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USA 25 AIRFOIL (usa25-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: USA 25 AIRFOIL (usa25-il)
Reynolds number: 1,000,000
Max Cl/Cd: 106.57 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa25-il-1000000-n5.txt
Download as CSV file: xf-usa25-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.4116   0.15845   0.15671  -0.0157   1.0000   0.0045
 -14.000  -0.4115   0.15389   0.15216  -0.0165   1.0000   0.0051
 -13.750  -0.4124   0.14917   0.14745  -0.0174   1.0000   0.0053
  -9.750  -0.2952   0.09099   0.08930  -0.0516   0.9866   0.0104
  -8.750  -0.2702   0.07411   0.07242  -0.0667   0.9743   0.0131
  -8.500  -0.2673   0.07115   0.06947  -0.0692   0.9669   0.0132
  -8.000  -0.2337   0.06426   0.06253  -0.0784   0.9564   0.0140
  -7.500  -0.2076   0.04785   0.04586  -0.0956   0.9402   0.0168
  -7.250  -0.2533   0.02162   0.01852  -0.1006   0.9227   0.0197
  -7.000  -0.2305   0.01859   0.01506  -0.1010   0.9069   0.0201
  -6.750  -0.2024   0.01727   0.01340  -0.1016   0.8715   0.0204
  -6.500  -0.1821   0.01663   0.01236  -0.1002   0.8206   0.0206
  -6.250  -0.1627   0.01629   0.01175  -0.0985   0.7841   0.0208
  -6.000  -0.1418   0.01600   0.01124  -0.0970   0.7537   0.0209
  -5.750  -0.1235   0.01521   0.01015  -0.0952   0.7168   0.0210
  -5.500  -0.1084   0.01415   0.00869  -0.0929   0.6627   0.0213
  -5.250  -0.0913   0.01369   0.00786  -0.0908   0.5962   0.0215
  -5.000  -0.0715   0.01333   0.00721  -0.0892   0.5404   0.0217
  -4.750  -0.0498   0.01303   0.00666  -0.0880   0.4988   0.0218
  -4.500  -0.0265   0.01270   0.00617  -0.0870   0.4751   0.0220
  -4.000   0.0228   0.01209   0.00534  -0.0857   0.4509   0.0225
  -3.750   0.0479   0.01185   0.00502  -0.0851   0.4428   0.0228
  -3.500   0.0733   0.01155   0.00464  -0.0845   0.4366   0.0230
  -3.250   0.0987   0.01129   0.00430  -0.0839   0.4309   0.0233
  -3.000   0.1242   0.01104   0.00399  -0.0833   0.4264   0.0235
  -2.750   0.1500   0.01082   0.00372  -0.0828   0.4223   0.0239
  -2.500   0.1756   0.01062   0.00346  -0.0822   0.4179   0.0242
  -2.250   0.2011   0.01046   0.00325  -0.0817   0.4138   0.0246
  -2.000   0.2269   0.01030   0.00305  -0.0811   0.4107   0.0250
  -1.750   0.2527   0.01015   0.00287  -0.0806   0.4081   0.0253
  -1.500   0.2784   0.01001   0.00270  -0.0801   0.4054   0.0255
  -1.250   0.3041   0.00990   0.00256  -0.0795   0.4027   0.0257
  -1.000   0.3296   0.00980   0.00244  -0.0790   0.3999   0.0259
  -0.500   0.3808   0.00963   0.00223  -0.0778   0.3949   0.0263
  -0.250   0.4066   0.00955   0.00214  -0.0773   0.3929   0.0264
   0.000   0.4322   0.00949   0.00207  -0.0768   0.3902   0.0266
   0.250   0.4578   0.00944   0.00202  -0.0762   0.3875   0.0268
   0.500   0.4829   0.00939   0.00193  -0.0756   0.3842   0.0274
   0.750   0.5080   0.00936   0.00187  -0.0749   0.3812   0.0279
   1.000   0.5337   0.00931   0.00182  -0.0744   0.3791   0.0288
   1.250   0.5594   0.00928   0.00179  -0.0739   0.3765   0.0299
   1.500   0.5849   0.00926   0.00177  -0.0733   0.3732   0.0313
   1.750   0.6104   0.00926   0.00177  -0.0728   0.3704   0.0327
   2.250   0.6604   0.00924   0.00182  -0.0715   0.3650   0.0641
   2.500   0.6860   0.00923   0.00186  -0.0711   0.3630   0.0763
   2.750   0.7116   0.00923   0.00191  -0.0706   0.3600   0.0862
   3.000   0.7369   0.00925   0.00196  -0.0700   0.3564   0.0988
   3.250   0.7616   0.00926   0.00204  -0.0694   0.3525   0.1257
   3.500   0.7868   0.00929   0.00212  -0.0689   0.3488   0.1431
   3.750   0.8123   0.00931   0.00219  -0.0684   0.3457   0.1572
   4.000   0.8376   0.00935   0.00227  -0.0679   0.3420   0.1693
   4.250   0.8625   0.00941   0.00236  -0.0673   0.3377   0.1857
   4.500   0.8873   0.00946   0.00245  -0.0667   0.3289   0.2083
   4.750   0.9113   0.00954   0.00255  -0.0660   0.3179   0.2380
   5.000   0.9348   0.00963   0.00268  -0.0652   0.3038   0.2760
   5.250   0.9443   0.00895   0.00283  -0.0618   0.2855   0.7482
   5.500   0.9527   0.00894   0.00315  -0.0576   0.2452   0.9281
   5.750   1.0003   0.00986   0.00378  -0.0628   0.1817   0.9687
   6.000   1.0479   0.01050   0.00425  -0.0679   0.1514   0.9842
   6.250   1.0844   0.01106   0.00465  -0.0703   0.1236   0.9933
   6.750   1.1208   0.01312   0.00611  -0.0677   0.0155   1.0000
   7.000   1.1391   0.01337   0.00638  -0.0659   0.0134   1.0000
   7.250   1.1574   0.01365   0.00667  -0.0641   0.0122   1.0000
   7.500   1.1754   0.01395   0.00699  -0.0622   0.0112   1.0000
   7.750   1.1927   0.01429   0.00737  -0.0603   0.0099   1.0000
   8.000   1.2109   0.01459   0.00769  -0.0585   0.0094   1.0000
   8.250   1.2283   0.01491   0.00803  -0.0567   0.0089   1.0000
   8.500   1.2437   0.01524   0.00839  -0.0544   0.0084   1.0000
   8.750   1.2580   0.01560   0.00877  -0.0519   0.0079   1.0000
   9.000   1.2715   0.01601   0.00922  -0.0493   0.0075   1.0000
   9.250   1.2844   0.01649   0.00975  -0.0467   0.0070   1.0000
   9.500   1.2994   0.01688   0.01018  -0.0446   0.0068   1.0000
   9.750   1.3145   0.01729   0.01062  -0.0425   0.0064   1.0000
  10.000   1.3287   0.01776   0.01112  -0.0404   0.0062   1.0000
  10.250   1.3424   0.01828   0.01167  -0.0382   0.0059   1.0000
  10.500   1.3556   0.01882   0.01227  -0.0360   0.0057   1.0000
  10.750   1.3680   0.01943   0.01291  -0.0338   0.0054   1.0000
  11.000   1.3787   0.02014   0.01367  -0.0314   0.0052   1.0000
  11.250   1.3872   0.02100   0.01460  -0.0289   0.0051   1.0000
  11.500   1.3967   0.02183   0.01549  -0.0265   0.0049   1.0000
  11.750   1.4064   0.02268   0.01641  -0.0244   0.0048   1.0000
  12.000   1.4144   0.02367   0.01747  -0.0222   0.0047   1.0000
  12.250   1.4230   0.02466   0.01853  -0.0202   0.0045   1.0000
  12.500   1.4296   0.02585   0.01979  -0.0182   0.0044   1.0000
  12.750   1.4360   0.02711   0.02113  -0.0163   0.0043   1.0000
  13.000   1.4423   0.02846   0.02255  -0.0147   0.0041   1.0000
  13.250   1.4478   0.02995   0.02410  -0.0133   0.0040   1.0000
  13.500   1.4515   0.03170   0.02593  -0.0120   0.0039   1.0000
  13.750   1.4567   0.03340   0.02770  -0.0110   0.0038   1.0000
  14.000   1.4583   0.03556   0.02994  -0.0101   0.0037   1.0000
  14.250   1.4599   0.03785   0.03231  -0.0095   0.0036   1.0000
  14.500   1.4566   0.04085   0.03542  -0.0091   0.0036   1.0000
  14.750   1.4525   0.04416   0.03883  -0.0092   0.0035   1.0000
  15.000   1.4458   0.04803   0.04280  -0.0097   0.0034   1.0000
  15.250   1.4393   0.05206   0.04694  -0.0105   0.0034   1.0000
  15.500   1.4316   0.05634   0.05135  -0.0114   0.0034   1.0000
  15.750   1.4160   0.06181   0.05694  -0.0128   0.0033   1.0000
  16.000   1.4062   0.06646   0.06169  -0.0139   0.0033   1.0000
  16.250   1.3988   0.07070   0.06603  -0.0149   0.0033   1.0000
  16.500   1.3828   0.07621   0.07165  -0.0163   0.0033   1.0000
  16.750   1.3736   0.08077   0.07630  -0.0175   0.0033   1.0000
  17.000   1.3647   0.08529   0.08092  -0.0186   0.0032   1.0000
  17.250   1.3540   0.09018   0.08590  -0.0200   0.0032   1.0000
  17.500   1.3437   0.09510   0.09090  -0.0214   0.0032   1.0000
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