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USA 25 AIRFOIL (usa25-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: USA 25 AIRFOIL (usa25-il)
Reynolds number: 1,000,000
Max Cl/Cd: 124.57 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa25-il-1000000.txt
Download as CSV file: xf-usa25-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 25 AIRFOIL                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.3706   0.13249   0.13083  -0.0203   1.0000   0.0135
 -11.500  -0.3695   0.12938   0.12773  -0.0208   1.0000   0.0136
 -11.250  -0.3689   0.12601   0.12437  -0.0212   1.0000   0.0136
 -11.000  -0.3665   0.12271   0.12108  -0.0204   1.0000   0.0139
 -10.750  -0.3636   0.12024   0.11862  -0.0202   1.0000   0.0140
 -10.500  -0.3601   0.11804   0.11644  -0.0199   1.0000   0.0142
 -10.250  -0.3564   0.11603   0.11444  -0.0196   1.0000   0.0146
 -10.000  -0.3440   0.11277   0.11118  -0.0223   0.9993   0.0152
  -9.750  -0.3316   0.10901   0.10742  -0.0255   0.9984   0.0158
  -9.500  -0.3238   0.10381   0.10221  -0.0311   0.9970   0.0171
  -9.250  -0.3128   0.09930   0.09770  -0.0355   0.9957   0.0172
  -8.750  -0.3002   0.08894   0.08735  -0.0438   0.9924   0.0175
  -8.500  -0.2858   0.08595   0.08436  -0.0463   0.9902   0.0177
  -8.250  -0.2681   0.08364   0.08205  -0.0486   0.9883   0.0180
  -8.000  -0.2510   0.08062   0.07902  -0.0525   0.9862   0.0184
  -7.750  -0.2327   0.07728   0.07569  -0.0578   0.9842   0.0192
  -7.500  -0.2218   0.07367   0.07207  -0.0619   0.9792   0.0199
  -7.250  -0.1998   0.06697   0.06531  -0.0728   0.9742   0.0217
  -6.750  -0.1663   0.05405   0.05224  -0.0853   0.9653   0.0223
  -6.500  -0.1411   0.05168   0.04983  -0.0881   0.9609   0.0226
  -6.250  -0.1097   0.04952   0.04763  -0.0918   0.9580   0.0232
  -6.000  -0.0550   0.03091   0.02910  -0.0920   0.9332   0.0252
  -5.750  -0.0335   0.02634   0.02436  -0.0952   0.9191   0.0273
  -5.500  -0.0172   0.02198   0.01983  -0.0967   0.8992   0.0274
  -5.250  -0.0269   0.03004   0.02749  -0.1007   0.9188   0.0285
  -5.000   0.0027   0.02919   0.02654  -0.1019   0.8993   0.0290
  -4.750   0.0211   0.01355   0.01071  -0.0951   0.8104   0.0298
  -4.500   0.0383   0.01218   0.00914  -0.0941   0.7832   0.0312
  -4.250   0.0392   0.01336   0.00865  -0.0955   0.8152   0.0284
  -4.000   0.0606   0.01285   0.00787  -0.0939   0.7852   0.0282
  -3.750   0.0804   0.01230   0.00704  -0.0920   0.7479   0.0281
  -3.500   0.0965   0.01172   0.00610  -0.0894   0.6817   0.0285
  -3.250   0.1108   0.01155   0.00547  -0.0865   0.5884   0.0289
  -3.000   0.1301   0.01138   0.00498  -0.0847   0.5244   0.0290
  -2.750   0.1527   0.01112   0.00451  -0.0835   0.4925   0.0293
  -2.500   0.1766   0.01086   0.00412  -0.0826   0.4743   0.0296
  -2.250   0.2013   0.01060   0.00377  -0.0819   0.4630   0.0299
  -2.000   0.2261   0.01037   0.00346  -0.0811   0.4548   0.0301
  -1.750   0.2512   0.01015   0.00318  -0.0804   0.4483   0.0304
  -1.500   0.2759   0.00999   0.00295  -0.0796   0.4421   0.0306
  -1.250   0.3013   0.00981   0.00274  -0.0790   0.4380   0.0308
  -1.000   0.3264   0.00966   0.00256  -0.0783   0.4334   0.0312
  -0.750   0.3512   0.00956   0.00241  -0.0776   0.4293   0.0318
  -0.500   0.3761   0.00947   0.00228  -0.0768   0.4256   0.0325
  -0.250   0.4016   0.00935   0.00216  -0.0762   0.4230   0.0330
   0.000   0.4269   0.00928   0.00206  -0.0755   0.4201   0.0337
   0.250   0.4521   0.00923   0.00198  -0.0749   0.4166   0.0343
   0.500   0.4767   0.00923   0.00193  -0.0741   0.4126   0.0355
   0.750   0.5021   0.00921   0.00189  -0.0735   0.4095   0.0372
   1.000   0.5278   0.00916   0.00185  -0.0729   0.4069   0.0407
   1.250   0.5524   0.00905   0.00186  -0.0722   0.4040   0.0729
   1.500   0.5775   0.00905   0.00189  -0.0716   0.4008   0.0891
   1.750   0.6023   0.00907   0.00195  -0.0709   0.3974   0.1066
   2.000   0.6273   0.00911   0.00203  -0.0703   0.3947   0.1219
   2.250   0.6532   0.00910   0.00208  -0.0699   0.3927   0.1379
   2.500   0.6790   0.00911   0.00212  -0.0694   0.3900   0.1505
   2.750   0.7047   0.00912   0.00218  -0.0689   0.3869   0.1629
   3.000   0.7298   0.00916   0.00224  -0.0683   0.3836   0.1764
   3.250   0.7544   0.00925   0.00233  -0.0677   0.3794   0.1913
   3.500   0.7801   0.00923   0.00241  -0.0672   0.3773   0.2141
   3.750   0.8055   0.00923   0.00248  -0.0667   0.3750   0.2406
   4.000   0.8304   0.00920   0.00257  -0.0661   0.3724   0.2837
   4.250   0.8291   0.00793   0.00270  -0.0600   0.3705   0.8876
   4.500   0.8900   0.00809   0.00300  -0.0674   0.3643   0.9721
   4.750   0.9412   0.00819   0.00311  -0.0727   0.3567   0.9848
   5.000   0.9817   0.00835   0.00322  -0.0756   0.3471   0.9906
   5.250   1.0192   0.00848   0.00334  -0.0779   0.3387   0.9946
   5.750   1.1049   0.00887   0.00358  -0.0850   0.3031   1.0000
   6.000   1.1206   0.00916   0.00373  -0.0826   0.2746   1.0000
   6.250   1.1321   0.00970   0.00403  -0.0795   0.2314   1.0000
   6.500   1.1426   0.01035   0.00442  -0.0762   0.1894   1.0000
   6.750   1.1554   0.01089   0.00479  -0.0734   0.1600   1.0000
   7.000   1.1689   0.01143   0.00516  -0.0707   0.1310   1.0000
   7.250   1.1685   0.01281   0.00606  -0.0656   0.0531   1.0000
   7.500   1.1764   0.01371   0.00674  -0.0619   0.0179   1.0000
   7.750   1.1941   0.01403   0.00709  -0.0600   0.0156   1.0000
   8.000   1.2115   0.01437   0.00748  -0.0581   0.0147   1.0000
   8.250   1.2276   0.01479   0.00795  -0.0559   0.0137   1.0000
   8.500   1.2410   0.01526   0.00848  -0.0532   0.0127   1.0000
   8.750   1.2522   0.01577   0.00905  -0.0501   0.0122   1.0000
   9.000   1.2667   0.01613   0.00944  -0.0477   0.0117   1.0000
   9.250   1.2799   0.01658   0.00994  -0.0451   0.0113   1.0000
   9.500   1.2926   0.01709   0.01050  -0.0425   0.0109   1.0000
   9.750   1.3049   0.01765   0.01111  -0.0400   0.0105   1.0000
  10.000   1.3163   0.01827   0.01178  -0.0373   0.0102   1.0000
  10.250   1.3256   0.01902   0.01259  -0.0345   0.0098   1.0000
  10.500   1.3314   0.01997   0.01362  -0.0312   0.0095   1.0000
  10.750   1.3247   0.02164   0.01542  -0.0264   0.0090   1.0000
  11.000   1.3313   0.02264   0.01649  -0.0237   0.0090   1.0000
  11.250   1.3446   0.02329   0.01719  -0.0220   0.0088   1.0000
  11.500   1.3522   0.02431   0.01829  -0.0198   0.0086   1.0000
  11.750   1.3585   0.02548   0.01953  -0.0176   0.0084   1.0000
  12.000   1.3634   0.02682   0.02094  -0.0155   0.0083   1.0000
  12.250   1.3655   0.02846   0.02266  -0.0134   0.0081   1.0000
  12.500   1.3718   0.02990   0.02416  -0.0120   0.0077   1.0000
  12.750   1.3724   0.03191   0.02626  -0.0104   0.0076   1.0000
  13.000   1.3731   0.03406   0.02850  -0.0092   0.0075   1.0000
  13.250   1.3713   0.03662   0.03114  -0.0083   0.0073   1.0000
  13.500   1.3702   0.03929   0.03389  -0.0077   0.0072   1.0000
  13.750   1.3691   0.04216   0.03683  -0.0076   0.0070   1.0000
  14.000   1.3632   0.04573   0.04050  -0.0077   0.0070   1.0000
  14.250   1.3592   0.04925   0.04412  -0.0080   0.0070   1.0000
  14.500   1.3500   0.05346   0.04841  -0.0086   0.0068   1.0000
  14.750   1.3464   0.05704   0.05207  -0.0091   0.0068   1.0000
  15.000   1.3359   0.06128   0.05638  -0.0094   0.0067   1.0000
  15.250   1.3267   0.06504   0.06018  -0.0092   0.0066   1.0000
  15.500   1.3223   0.06814   0.06334  -0.0086   0.0065   1.0000
  15.750   1.3216   0.07156   0.06686  -0.0095   0.0064   1.0000
  16.000   1.3206   0.07498   0.07036  -0.0103   0.0064   1.0000
  16.250   1.3194   0.07791   0.07336  -0.0101   0.0064   1.0000
  16.500   1.3182   0.08135   0.07688  -0.0110   0.0063   1.0000
  16.750   1.3157   0.08494   0.08056  -0.0118   0.0063   1.0000
  17.000   1.3127   0.08898   0.08471  -0.0134   0.0061   1.0000
  17.250   1.3108   0.09228   0.08808  -0.0138   0.0061   1.0000
  17.500   1.3080   0.09599   0.09187  -0.0148   0.0061   1.0000
  17.750   1.3054   0.09950   0.09547  -0.0154   0.0060   1.0000
  18.000   1.3014   0.10359   0.09965  -0.0168   0.0059   1.0000
  18.250   1.2994   0.10680   0.10296  -0.0170   0.0060   1.0000
  18.500   1.2941   0.11116   0.10741  -0.0187   0.0059   1.0000
  18.750   1.2889   0.11549   0.11185  -0.0203   0.0058   1.0000
  19.000   1.2844   0.11959   0.11605  -0.0216   0.0058   1.0000
  19.250   1.2779   0.12438   0.12094  -0.0237   0.0057   1.0000
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