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USA 25 AIRFOIL (usa25-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: USA 25 AIRFOIL (usa25-il)
Reynolds number: 100,000
Max Cl/Cd: 54.57 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa25-il-100000-n5.txt
Download as CSV file: xf-usa25-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3424   0.10283   0.09825  -0.0252   1.0000   0.0619
  -7.750  -0.3623   0.10229   0.09782  -0.0242   1.0000   0.0622
  -7.500  -0.3732   0.10079   0.09639  -0.0249   1.0000   0.0625
  -7.250  -0.3788   0.09878   0.09441  -0.0254   1.0000   0.0626
  -7.000  -0.3810   0.09640   0.09204  -0.0257   1.0000   0.0627
  -6.750  -0.3691   0.09040   0.08612  -0.0230   0.9984   0.0636
  -6.500  -0.3478   0.08609   0.08178  -0.0238   0.9946   0.0653
  -6.250  -0.3240   0.08240   0.07805  -0.0277   0.9884   0.0693
  -6.000  -0.2899   0.07903   0.07448  -0.0397   0.9781   0.0745
  -5.750  -0.2592   0.07486   0.07013  -0.0467   0.9691   0.0749
  -5.250  -0.2045   0.06627   0.06126  -0.0548   0.9524   0.0750
  -4.750  -0.1651   0.05310   0.04776  -0.0592   0.9372   0.0518
  -4.500  -0.1417   0.04991   0.04444  -0.0605   0.9288   0.0511
  -4.250  -0.1149   0.04650   0.04085  -0.0623   0.9206   0.0505
  -4.000  -0.0910   0.04290   0.03700  -0.0633   0.9103   0.0511
  -3.750  -0.0593   0.03873   0.03248  -0.0654   0.9036   0.0516
  -3.500  -0.0375   0.03584   0.02936  -0.0651   0.8920   0.0512
  -3.250  -0.0127   0.03261   0.02581  -0.0650   0.8811   0.0509
  -3.000   0.0155   0.02889   0.02164  -0.0653   0.8715   0.0506
  -2.750   0.0453   0.02528   0.01743  -0.0656   0.8610   0.0509
  -2.500   0.0754   0.02275   0.01435  -0.0658   0.8479   0.0515
  -2.250   0.1095   0.02140   0.01273  -0.0667   0.8334   0.0537
  -2.000   0.1473   0.02046   0.01162  -0.0684   0.8171   0.0560
  -1.750   0.1851   0.01923   0.01012  -0.0699   0.7972   0.0574
  -1.500   0.2233   0.01821   0.00884  -0.0714   0.7714   0.0593
  -1.250   0.2611   0.01740   0.00775  -0.0728   0.7369   0.0620
  -1.000   0.2967   0.01693   0.00709  -0.0739   0.6927   0.0660
  -0.750   0.3293   0.01660   0.00645  -0.0744   0.6486   0.0735
  -0.500   0.3585   0.01647   0.00611  -0.0743   0.6138   0.0863
  -0.250   0.3864   0.01653   0.00600  -0.0741   0.5885   0.1057
   0.000   0.4135   0.01672   0.00605  -0.0738   0.5698   0.1238
   0.250   0.4403   0.01692   0.00611  -0.0736   0.5550   0.1400
   0.500   0.4675   0.01699   0.00601  -0.0733   0.5427   0.1495
   0.750   0.4944   0.01709   0.00601  -0.0731   0.5326   0.1597
   1.000   0.5212   0.01720   0.00604  -0.0728   0.5242   0.1712
   1.250   0.5479   0.01730   0.00609  -0.0726   0.5171   0.1846
   1.500   0.5741   0.01738   0.00612  -0.0723   0.5104   0.1982
   1.750   0.6002   0.01747   0.00612  -0.0719   0.5045   0.2102
   2.000   0.6252   0.01753   0.00618  -0.0714   0.4984   0.2243
   2.250   0.6506   0.01762   0.00625  -0.0709   0.4934   0.2420
   2.500   0.6761   0.01771   0.00633  -0.0705   0.4888   0.2653
   2.750   0.7005   0.01771   0.00646  -0.0699   0.4838   0.3041
   3.000   0.8035   0.01687   0.00692  -0.0857   0.4764   1.0000
   3.250   0.8264   0.01714   0.00715  -0.0847   0.4722   1.0000
   3.500   0.8490   0.01741   0.00739  -0.0837   0.4676   1.0000
   3.750   0.8720   0.01770   0.00762  -0.0828   0.4626   1.0000
   4.000   0.8943   0.01800   0.00788  -0.0817   0.4572   1.0000
   4.250   0.9152   0.01827   0.00816  -0.0804   0.4504   1.0000
   4.500   0.9376   0.01858   0.00836  -0.0793   0.4438   1.0000
   4.750   0.9570   0.01883   0.00869  -0.0777   0.4363   1.0000
   5.000   0.9790   0.01913   0.00897  -0.0766   0.4303   1.0000
   5.250   1.0007   0.01945   0.00933  -0.0754   0.4253   1.0000
   5.500   1.0217   0.01976   0.00973  -0.0741   0.4199   1.0000
   5.750   1.0438   0.02008   0.01009  -0.0731   0.4148   1.0000
   6.000   1.0650   0.02041   0.01049  -0.0719   0.4095   1.0000
   6.250   1.0852   0.02074   0.01094  -0.0705   0.4037   1.0000
   6.500   1.1072   0.02107   0.01132  -0.0694   0.3986   1.0000
   6.750   1.1276   0.02142   0.01182  -0.0681   0.3931   1.0000
   7.000   1.1472   0.02175   0.01230  -0.0666   0.3867   1.0000
   7.250   1.1647   0.02194   0.01256  -0.0646   0.3771   1.0000
   7.500   1.1791   0.02198   0.01266  -0.0620   0.3638   1.0000
   7.750   1.1924   0.02204   0.01281  -0.0592   0.3492   1.0000
   8.000   1.2071   0.02220   0.01312  -0.0568   0.3355   1.0000
   8.250   1.2215   0.02239   0.01343  -0.0544   0.3199   1.0000
   8.500   1.2361   0.02265   0.01381  -0.0521   0.3025   1.0000
   8.750   1.2484   0.02296   0.01413  -0.0494   0.2801   1.0000
   9.000   1.2552   0.02346   0.01447  -0.0459   0.2488   1.0000
   9.250   1.2593   0.02427   0.01511  -0.0421   0.2190   1.0000
   9.500   1.2639   0.02516   0.01592  -0.0385   0.1966   1.0000
   9.750   1.2683   0.02615   0.01686  -0.0351   0.1788   1.0000
  10.000   1.2723   0.02723   0.01792  -0.0318   0.1620   1.0000
  10.250   1.2732   0.02856   0.01918  -0.0283   0.1346   1.0000
  10.500   1.2684   0.03027   0.02071  -0.0245   0.0938   1.0000
  10.750   1.2535   0.03275   0.02289  -0.0201   0.0632   1.0000
  11.000   1.2459   0.03493   0.02503  -0.0169   0.0456   1.0000
  11.250   1.2351   0.03754   0.02757  -0.0140   0.0299   1.0000
  11.500   1.2291   0.04001   0.03009  -0.0120   0.0271   1.0000
  11.750   1.2229   0.04271   0.03289  -0.0104   0.0253   1.0000
  12.000   1.2168   0.04566   0.03598  -0.0094   0.0243   1.0000
  12.250   1.2103   0.04890   0.03938  -0.0088   0.0236   1.0000
  12.500   1.2035   0.05244   0.04309  -0.0087   0.0231   1.0000
  12.750   1.1954   0.05640   0.04723  -0.0091   0.0227   1.0000
  13.000   1.1871   0.06062   0.05162  -0.0099   0.0223   1.0000
  13.250   1.1783   0.06507   0.05624  -0.0109   0.0220   1.0000
  13.500   1.1683   0.06982   0.06114  -0.0121   0.0216   1.0000
  13.750   1.1584   0.07462   0.06610  -0.0134   0.0213   1.0000
  14.000   1.1474   0.07965   0.07127  -0.0148   0.0208   1.0000
  14.250   1.1373   0.08464   0.07640  -0.0163   0.0205   1.0000
  14.500   1.1268   0.08977   0.08166  -0.0179   0.0202   1.0000
  14.750   1.1161   0.09503   0.08704  -0.0196   0.0198   1.0000
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