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EPPLER 325 AIRFOIL (e325-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 325 AIRFOIL (e325-il)
Reynolds number: 200,000
Max Cl/Cd: 51.11 at α=9.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e325-il-200000-n5.txt
Download as CSV file: xf-e325-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5842   0.09287   0.08943  -0.0053   1.0000   0.0104
 -10.500  -0.5964   0.08483   0.08140  -0.0114   1.0000   0.0104
 -10.250  -0.6143   0.07782   0.07432  -0.0155   1.0000   0.0104
 -10.000  -0.6208   0.07504   0.07152  -0.0162   1.0000   0.0101
  -9.750  -0.6393   0.07031   0.06671  -0.0165   1.0000   0.0101
  -9.500  -0.6576   0.06614   0.06244  -0.0153   1.0000   0.0100
  -9.250  -0.6726   0.06284   0.05903  -0.0129   1.0000   0.0099
  -9.000  -0.6875   0.05958   0.05565  -0.0095   1.0000   0.0098
  -8.750  -0.7050   0.05493   0.05076  -0.0050   1.0000   0.0101
  -8.500  -0.7112   0.05151   0.04714  -0.0015   1.0000   0.0100
  -8.250  -0.7184   0.04688   0.04217   0.0026   1.0000   0.0102
  -8.000  -0.7268   0.04153   0.03626   0.0078   1.0000   0.0105
  -7.750  -0.7193   0.03968   0.03429   0.0102   1.0000   0.0107
  -7.500  -0.7097   0.03791   0.03238   0.0125   1.0000   0.0110
  -7.250  -0.7055   0.03313   0.02689   0.0170   1.0000   0.0106
  -6.500  -0.6547   0.02643   0.01919   0.0231   1.0000   0.0105
  -6.250  -0.6221   0.02440   0.01691   0.0220   0.9642   0.0107
  -6.000  -0.5702   0.02227   0.01448   0.0170   0.8985   0.0109
  -5.750  -0.5326   0.02093   0.01289   0.0152   0.8466   0.0112
  -5.500  -0.5049   0.01993   0.01165   0.0155   0.8077   0.0115
  -5.250  -0.4800   0.01905   0.01058   0.0163   0.7768   0.0120
  -5.000  -0.4573   0.01828   0.00964   0.0174   0.7506   0.0126
  -4.750  -0.4357   0.01762   0.00880   0.0188   0.7275   0.0133
  -4.500  -0.4151   0.01704   0.00811   0.0202   0.7069   0.0139
  -4.250  -0.3939   0.01658   0.00752   0.0216   0.6881   0.0161
  -4.000  -0.3726   0.01615   0.00701   0.0228   0.6705   0.0194
  -3.750  -0.3515   0.01571   0.00645   0.0242   0.6541   0.0219
  -3.500  -0.3311   0.01521   0.00588   0.0257   0.6390   0.0301
  -3.250  -0.3118   0.01469   0.00543   0.0273   0.6247   0.0529
  -3.000  -0.2948   0.01403   0.00505   0.0292   0.6111   0.1178
  -2.750  -0.2866   0.01292   0.00460   0.0325   0.5993   0.2724
  -2.250  -0.2607   0.01207   0.00594   0.0409   0.5767   0.8229
  -2.000  -0.2370   0.01277   0.00650   0.0430   0.5646   0.8472
  -1.750  -0.1908   0.01375   0.00728   0.0408   0.5511   0.8604
  -1.500  -0.1323   0.01479   0.00811   0.0361   0.5371   0.8706
  -1.250  -0.1172   0.01490   0.00807   0.0389   0.5276   0.8806
  -1.000  -0.0820   0.01495   0.00797   0.0375   0.5160   0.8818
  -0.750  -0.0499   0.01496   0.00784   0.0366   0.5057   0.8832
  -0.500  -0.0197   0.01497   0.00770   0.0361   0.4960   0.8848
  -0.250   0.0095   0.01495   0.00759   0.0358   0.4858   0.8867
   0.000   0.0351   0.01493   0.00746   0.0361   0.4773   0.8892
   0.250   0.0367   0.01473   0.00720   0.0412   0.4703   0.8961
   0.500   0.0682   0.01474   0.00711   0.0404   0.4619   0.8970
   0.750   0.0987   0.01474   0.00703   0.0397   0.4530   0.8980
   1.000   0.1286   0.01475   0.00696   0.0392   0.4452   0.8992
   1.250   0.1575   0.01476   0.00690   0.0388   0.4372   0.9006
   1.500   0.1847   0.01476   0.00684   0.0388   0.4300   0.9021
   1.750   0.2107   0.01476   0.00680   0.0390   0.4224   0.9039
   2.000   0.2328   0.01476   0.00674   0.0400   0.4163   0.9064
   2.250   0.2363   0.01461   0.00659   0.0447   0.4110   0.9118
   2.500   0.2659   0.01465   0.00658   0.0442   0.4040   0.9126
   2.750   0.2946   0.01468   0.00660   0.0438   0.3973   0.9135
   3.000   0.3230   0.01472   0.00662   0.0435   0.3907   0.9144
   3.250   0.3514   0.01479   0.00664   0.0431   0.3847   0.9156
   3.500   0.3792   0.01483   0.00671   0.0429   0.3780   0.9169
   3.750   0.4046   0.01489   0.00675   0.0432   0.3721   0.9183
   4.000   0.4284   0.01493   0.00681   0.0438   0.3663   0.9200
   4.250   0.4500   0.01496   0.00685   0.0448   0.3604   0.9221
   4.500   0.4638   0.01498   0.00685   0.0474   0.3556   0.9258
   4.750   0.4848   0.01501   0.00693   0.0486   0.3500   0.9277
   5.000   0.5129   0.01510   0.00705   0.0482   0.3437   0.9286
   5.250   0.5404   0.01522   0.00717   0.0480   0.3380   0.9295
   5.500   0.5678   0.01531   0.00735   0.0478   0.3311   0.9305
   5.750   0.5942   0.01544   0.00747   0.0478   0.3250   0.9317
   6.000   0.6209   0.01556   0.00768   0.0477   0.3183   0.9332
   6.250   0.6460   0.01569   0.00785   0.0480   0.3118   0.9350
   6.500   0.6688   0.01581   0.00803   0.0486   0.3056   0.9370
   6.750   0.6882   0.01590   0.00819   0.0500   0.2989   0.9396
   7.000   0.7034   0.01600   0.00831   0.0522   0.2934   0.9426
   7.250   0.7316   0.01616   0.00859   0.0517   0.2854   0.9436
   7.500   0.7587   0.01636   0.00882   0.0514   0.2778   0.9447
   7.750   0.7857   0.01654   0.00912   0.0512   0.2688   0.9459
   8.000   0.8120   0.01676   0.00942   0.0510   0.2600   0.9475
   8.250   0.8367   0.01700   0.00970   0.0511   0.2503   0.9495
   8.500   0.8599   0.01723   0.01004   0.0515   0.2399   0.9518
   8.750   0.8786   0.01747   0.01035   0.0527   0.2308   0.9547
   9.000   0.8964   0.01776   0.01067   0.0541   0.2207   0.9577
   9.250   0.9228   0.01812   0.01114   0.0536   0.2078   0.9590
   9.500   0.9480   0.01855   0.01164   0.0533   0.1943   0.9606
   9.750   0.9712   0.01906   0.01219   0.0532   0.1796   0.9626
  10.250   1.0070   0.02027   0.01346   0.0548   0.1489   0.9696
  10.500   1.0268   0.02107   0.01429   0.0548   0.1326   0.9724
  10.750   1.0471   0.02203   0.01527   0.0544   0.1162   0.9750
  11.000   1.0633   0.02308   0.01635   0.0546   0.1022   0.9788
  11.250   1.0750   0.02421   0.01750   0.0554   0.0900   0.9838
  11.500   1.0887   0.02549   0.01885   0.0552   0.0791   0.9880
  11.750   1.0973   0.02698   0.02040   0.0552   0.0703   0.9939
  12.000   1.1072   0.02898   0.02247   0.0537   0.0626   0.9998
  12.250   1.0871   0.03030   0.02386   0.0584   0.0605   1.0000
  12.500   1.0720   0.03212   0.02572   0.0614   0.0577   1.0000
  12.750   1.0604   0.03453   0.02817   0.0629   0.0548   1.0000
  13.000   1.0530   0.03708   0.03080   0.0635   0.0517   1.0000
  13.250   1.0459   0.03989   0.03369   0.0637   0.0485   1.0000
  13.500   1.0359   0.04325   0.03709   0.0633   0.0457   1.0000
  13.750   1.0290   0.04643   0.04036   0.0629   0.0433   1.0000
  14.000   1.0219   0.04976   0.04379   0.0622   0.0409   1.0000
  14.250   1.0122   0.05350   0.04760   0.0613   0.0390   1.0000
  14.500   1.0013   0.05750   0.05165   0.0601   0.0373   1.0000
  14.750   0.9945   0.06108   0.05534   0.0591   0.0353   1.0000
  15.000   0.9866   0.06497   0.05932   0.0579   0.0338   1.0000
  15.250   0.9774   0.06922   0.06364   0.0563   0.0323   1.0000
  15.500   0.9666   0.07382   0.06826   0.0545   0.0308   1.0000
  15.750   0.9615   0.07774   0.07230   0.0530   0.0294   1.0000
  16.000   0.9545   0.08199   0.07665   0.0513   0.0279   1.0000
  16.250   0.9468   0.08649   0.08122   0.0494   0.0267   1.0000
  16.500   0.9388   0.09111   0.08590   0.0475   0.0259   1.0000
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