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USA 25 AIRFOIL (usa25-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: USA 25 AIRFOIL (usa25-il)
Reynolds number: 200,000
Max Cl/Cd: 74.08 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa25-il-200000.txt
Download as CSV file: xf-usa25-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3614   0.09269   0.08959  -0.0164   1.0000   0.0466
  -7.000  -0.3731   0.09115   0.08811  -0.0143   1.0000   0.0472
  -6.750  -0.3804   0.08920   0.08620  -0.0131   1.0000   0.0484
  -6.500  -0.3855   0.08706   0.08409  -0.0129   0.9998   0.0500
  -6.250  -0.3430   0.08064   0.07750  -0.0318   0.9901   0.0531
  -6.000  -0.3246   0.07659   0.07349  -0.0304   0.9868   0.0545
  -5.750  -0.2959   0.07316   0.07003  -0.0342   0.9832   0.0573
  -5.250  -0.2271   0.06409   0.06065  -0.0503   0.9704   0.0646
  -5.000  -0.2097   0.06102   0.05760  -0.0502   0.9629   0.0660
  -4.750  -0.1770   0.05778   0.05429  -0.0539   0.9584   0.0691
  -4.500  -0.1333   0.05462   0.05071  -0.0614   0.9491   0.0763
  -4.250  -0.1083   0.05039   0.04653  -0.0631   0.9446   0.0776
  -4.000  -0.0826   0.04758   0.04370  -0.0643   0.9380   0.0794
  -3.750  -0.0514   0.04486   0.04089  -0.0664   0.9311   0.0827
  -3.500  -0.0069   0.04235   0.03784  -0.0704   0.9234   0.0899
  -3.250   0.0177   0.03868   0.03425  -0.0715   0.9165   0.0916
  -3.000   0.0460   0.03638   0.03193  -0.0723   0.9082   0.0941
  -2.750   0.0813   0.03391   0.02930  -0.0741   0.9006   0.0976
  -2.500   0.1111   0.02736   0.02201  -0.0738   0.8896   0.0776
  -2.250   0.1421   0.01984   0.01349  -0.0735   0.8821   0.0606
  -2.000   0.1808   0.01752   0.01071  -0.0750   0.8696   0.0615
  -1.750   0.2184   0.01589   0.00874  -0.0763   0.8500   0.0621
  -1.500   0.2685   0.01443   0.00696  -0.0801   0.8227   0.0630
  -1.250   0.3124   0.01337   0.00565  -0.0828   0.7735   0.0654
  -1.000   0.3422   0.01314   0.00508  -0.0826   0.6964   0.0688
  -0.750   0.3633   0.01317   0.00467  -0.0807   0.6330   0.0735
  -0.500   0.3842   0.01315   0.00443  -0.0790   0.5989   0.0812
  -0.250   0.4072   0.01321   0.00435  -0.0778   0.5781   0.1018
   0.000   0.4319   0.01344   0.00450  -0.0771   0.5635   0.1262
   0.250   0.4572   0.01369   0.00461  -0.0765   0.5518   0.1406
   0.500   0.4828   0.01387   0.00469  -0.0760   0.5419   0.1520
   0.750   0.5086   0.01404   0.00474  -0.0755   0.5341   0.1603
   1.000   0.5341   0.01408   0.00479  -0.0750   0.5269   0.1689
   1.250   0.5604   0.01427   0.00491  -0.0748   0.5209   0.1823
   1.500   0.5862   0.01436   0.00499  -0.0743   0.5151   0.1950
   1.750   0.6116   0.01442   0.00508  -0.0739   0.5093   0.2099
   2.000   0.6377   0.01450   0.00516  -0.0736   0.5047   0.2268
   2.250   0.6623   0.01449   0.00523  -0.0729   0.5003   0.2443
   2.500   0.6863   0.01449   0.00528  -0.0721   0.4953   0.2661
   2.750   0.7105   0.01450   0.00534  -0.0714   0.4904   0.2967
   3.000   0.8403   0.01358   0.00583  -0.0931   0.4787   1.0000
   3.250   0.8639   0.01387   0.00598  -0.0922   0.4736   1.0000
   3.500   0.8843   0.01404   0.00617  -0.0908   0.4678   1.0000
   3.750   0.9059   0.01425   0.00633  -0.0895   0.4619   1.0000
   4.000   0.9295   0.01457   0.00657  -0.0887   0.4571   1.0000
   4.250   0.9501   0.01475   0.00683  -0.0873   0.4527   1.0000
   4.500   0.9721   0.01499   0.00708  -0.0861   0.4482   1.0000
   4.750   0.9955   0.01528   0.00733  -0.0853   0.4441   1.0000
   5.000   1.0175   0.01558   0.00766  -0.0842   0.4397   1.0000
   5.250   1.0379   0.01579   0.00795  -0.0827   0.4345   1.0000
   5.500   1.0604   0.01605   0.00820  -0.0817   0.4294   1.0000
   5.750   1.0829   0.01638   0.00854  -0.0807   0.4246   1.0000
   6.000   1.1017   0.01655   0.00883  -0.0789   0.4181   1.0000
   6.250   1.1223   0.01672   0.00894  -0.0774   0.4095   1.0000
   6.500   1.1380   0.01670   0.00899  -0.0749   0.3992   1.0000
   6.750   1.1556   0.01679   0.00914  -0.0729   0.3903   1.0000
   7.000   1.1736   0.01684   0.00920  -0.0709   0.3814   1.0000
   7.250   1.1887   0.01684   0.00932  -0.0683   0.3708   1.0000
   7.500   1.2040   0.01682   0.00935  -0.0658   0.3596   1.0000
   7.750   1.2196   0.01684   0.00940  -0.0633   0.3486   1.0000
   8.000   1.2342   0.01686   0.00949  -0.0607   0.3350   1.0000
   8.250   1.2486   0.01690   0.00963  -0.0581   0.3169   1.0000
   8.500   1.2624   0.01704   0.00978  -0.0554   0.2946   1.0000
   8.750   1.2745   0.01736   0.01003  -0.0525   0.2683   1.0000
   9.000   1.2829   0.01793   0.01043  -0.0491   0.2375   1.0000
   9.250   1.2892   0.01865   0.01100  -0.0454   0.2101   1.0000
   9.500   1.2952   0.01947   0.01169  -0.0418   0.1858   1.0000
   9.750   1.2997   0.02044   0.01254  -0.0381   0.1598   1.0000
  10.000   1.3052   0.02143   0.01342  -0.0348   0.1300   1.0000
  10.250   1.2962   0.02327   0.01482  -0.0297   0.0743   1.0000
  10.500   1.2916   0.02495   0.01634  -0.0254   0.0490   1.0000
  10.750   1.2914   0.02642   0.01777  -0.0218   0.0355   1.0000
  11.000   1.2939   0.02779   0.01917  -0.0189   0.0313   1.0000
  11.250   1.2962   0.02923   0.02070  -0.0161   0.0291   1.0000
  11.500   1.2971   0.03083   0.02241  -0.0135   0.0278   1.0000
  11.750   1.2948   0.03279   0.02451  -0.0110   0.0267   1.0000
  12.000   1.2924   0.03488   0.02674  -0.0089   0.0262   1.0000
  12.250   1.2892   0.03721   0.02923  -0.0072   0.0255   1.0000
  12.500   1.2844   0.03989   0.03206  -0.0059   0.0248   1.0000
  12.750   1.2787   0.04289   0.03521  -0.0050   0.0243   1.0000
  13.000   1.2719   0.04626   0.03872  -0.0046   0.0241   1.0000
  13.250   1.2642   0.04997   0.04256  -0.0047   0.0235   1.0000
  13.500   1.2569   0.05384   0.04655  -0.0051   0.0232   1.0000
  13.750   1.2500   0.05777   0.05059  -0.0056   0.0230   1.0000
  14.000   1.2436   0.06167   0.05459  -0.0061   0.0228   1.0000
  14.250   1.2394   0.06525   0.05827  -0.0065   0.0227   1.0000
  14.500   1.2345   0.06890   0.06199  -0.0069   0.0224   1.0000
  14.750   1.2333   0.07202   0.06520  -0.0070   0.0223   1.0000
  15.000   1.2328   0.07499   0.06822  -0.0069   0.0220   1.0000
  15.250   1.2352   0.07749   0.07078  -0.0065   0.0218   1.0000
  15.500   1.2401   0.07963   0.07296  -0.0057   0.0216   1.0000
  15.750   1.2475   0.08146   0.07486  -0.0048   0.0215   1.0000
  16.000   1.2554   0.08338   0.07687  -0.0039   0.0215   1.0000
  16.250   1.2625   0.08552   0.07912  -0.0031   0.0215   1.0000
  16.500   1.2673   0.08812   0.08184  -0.0029   0.0214   1.0000
  16.750   1.2703   0.09112   0.08500  -0.0028   0.0213   1.0000
  17.000   1.2726   0.09439   0.08842  -0.0023   0.0209   1.0000
  17.250   1.2688   0.09855   0.09276  -0.0036   0.0209   1.0000
  17.500   1.2615   0.10338   0.09779  -0.0051   0.0208   1.0000
  17.750   1.2543   0.10817   0.10276  -0.0072   0.0209   1.0000
  18.000   1.2451   0.11339   0.10816  -0.0097   0.0210   1.0000
  18.250   1.2340   0.11909   0.11407  -0.0130   0.0213   1.0000
  18.500   1.2198   0.12557   0.12078  -0.0167   0.0215   1.0000
  18.750   1.2011   0.13331   0.12877  -0.0213   0.0218   1.0000
  19.000   1.1787   0.14230   0.13804  -0.0269   0.0223   1.0000
  19.250   1.1504   0.15322   0.14921  -0.0341   0.0226   1.0000
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