.0756   0.4044   1.0000
   8.250   1.3000   0.02631   0.01727  -0.0733   0.3910   1.0000
   8.500   1.3148   0.02652   0.01749  -0.0709   0.3770   1.0000
   8.750   1.3298   0.02678   0.01776  -0.0686   0.3638   1.0000
   9.000   1.3472   0.02709   0.01808  -0.0668   0.3520   1.0000
   9.250   1.3614   0.02735   0.01836  -0.0645   0.3395   1.0000
   9.500   1.3687   0.02766   0.01881  -0.0610   0.3265   1.0000
   9.750   1.3777   0.02808   0.01934  -0.0580   0.3147   1.0000
  10.000   1.3874   0.02847   0.01982  -0.0551   0.3036   1.0000
  10.250   1.3944   0.02877   0.02014  -0.0517   0.2922   1.0000
  10.500   1.3930   0.02919   0.02068  -0.0471   0.2797   1.0000
  10.750   1.3943   0.02979   0.02141  -0.0432   0.2675   1.0000
  11.000   1.3979   0.03049   0.02223  -0.0399   0.2562   1.0000
  11.250   1.3996   0.03132   0.02314  -0.0366   0.2434   1.0000
  11.500   1.4015   0.03233   0.02424  -0.0336   0.2308   1.0000
  11.750   1.4027   0.03354   0.02552  -0.0309   0.2179   1.0000
  12.000   1.4007   0.03510   0.02710  -0.0282   0.2022   1.0000
  12.250   1.3975   0.03697   0.02898  -0.0257   0.1878   1.0000
  12.500   1.3930   0.03916   0.03117  -0.0235   0.1746   1.0000
  12.750   1.3856   0.04181   0.03383  -0.0216   0.1602   1.0000
  13.000   1.3785   0.04469   0.03678  -0.0201   0.1454   1.0000
  13.500   1.3551   0.05217   0.04430  -0.0184   0.0968   1.0000
  13.750   1.3348   0.05733   0.04937  -0.0184   0.0803   1.0000
  14.000   1.3152   0.06273   0.05476  -0.0189   0.0694   1.0000
  14.250   1.2967   0.06827   0.06034  -0.0196   0.0627   1.0000
  14.500   1.2792   0.07391   0.06606  -0.0206   0.0586   1.0000
  14.750   1.2620   0.07971   0.07194  -0.0219   0.0559   1.0000
  15.000   1.2467   0.08541   0.07775  -0.0233   0.0540   1.0000
  15.250   1.2325   0.09106   0.08354  -0.0247   0.0524   1.0000
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