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USA 25 AIRFOIL (usa25-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: USA 25 AIRFOIL (usa25-il)
Reynolds number: 50,000
Max Cl/Cd: 25.62 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa25-il-50000.txt
Download as CSV file: xf-usa25-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3279   0.10833   0.10175  -0.0230   1.0000   0.1463
  -7.750  -0.3471   0.10851   0.10209  -0.0221   1.0000   0.1476
  -7.500  -0.3657   0.10873   0.10245  -0.0221   1.0000   0.1483
  -7.250  -0.3408   0.10127   0.09497  -0.0192   1.0000   0.1529
  -7.000  -0.3435   0.09893   0.09271  -0.0176   1.0000   0.1565
  -6.750  -0.3508   0.09724   0.09111  -0.0170   1.0000   0.1601
  -6.500  -0.3639   0.09696   0.09092  -0.0179   1.0000   0.1628
  -6.250  -0.3685   0.09496   0.08899  -0.0181   1.0000   0.1642
  -6.000  -0.3594   0.08997   0.08406  -0.0146   1.0000   0.1678
  -5.750  -0.3588   0.08746   0.08160  -0.0134   1.0000   0.1724
  -5.500  -0.3630   0.08694   0.08106  -0.0153   1.0000   0.1778
  -5.250  -0.3607   0.08356   0.07774  -0.0143   1.0000   0.1801
  -5.000  -0.3562   0.08008   0.07433  -0.0118   1.0000   0.1849
  -4.750  -0.3515   0.08051   0.07461  -0.0155   1.0000   0.1935
  -4.500  -0.3485   0.07519   0.06945  -0.0113   1.0000   0.1977
  -4.250  -0.3388   0.07486   0.06896  -0.0140   1.0000   0.2084
  -4.000  -0.3356   0.07020   0.06444  -0.0106   1.0000   0.2127
  -3.500  -0.3187   0.06527   0.05948  -0.0099   1.0000   0.2292
  -3.250  -0.3075   0.06329   0.05743  -0.0106   1.0000   0.2402
  -2.750  -0.2853   0.05996   0.05398  -0.0109   1.0000   0.2673
  -2.500  -0.2806   0.05695   0.05109  -0.0089   1.0000   0.2764
  -2.250  -0.2634   0.05497   0.04906  -0.0107   0.9960   0.2994
  -1.750  -0.1770   0.04700   0.04106  -0.0208   0.9549   0.4329
  -1.500  -0.1322   0.04344   0.03744  -0.0252   0.9317   0.4730
  -1.250  -0.0771   0.04073   0.03447  -0.0320   0.9091   0.4946
  -1.000  -0.0131   0.03859   0.03197  -0.0400   0.8871   0.4839
  -0.750   0.1192   0.04058   0.03199  -0.0577   0.8640   0.2065
  -0.500   0.1686   0.03822   0.02917  -0.0609   0.8470   0.1885
  -0.250   0.2165   0.03621   0.02673  -0.0636   0.8317   0.1859
   0.000   0.2629   0.03450   0.02466  -0.0661   0.8178   0.1984
   0.250   0.3258   0.03205   0.02177  -0.0708   0.8095   0.2362
   0.500   0.3701   0.03057   0.02020  -0.0735   0.7958   0.3057
   0.750   0.4169   0.02960   0.01903  -0.0764   0.7826   0.3389
   1.000   0.4565   0.02893   0.01833  -0.0781   0.7701   0.3595
   1.250   0.4930   0.02839   0.01779  -0.0792   0.7594   0.3779
   1.500   0.5266   0.02776   0.01728  -0.0798   0.7497   0.4105
   1.750   0.5403   0.02755   0.01760  -0.0778   0.7381   0.4806
   2.000   0.6565   0.02670   0.01715  -0.0931   0.7275   1.0000
   2.250   0.6909   0.02697   0.01712  -0.0938   0.7189   1.0000
   2.500   0.7010   0.02810   0.01813  -0.0912   0.7083   1.0000
   2.750   0.7256   0.02873   0.01860  -0.0907   0.7001   1.0000
   3.000   0.7420   0.02968   0.01946  -0.0891   0.6912   1.0000
   3.250   0.7546   0.03085   0.02056  -0.0871   0.6829   1.0000
   3.500   0.7779   0.03155   0.02119  -0.0864   0.6750   1.0000
   3.750   0.7808   0.03324   0.02286  -0.0833   0.6666   1.0000
   4.000   0.8088   0.03379   0.02338  -0.0832   0.6592   1.0000
   4.250   0.8029   0.03599   0.02559  -0.0792   0.6503   1.0000
   4.500   0.8427   0.03596   0.02552  -0.0803   0.6429   1.0000
   4.750   0.8240   0.03888   0.02847  -0.0751   0.6330   1.0000
   5.000   0.8508   0.03944   0.02903  -0.0746   0.6240   1.0000
   5.250   0.8771   0.03992   0.02954  -0.0738   0.6135   1.0000
   5.500   0.8621   0.04280   0.03245  -0.0694   0.6027   1.0000
   5.750   0.8865   0.04345   0.03313  -0.0684   0.5922   1.0000
   6.000   0.9351   0.04267   0.03240  -0.0695   0.5818   1.0000
   6.250   0.8981   0.04710   0.03687  -0.0636   0.5707   1.0000
   6.500   0.8990   0.04940   0.03924  -0.0610   0.5604   1.0000
   6.750   0.9722   0.04711   0.03706  -0.0636   0.5498   1.0000
   7.000   0.9108   0.05335   0.04329  -0.0566   0.5384   1.0000
   7.250   0.8651   0.05958   0.04948  -0.0529   0.5269   1.0000
   7.500   0.8827   0.06101   0.05100  -0.0516   0.5156   1.0000
   8.000   0.8605   0.06915   0.05919  -0.0490   0.4933   1.0000
   8.250   0.8530   0.07313   0.06320  -0.0481   0.4834   1.0000
   8.500   0.8930   0.07296   0.06317  -0.0470   0.4723   1.0000
   8.750   0.8391   0.08115   0.07128  -0.0470   0.4656   1.0000
   9.000   0.8675   0.08248   0.07273  -0.0463   0.4565   1.0000
   9.250   0.8386   0.08901   0.07926  -0.0470   0.4551   1.0000
   9.500   0.8250   0.09432   0.08459  -0.0478   0.4550   1.0000
   9.750   0.8201   0.09910   0.08943  -0.0486   0.4559   1.0000
  12.500   1.2689   0.05661   0.04958  -0.0092   0.2443   1.0000
  12.750   1.2671   0.05630   0.04916  -0.0063   0.2164   1.0000
  13.000   1.1993   0.07146   0.06457  -0.0102   0.2381   1.0000
  13.250   1.1606   0.08150   0.07460  -0.0131   0.2355   1.0000
  13.500   1.2100   0.06819   0.06038  -0.0040   0.1474   1.0000
  13.750   1.1935   0.07326   0.06537  -0.0045   0.1319   1.0000
  14.000   1.1808   0.07799   0.07000  -0.0050   0.1186   1.0000
  14.250   1.1766   0.08158   0.07341  -0.0050   0.1085   1.0000
  14.500   1.1697   0.08611   0.07806  -0.0056   0.1010   1.0000
  14.750   1.1727   0.08917   0.08108  -0.0050   0.0949   1.0000
  15.000   1.1666   0.09411   0.08625  -0.0059   0.0914   1.0000
  15.250   1.1888   0.09456   0.08648  -0.0032   0.0851   1.0000
  15.500   1.1745   0.10091   0.09315  -0.0054   0.0844   1.0000
  15.750   1.1560   0.10816   0.10067  -0.0085   0.0843   1.0000
  16.000   1.1339   0.11642   0.10915  -0.0125   0.0847   1.0000
  16.250   1.1088   0.12576   0.11865  -0.0173   0.0852   1.0000
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