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EPPLER 325 AIRFOIL (e325-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 325 AIRFOIL (e325-il)
Reynolds number: 500,000
Max Cl/Cd: 69.19 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e325-il-500000-n5.txt
Download as CSV file: xf-e325-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 325 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.6160   0.08030   0.07810  -0.0135   1.0000   0.0045
 -10.250  -0.6455   0.07251   0.07022  -0.0171   1.0000   0.0045
 -10.000  -0.7075   0.06159   0.05907  -0.0159   1.0000   0.0041
  -9.750  -0.7334   0.05689   0.05422  -0.0124   1.0000   0.0041
  -9.500  -0.7543   0.05297   0.05013  -0.0078   1.0000   0.0042
  -9.250  -0.7914   0.04470   0.04147  -0.0004   1.0000   0.0041
  -9.000  -0.8100   0.03831   0.03466   0.0054   1.0000   0.0042
  -8.750  -0.7987   0.03756   0.03383   0.0074   1.0000   0.0043
  -8.500  -0.8058   0.03228   0.02805   0.0125   1.0000   0.0044
  -8.250  -0.8000   0.02910   0.02450   0.0159   1.0000   0.0045
  -8.000  -0.7875   0.02707   0.02220   0.0184   1.0000   0.0046
  -7.750  -0.7733   0.02473   0.01953   0.0207   1.0000   0.0047
  -7.500  -0.7199   0.02190   0.01619   0.0149   0.8979   0.0049
  -7.250  -0.6977   0.02072   0.01456   0.0161   0.8296   0.0051
  -7.000  -0.6766   0.01984   0.01338   0.0174   0.7892   0.0052
  -6.750  -0.6538   0.01899   0.01226   0.0185   0.7593   0.0055
  -6.500  -0.6305   0.01832   0.01134   0.0194   0.7329   0.0057
  -6.250  -0.6068   0.01759   0.01040   0.0202   0.7095   0.0058
  -6.000  -0.5837   0.01671   0.00937   0.0210   0.6896   0.0061
  -5.750  -0.5610   0.01604   0.00858   0.0220   0.6712   0.0062
  -5.500  -0.5385   0.01544   0.00788   0.0230   0.6541   0.0063
  -5.250  -0.5163   0.01492   0.00724   0.0240   0.6375   0.0064
  -5.000  -0.4941   0.01444   0.00667   0.0251   0.6224   0.0066
  -4.500  -0.4493   0.01364   0.00571   0.0273   0.5951   0.0070
  -4.250  -0.4268   0.01327   0.00524   0.0284   0.5816   0.0075
  -4.000  -0.4040   0.01295   0.00483   0.0294   0.5694   0.0081
  -3.750  -0.3809   0.01267   0.00448   0.0303   0.5577   0.0084
  -3.500  -0.3577   0.01240   0.00414   0.0313   0.5464   0.0098
  -3.250  -0.3344   0.01214   0.00384   0.0322   0.5353   0.0124
  -3.000  -0.3114   0.01189   0.00357   0.0332   0.5246   0.0194
  -2.750  -0.2890   0.01160   0.00333   0.0342   0.5142   0.0382
  -2.500  -0.2672   0.01127   0.00313   0.0353   0.5050   0.0741
  -2.250  -0.2475   0.01084   0.00292   0.0367   0.4956   0.1394
  -2.000  -0.2389   0.00975   0.00258   0.0401   0.4875   0.3313
  -1.750  -0.2634   0.00758   0.00208   0.0504   0.4825   0.7133
  -1.500  -0.2424   0.00765   0.00238   0.0524   0.4741   0.8049
  -1.250  -0.2175   0.00784   0.00251   0.0534   0.4654   0.8275
  -1.000  -0.1916   0.00805   0.00268   0.0542   0.4567   0.8430
  -0.750  -0.1657   0.00821   0.00274   0.0549   0.4483   0.8515
  -0.500  -0.1379   0.00842   0.00291   0.0552   0.4404   0.8601
  -0.250  -0.1113   0.00862   0.00303   0.0558   0.4325   0.8673
   0.000  -0.0826   0.00870   0.00306   0.0557   0.4245   0.8699
   0.500  -0.0277   0.00875   0.00296   0.0558   0.4102   0.8726
   0.750  -0.0006   0.00878   0.00290   0.0559   0.4029   0.8740
   1.000   0.0266   0.00879   0.00286   0.0559   0.3963   0.8754
   1.250   0.0535   0.00881   0.00283   0.0560   0.3899   0.8769
   1.500   0.0804   0.00884   0.00279   0.0561   0.3838   0.8782
   1.750   0.1074   0.00886   0.00276   0.0562   0.3771   0.8793
   2.000   0.1344   0.00890   0.00274   0.0562   0.3711   0.8804
   2.250   0.1624   0.00893   0.00276   0.0561   0.3658   0.8813
   2.500   0.1902   0.00899   0.00278   0.0561   0.3596   0.8822
   2.750   0.2178   0.00905   0.00281   0.0560   0.3540   0.8831
   3.000   0.2456   0.00910   0.00285   0.0559   0.3487   0.8840
   3.250   0.2731   0.00917   0.00289   0.0558   0.3429   0.8849
   3.500   0.3005   0.00924   0.00295   0.0558   0.3377   0.8859
   3.750   0.3280   0.00930   0.00300   0.0557   0.3323   0.8869
   4.000   0.3551   0.00938   0.00308   0.0557   0.3269   0.8881
   4.250   0.3822   0.00946   0.00315   0.0557   0.3217   0.8894
   4.500   0.4094   0.00954   0.00323   0.0557   0.3161   0.8907
   4.750   0.4360   0.00964   0.00331   0.0558   0.3104   0.8920
   5.000   0.4631   0.00972   0.00341   0.0557   0.3046   0.8931
   5.250   0.4898   0.00981   0.00350   0.0557   0.2985   0.8943
   5.500   0.5163   0.00993   0.00361   0.0558   0.2928   0.8955
   5.750   0.5434   0.01001   0.00373   0.0557   0.2867   0.8965
   6.000   0.5700   0.01014   0.00386   0.0558   0.2803   0.8975
   6.250   0.5969   0.01026   0.00401   0.0557   0.2742   0.8985
   6.500   0.6233   0.01039   0.00417   0.0558   0.2672   0.8997
   6.750   0.6496   0.01054   0.00434   0.0559   0.2606   0.9009
   7.000   0.6755   0.01070   0.00451   0.0560   0.2527   0.9024
   7.250   0.7013   0.01086   0.00471   0.0561   0.2449   0.9040
   7.500   0.7264   0.01107   0.00491   0.0563   0.2354   0.9056
   7.750   0.7518   0.01126   0.00513   0.0565   0.2257   0.9072
   8.000   0.7766   0.01148   0.00536   0.0567   0.2168   0.9088
   8.250   0.8008   0.01174   0.00561   0.0570   0.2065   0.9104
   8.500   0.8251   0.01199   0.00588   0.0573   0.1953   0.9120
   8.750   0.8489   0.01227   0.00619   0.0576   0.1838   0.9135
   9.000   0.8717   0.01261   0.00653   0.0581   0.1705   0.9153
   9.250   0.8934   0.01301   0.00691   0.0587   0.1559   0.9173
   9.500   0.9138   0.01348   0.00736   0.0595   0.1400   0.9196
   9.750   0.9334   0.01398   0.00782   0.0604   0.1255   0.9222
  10.000   0.9519   0.01451   0.00833   0.0614   0.1117   0.9252
  10.250   0.9690   0.01510   0.00889   0.0626   0.0973   0.9283
  10.500   0.9854   0.01571   0.00950   0.0639   0.0841   0.9315
  10.750   1.0006   0.01634   0.01013   0.0653   0.0732   0.9353
  11.000   1.0143   0.01698   0.01078   0.0669   0.0643   0.9399
  11.250   1.0281   0.01761   0.01144   0.0685   0.0571   0.9446
  11.500   1.0394   0.01829   0.01217   0.0703   0.0509   0.9507
  11.750   1.0494   0.01914   0.01306   0.0720   0.0451   0.9585
  12.000   1.0665   0.02010   0.01409   0.0719   0.0395   0.9651
  12.250   1.0833   0.02128   0.01533   0.0712   0.0347   0.9725
  12.500   1.1012   0.02281   0.01691   0.0694   0.0300   0.9793
  12.750   1.1175   0.02465   0.01883   0.0671   0.0258   0.9862
  13.000   1.1324   0.02688   0.02113   0.0642   0.0217   0.9931
  13.250   1.1388   0.02917   0.02350   0.0630   0.0204   1.0000
  13.500   1.1320   0.03171   0.02607   0.0635   0.0175   1.0000
  13.750   1.1296   0.03416   0.02863   0.0636   0.0175   1.0000
  14.000   1.1249   0.03703   0.03157   0.0634   0.0165   1.0000
  14.250   1.1193   0.04009   0.03470   0.0630   0.0147   1.0000
  14.500   1.1139   0.04326   0.03797   0.0624   0.0145   1.0000
  14.750   1.1047   0.04689   0.04165   0.0615   0.0129   1.0000
  15.000   1.0980   0.05036   0.04522   0.0607   0.0132   1.0000
  15.250   1.0888   0.05412   0.04902   0.0597   0.0111   1.0000
  15.500   1.0795   0.05803   0.05301   0.0585   0.0104   1.0000
  15.750   1.0730   0.06175   0.05682   0.0573   0.0102   1.0000
  16.000   1.0652   0.06577   0.06095   0.0559   0.0101   1.0000
  16.250   1.0582   0.06977   0.06504   0.0544   0.0099   1.0000
  16.500   1.0501   0.07404   0.06941   0.0528   0.0102   1.0000
  16.750   1.0435   0.07815   0.07360   0.0512   0.0094   1.0000
  17.000   1.0343   0.08270   0.07820   0.0494   0.0084   1.0000
  17.250   1.0265   0.08716   0.08275   0.0475   0.0084   1.0000
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