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EPPLER 335 AIRFOIL (e335-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 335 AIRFOIL (e335-il)
Reynolds number: 1,000,000
Max Cl/Cd: 88.75 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e335-il-1000000-n5.txt
Download as CSV file: xf-e335-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 335 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5052   0.08643   0.08404  -0.0135   0.7201   0.0046
  -9.750  -0.5165   0.08056   0.07814  -0.0180   0.7026   0.0045
  -9.500  -0.5359   0.07450   0.07201  -0.0220   0.6885   0.0046
  -9.250  -0.5555   0.07006   0.06748  -0.0224   0.6751   0.0045
  -9.000  -0.5751   0.06637   0.06369  -0.0207   0.6612   0.0044
  -8.750  -0.5956   0.06297   0.06019  -0.0171   0.6498   0.0043
  -8.500  -0.6571   0.05196   0.04887  -0.0086   0.6512   0.0033
  -8.000  -0.6665   0.04291   0.03936  -0.0009   0.6293   0.0031
  -7.750  -0.7306   0.02350   0.01847   0.0143   0.6354   0.0028
  -7.500  -0.7156   0.02101   0.01555   0.0166   0.6225   0.0028
  -7.250  -0.6957   0.01954   0.01379   0.0180   0.6089   0.0028
  -7.000  -0.6745   0.01792   0.01186   0.0194   0.5944   0.0028
  -6.750  -0.6515   0.01690   0.01064   0.0203   0.5823   0.0028
  -6.500  -0.6277   0.01604   0.00961   0.0211   0.5714   0.0029
  -6.250  -0.6038   0.01525   0.00866   0.0220   0.5601   0.0029
  -6.000  -0.5795   0.01466   0.00794   0.0227   0.5484   0.0029
  -5.750  -0.5553   0.01406   0.00721   0.0235   0.5366   0.0030
  -5.500  -0.5311   0.01354   0.00658   0.0242   0.5264   0.0030
  -5.250  -0.5066   0.01315   0.00611   0.0249   0.5166   0.0030
  -5.000  -0.4820   0.01276   0.00563   0.0257   0.5078   0.0031
  -4.750  -0.4589   0.01216   0.00494   0.0267   0.4986   0.0034
  -4.500  -0.4341   0.01188   0.00461   0.0273   0.4892   0.0037
  -4.250  -0.4094   0.01163   0.00429   0.0280   0.4799   0.0038
  -4.000  -0.3842   0.01141   0.00403   0.0286   0.4714   0.0042
  -3.750  -0.3593   0.01118   0.00374   0.0293   0.4638   0.0043
  -3.500  -0.3341   0.01098   0.00350   0.0299   0.4563   0.0047
  -3.250  -0.3089   0.01080   0.00327   0.0305   0.4486   0.0050
  -3.000  -0.2839   0.01059   0.00303   0.0311   0.4410   0.0054
  -2.750  -0.2586   0.01045   0.00284   0.0317   0.4333   0.0061
  -2.500  -0.2330   0.01030   0.00266   0.0322   0.4270   0.0069
  -2.250  -0.2076   0.01016   0.00249   0.0328   0.4201   0.0084
  -2.000  -0.1822   0.01001   0.00235   0.0333   0.4139   0.0126
  -1.750  -0.1570   0.00986   0.00222   0.0339   0.4071   0.0227
  -1.500  -0.1325   0.00966   0.00210   0.0345   0.4014   0.0459
  -1.250  -0.1081   0.00944   0.00199   0.0352   0.3961   0.0810
  -1.000  -0.0842   0.00922   0.00190   0.0360   0.3901   0.1289
  -0.750  -0.0670   0.00857   0.00175   0.0379   0.3854   0.2835
  -0.500  -0.0860   0.00658   0.00134   0.0472   0.3827   0.7058
  -0.250  -0.0758   0.00622   0.00160   0.0516   0.3783   0.8706
   0.000  -0.0499   0.00641   0.00175   0.0523   0.3734   0.8885
   0.250  -0.0252   0.00655   0.00184   0.0532   0.3690   0.8984
   0.500   0.0050   0.00674   0.00200   0.0530   0.3636   0.9036
   0.750   0.0323   0.00695   0.00217   0.0533   0.3587   0.9103
   1.000   0.0587   0.00708   0.00226   0.0538   0.3549   0.9148
   1.250   0.0877   0.00714   0.00228   0.0536   0.3508   0.9159
   1.500   0.1159   0.00719   0.00228   0.0535   0.3461   0.9167
   1.750   0.1438   0.00725   0.00228   0.0535   0.3414   0.9174
   2.000   0.1720   0.00728   0.00229   0.0534   0.3383   0.9181
   2.250   0.2000   0.00732   0.00230   0.0533   0.3344   0.9189
   2.500   0.2276   0.00737   0.00232   0.0533   0.3299   0.9197
   2.750   0.2550   0.00743   0.00234   0.0533   0.3257   0.9204
   3.000   0.2828   0.00746   0.00236   0.0533   0.3228   0.9210
   3.250   0.3103   0.00750   0.00238   0.0533   0.3190   0.9218
   3.500   0.3375   0.00757   0.00242   0.0533   0.3143   0.9227
   3.750   0.3647   0.00764   0.00246   0.0533   0.3106   0.9235
   4.000   0.3921   0.00768   0.00250   0.0533   0.3071   0.9242
   4.250   0.4194   0.00773   0.00254   0.0533   0.3030   0.9249
   4.500   0.4464   0.00780   0.00259   0.0533   0.2987   0.9256
   4.750   0.4734   0.00787   0.00264   0.0534   0.2947   0.9263
   5.000   0.5007   0.00793   0.00271   0.0533   0.2907   0.9269
   5.250   0.5277   0.00801   0.00277   0.0533   0.2860   0.9275
   5.500   0.5544   0.00811   0.00286   0.0534   0.2813   0.9282
   5.750   0.5815   0.00818   0.00294   0.0534   0.2769   0.9288
   6.000   0.6087   0.00826   0.00302   0.0533   0.2715   0.9294
   6.250   0.6355   0.00838   0.00312   0.0533   0.2660   0.9301
   6.500   0.6627   0.00847   0.00323   0.0532   0.2605   0.9306
   6.750   0.6892   0.00860   0.00335   0.0533   0.2538   0.9312
   7.000   0.7159   0.00872   0.00348   0.0533   0.2482   0.9318
   7.250   0.7421   0.00887   0.00362   0.0533   0.2407   0.9325
   7.500   0.7683   0.00902   0.00378   0.0534   0.2340   0.9331
   7.750   0.7939   0.00921   0.00395   0.0535   0.2252   0.9338
   8.000   0.8196   0.00938   0.00413   0.0536   0.2172   0.9345
   8.250   0.8446   0.00960   0.00433   0.0539   0.2087   0.9353
   8.500   0.8693   0.00982   0.00454   0.0541   0.1982   0.9362
   8.750   0.8937   0.01007   0.00478   0.0544   0.1878   0.9370
   9.000   0.9171   0.01037   0.00505   0.0548   0.1759   0.9381
   9.250   0.9400   0.01068   0.00534   0.0553   0.1646   0.9393
   9.500   0.9620   0.01104   0.00566   0.0559   0.1517   0.9404
   9.750   0.9833   0.01144   0.00601   0.0566   0.1386   0.9415
  10.000   1.0036   0.01187   0.00640   0.0574   0.1250   0.9426
  10.250   1.0229   0.01234   0.00682   0.0584   0.1115   0.9437
  10.500   1.0408   0.01287   0.00731   0.0595   0.0967   0.9451
  10.750   1.0581   0.01340   0.00780   0.0608   0.0846   0.9466
  11.000   1.0748   0.01391   0.00830   0.0621   0.0753   0.9483
  11.250   1.0904   0.01443   0.00882   0.0636   0.0677   0.9502
  11.500   1.1047   0.01496   0.00935   0.0652   0.0603   0.9523
  11.750   1.1159   0.01547   0.00987   0.0675   0.0543   0.9550
  12.250   1.1317   0.01670   0.01115   0.0726   0.0441   0.9623
  12.500   1.1392   0.01756   0.01203   0.0745   0.0391   0.9668
  12.750   1.1454   0.01860   0.01309   0.0761   0.0340   0.9721
  13.000   1.1587   0.02010   0.01463   0.0752   0.0279   0.9757
  13.250   1.1711   0.02200   0.01655   0.0735   0.0224   0.9793
  13.500   1.1810   0.02430   0.01889   0.0714   0.0176   0.9831
  13.750   1.1965   0.02633   0.02098   0.0689   0.0161   0.9847
  14.000   1.2075   0.02899   0.02370   0.0660   0.0139   0.9863
  14.250   1.2179   0.03153   0.02634   0.0636   0.0128   0.9881
  14.500   1.2235   0.03451   0.02940   0.0612   0.0117   0.9904
  14.750   1.2253   0.03779   0.03275   0.0590   0.0103   0.9931
  15.000   1.2220   0.04155   0.03658   0.0570   0.0089   0.9991
  15.250   1.2217   0.04504   0.04015   0.0550   0.0083   1.0000
  15.500   1.2138   0.04811   0.04330   0.0550   0.0086   1.0000
  15.750   1.2048   0.05152   0.04679   0.0546   0.0082   1.0000
  16.000   1.1928   0.05543   0.05077   0.0539   0.0073   1.0000
  16.250   1.1807   0.05957   0.05496   0.0529   0.0065   1.0000
  16.500   1.1763   0.06293   0.05841   0.0521   0.0069   1.0000
  16.750   1.1665   0.06703   0.06258   0.0509   0.0062   1.0000
  17.000   1.1590   0.07092   0.06655   0.0497   0.0060   1.0000
  17.250   1.1497   0.07515   0.07084   0.0484   0.0054   1.0000
  17.500   1.1461   0.07865   0.07443   0.0472   0.0058   1.0000
  17.750   1.1348   0.08327   0.07910   0.0457   0.0049   1.0000
  18.000   1.1266   0.08754   0.08345   0.0441   0.0046   1.0000
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