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USA 25 AIRFOIL (usa25-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: USA 25 AIRFOIL (usa25-il)
Reynolds number: 500,000
Max Cl/Cd: 97.33 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa25-il-500000-n5.txt
Download as CSV file: xf-usa25-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2818   0.08842   0.08614  -0.0460   0.9869   0.0144
  -8.500  -0.2722   0.08405   0.08177  -0.0504   0.9844   0.0153
  -8.000  -0.2692   0.07241   0.07014  -0.0623   0.9737   0.0167
  -7.750  -0.2558   0.07038   0.06810  -0.0640   0.9676   0.0169
  -7.500  -0.2358   0.06738   0.06507  -0.0681   0.9638   0.0173
  -7.250  -0.2209   0.06434   0.06200  -0.0709   0.9577   0.0178
  -7.000  -0.2029   0.06065   0.05826  -0.0748   0.9512   0.0188
  -6.750  -0.1888   0.05508   0.05259  -0.0794   0.9429   0.0198
  -6.250  -0.1476   0.04494   0.04217  -0.0875   0.9225   0.0219
  -6.000  -0.1175   0.04205   0.03916  -0.0909   0.9069   0.0224
  -5.500  -0.0921   0.02022   0.01584  -0.0954   0.8654   0.0251
  -5.250  -0.0651   0.01797   0.01308  -0.0959   0.8407   0.0254
  -5.000  -0.0405   0.01674   0.01145  -0.0954   0.8151   0.0257
  -4.750  -0.0177   0.01588   0.01027  -0.0945   0.7898   0.0259
  -4.500   0.0043   0.01521   0.00930  -0.0932   0.7611   0.0261
  -4.250   0.0247   0.01474   0.00850  -0.0916   0.7184   0.0263
  -4.000   0.0416   0.01462   0.00797  -0.0891   0.6486   0.0265
  -3.750   0.0592   0.01466   0.00762  -0.0869   0.5805   0.0267
  -3.500   0.0794   0.01446   0.00710  -0.0853   0.5325   0.0269
  -3.250   0.1012   0.01381   0.00617  -0.0841   0.5043   0.0271
  -3.000   0.1244   0.01329   0.00547  -0.0831   0.4861   0.0273
  -2.750   0.1482   0.01282   0.00485  -0.0822   0.4732   0.0278
  -2.500   0.1726   0.01250   0.00443  -0.0815   0.4631   0.0282
  -2.250   0.1972   0.01222   0.00408  -0.0808   0.4556   0.0286
  -2.000   0.2220   0.01199   0.00380  -0.0800   0.4489   0.0290
  -1.750   0.2467   0.01181   0.00356  -0.0793   0.4432   0.0294
  -1.500   0.2718   0.01164   0.00334  -0.0787   0.4380   0.0297
  -1.250   0.2968   0.01151   0.00317  -0.0780   0.4332   0.0301
  -1.000   0.3215   0.01140   0.00301  -0.0773   0.4292   0.0305
  -0.750   0.3467   0.01130   0.00288  -0.0766   0.4260   0.0309
  -0.500   0.3720   0.01120   0.00276  -0.0760   0.4228   0.0317
  -0.250   0.3971   0.01113   0.00266  -0.0753   0.4196   0.0324
   0.000   0.4220   0.01109   0.00258  -0.0747   0.4164   0.0329
   0.250   0.4468   0.01107   0.00252  -0.0740   0.4132   0.0333
   0.500   0.4721   0.01104   0.00246  -0.0733   0.4107   0.0339
   1.000   0.5226   0.01098   0.00239  -0.0721   0.4057   0.0369
   1.250   0.5474   0.01096   0.00238  -0.0714   0.4021   0.0411
   1.500   0.5714   0.01091   0.00241  -0.0706   0.3989   0.0725
   1.750   0.5963   0.01095   0.00246  -0.0700   0.3959   0.0818
   2.250   0.6468   0.01093   0.00257  -0.0689   0.3898   0.1076
   2.500   0.6716   0.01095   0.00266  -0.0683   0.3864   0.1294
   2.750   0.6963   0.01100   0.00274  -0.0676   0.3831   0.1449
   3.000   0.7212   0.01107   0.00282  -0.0670   0.3802   0.1566
   3.250   0.7467   0.01109   0.00290  -0.0665   0.3772   0.1680
   3.500   0.7718   0.01112   0.00300  -0.0660   0.3739   0.1842
   3.750   0.7964   0.01115   0.00310  -0.0653   0.3699   0.2076
   4.000   0.8205   0.01122   0.00321  -0.0646   0.3663   0.2295
   4.250   0.8454   0.01124   0.00333  -0.0640   0.3635   0.2556
   4.500   0.8685   0.01111   0.00345  -0.0632   0.3605   0.3682
   4.750   0.8990   0.01007   0.00376  -0.0639   0.3567   0.9527
   5.000   0.9571   0.01032   0.00401  -0.0708   0.3499   0.9799
   5.250   1.0041   0.01050   0.00416  -0.0752   0.3362   0.9937
   5.500   1.0395   0.01068   0.00429  -0.0771   0.3168   0.9989
   5.750   1.0631   0.01094   0.00442  -0.0765   0.2882   1.0000
   6.000   1.0781   0.01136   0.00464  -0.0741   0.2525   1.0000
   6.250   1.0905   0.01202   0.00503  -0.0713   0.2077   1.0000
   6.500   1.1043   0.01264   0.00546  -0.0688   0.1762   1.0000
   6.750   1.1202   0.01312   0.00584  -0.0667   0.1552   1.0000
   7.000   1.1359   0.01363   0.00623  -0.0645   0.1340   1.0000
   7.250   1.1388   0.01494   0.00709  -0.0603   0.0622   1.0000
   7.750   1.1596   0.01644   0.00836  -0.0541   0.0159   1.0000
   8.000   1.1738   0.01685   0.00883  -0.0515   0.0138   1.0000
   8.250   1.1886   0.01722   0.00926  -0.0492   0.0132   1.0000
   8.500   1.2026   0.01764   0.00974  -0.0467   0.0123   1.0000
   8.750   1.2158   0.01814   0.01030  -0.0442   0.0113   1.0000
   9.000   1.2283   0.01869   0.01092  -0.0417   0.0107   1.0000
   9.250   1.2384   0.01939   0.01171  -0.0388   0.0099   1.0000
   9.500   1.2515   0.01995   0.01234  -0.0365   0.0096   1.0000
   9.750   1.2635   0.02058   0.01305  -0.0341   0.0093   1.0000
  10.000   1.2745   0.02127   0.01381  -0.0317   0.0090   1.0000
  10.250   1.2844   0.02205   0.01466  -0.0292   0.0085   1.0000
  10.500   1.2938   0.02288   0.01556  -0.0268   0.0083   1.0000
  10.750   1.3013   0.02383   0.01658  -0.0243   0.0078   1.0000
  11.000   1.3075   0.02491   0.01774  -0.0218   0.0075   1.0000
  11.250   1.3107   0.02623   0.01914  -0.0191   0.0074   1.0000
  11.500   1.3104   0.02787   0.02088  -0.0164   0.0071   1.0000
  11.750   1.3151   0.02928   0.02237  -0.0144   0.0069   1.0000
  12.000   1.3165   0.03103   0.02423  -0.0125   0.0068   1.0000
  12.250   1.3187   0.03285   0.02615  -0.0109   0.0066   1.0000
  12.500   1.3176   0.03512   0.02852  -0.0095   0.0065   1.0000
  12.750   1.3169   0.03752   0.03103  -0.0085   0.0063   1.0000
  13.000   1.3145   0.04028   0.03390  -0.0079   0.0062   1.0000
  13.250   1.3106   0.04343   0.03717  -0.0077   0.0061   1.0000
  13.500   1.3062   0.04688   0.04073  -0.0079   0.0060   1.0000
  13.750   1.3024   0.05042   0.04438  -0.0083   0.0059   1.0000
  14.000   1.2983   0.05412   0.04818  -0.0090   0.0058   1.0000
  14.250   1.2937   0.05795   0.05211  -0.0097   0.0057   1.0000
  14.500   1.2870   0.06207   0.05633  -0.0105   0.0057   1.0000
  14.750   1.2811   0.06608   0.06043  -0.0113   0.0056   1.0000
  15.000   1.2779   0.06977   0.06421  -0.0122   0.0054   1.0000
  15.250   1.2715   0.07386   0.06838  -0.0131   0.0054   1.0000
  15.500   1.2648   0.07797   0.07258  -0.0139   0.0054   1.0000
  15.750   1.2604   0.08188   0.07656  -0.0149   0.0053   1.0000
  16.000   1.2549   0.08596   0.08071  -0.0159   0.0052   1.0000
  16.250   1.2489   0.09012   0.08494  -0.0169   0.0051   1.0000
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