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EPPLER 342 AIRFOIL (e342-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 342 AIRFOIL (e342-il)
Reynolds number: 500,000
Max Cl/Cd: 83.67 at α=10°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e342-il-500000-n5.txt
Download as CSV file: xf-e342-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 342 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3168   0.08635   0.08302  -0.0426   0.6748   0.0122
  -9.250  -0.2976   0.06274   0.05947  -0.0460   0.6267   0.0087
  -8.750  -0.3970   0.06084   0.05726  -0.0526   0.6410   0.0087
  -8.500  -0.4077   0.05873   0.05506  -0.0499   0.6299   0.0086
  -8.250  -0.4162   0.05636   0.05258  -0.0471   0.6195   0.0085
  -8.000  -0.4213   0.05342   0.04951  -0.0447   0.6095   0.0083
  -7.750  -0.4227   0.05050   0.04641  -0.0422   0.5996   0.0082
  -7.250  -0.4545   0.03492   0.02997  -0.0309   0.5904   0.0064
  -6.750  -0.4475   0.02651   0.02065  -0.0232   0.5740   0.0062
  -6.500  -0.4348   0.02345   0.01710  -0.0204   0.5648   0.0061
  -6.250  -0.4162   0.02118   0.01442  -0.0186   0.5560   0.0060
  -6.000  -0.3943   0.01963   0.01253  -0.0173   0.5472   0.0060
  -5.750  -0.3704   0.01845   0.01112  -0.0165   0.5382   0.0060
  -5.500  -0.3460   0.01740   0.00984  -0.0157   0.5294   0.0061
  -5.250  -0.3210   0.01657   0.00884  -0.0150   0.5202   0.0061
  -5.000  -0.2964   0.01589   0.00801  -0.0143   0.5116   0.0061
  -4.750  -0.2717   0.01532   0.00733  -0.0136   0.5031   0.0062
  -4.500  -0.2475   0.01477   0.00666  -0.0128   0.4954   0.0063
  -4.250  -0.2231   0.01431   0.00613  -0.0120   0.4882   0.0064
  -4.000  -0.1998   0.01381   0.00554  -0.0110   0.4810   0.0067
  -3.750  -0.1757   0.01347   0.00514  -0.0102   0.4746   0.0068
  -3.500  -0.1516   0.01317   0.00479  -0.0094   0.4675   0.0070
  -3.250  -0.1275   0.01291   0.00447  -0.0086   0.4608   0.0076
  -3.000  -0.1029   0.01267   0.00419  -0.0079   0.4541   0.0080
  -2.750  -0.0786   0.01246   0.00391  -0.0071   0.4481   0.0089
  -2.500  -0.0543   0.01226   0.00367  -0.0063   0.4429   0.0104
  -2.250  -0.0296   0.01207   0.00346  -0.0056   0.4375   0.0120
  -2.000  -0.0050   0.01192   0.00328  -0.0049   0.4321   0.0146
  -1.750   0.0195   0.01178   0.00313  -0.0042   0.4272   0.0213
  -1.500   0.0435   0.01156   0.00301  -0.0034   0.4222   0.0417
  -1.250   0.0671   0.01136   0.00291  -0.0026   0.4169   0.0725
  -0.750   0.0959   0.00984   0.00260   0.0021   0.4094   0.4253
  -0.500   0.0895   0.00862   0.00305   0.0099   0.4066   0.8506
  -0.250   0.1087   0.00880   0.00316   0.0121   0.4026   0.8767
   0.000   0.1337   0.00911   0.00340   0.0131   0.3986   0.8901
   0.250   0.1648   0.00960   0.00383   0.0132   0.3947   0.9012
   0.500   0.1910   0.00989   0.00407   0.0140   0.3907   0.9102
   0.750   0.2320   0.01035   0.00447   0.0119   0.3862   0.9153
   1.000   0.2585   0.01049   0.00453   0.0123   0.3827   0.9192
   1.250   0.2721   0.01044   0.00442   0.0151   0.3798   0.9233
   1.500   0.2992   0.01044   0.00439   0.0153   0.3768   0.9242
   1.750   0.3274   0.01047   0.00437   0.0151   0.3735   0.9249
   2.000   0.3548   0.01051   0.00436   0.0152   0.3698   0.9257
   2.250   0.3819   0.01056   0.00437   0.0153   0.3666   0.9265
   2.500   0.4086   0.01064   0.00439   0.0154   0.3637   0.9274
   2.750   0.4351   0.01067   0.00440   0.0156   0.3611   0.9283
   3.000   0.4613   0.01070   0.00442   0.0158   0.3581   0.9293
   3.250   0.4871   0.01075   0.00444   0.0162   0.3548   0.9305
   3.500   0.5118   0.01079   0.00446   0.0167   0.3521   0.9317
   3.750   0.5356   0.01085   0.00448   0.0174   0.3493   0.9329
   4.000   0.5590   0.01089   0.00451   0.0181   0.3466   0.9342
   4.250   0.5827   0.01091   0.00454   0.0188   0.3441   0.9357
   4.500   0.6058   0.01094   0.00457   0.0196   0.3414   0.9372
   4.750   0.6289   0.01098   0.00460   0.0204   0.3386   0.9384
   5.000   0.6542   0.01104   0.00466   0.0207   0.3357   0.9391
   5.250   0.6799   0.01114   0.00474   0.0209   0.3327   0.9397
   5.500   0.7060   0.01122   0.00483   0.0210   0.3302   0.9403
   5.750   0.7322   0.01129   0.00492   0.0211   0.3272   0.9410
   6.000   0.7580   0.01137   0.00503   0.0213   0.3244   0.9417
   6.250   0.7834   0.01147   0.00514   0.0216   0.3214   0.9427
   6.500   0.8081   0.01159   0.00526   0.0220   0.3184   0.9437
   6.750   0.8324   0.01171   0.00539   0.0224   0.3153   0.9446
   7.000   0.8576   0.01179   0.00552   0.0226   0.3124   0.9456
   7.250   0.8822   0.01188   0.00565   0.0230   0.3092   0.9466
   7.500   0.9061   0.01199   0.00578   0.0234   0.3055   0.9477
   7.750   0.9291   0.01213   0.00592   0.0240   0.3021   0.9488
   8.000   0.9529   0.01225   0.00608   0.0245   0.2987   0.9500
   8.250   0.9768   0.01235   0.00623   0.0249   0.2947   0.9511
   8.500   0.9997   0.01248   0.00640   0.0255   0.2907   0.9522
   8.750   1.0224   0.01266   0.00658   0.0260   0.2865   0.9531
   9.000   1.0467   0.01280   0.00679   0.0264   0.2824   0.9540
   9.250   1.0700   0.01296   0.00700   0.0268   0.2773   0.9552
   9.500   1.0912   0.01318   0.00723   0.0276   0.2720   0.9568
   9.750   1.1139   0.01335   0.00747   0.0281   0.2671   0.9581
  10.000   1.1346   0.01356   0.00771   0.0290   0.2606   0.9597
  10.250   1.1539   0.01381   0.00798   0.0300   0.2547   0.9615
  10.500   1.1717   0.01402   0.00825   0.0314   0.2474   0.9635
  10.750   1.1887   0.01433   0.00858   0.0328   0.2405   0.9654
  11.000   1.2071   0.01469   0.00897   0.0338   0.2317   0.9672
  11.250   1.2247   0.01511   0.00942   0.0348   0.2229   0.9693
  11.500   1.2403   0.01564   0.00996   0.0360   0.2138   0.9719
  11.750   1.2565   0.01617   0.01052   0.0370   0.2045   0.9746
  12.000   1.2738   0.01685   0.01122   0.0374   0.1944   0.9769
  12.250   1.2899   0.01772   0.01210   0.0377   0.1835   0.9794
  12.500   1.3036   0.01878   0.01317   0.0379   0.1719   0.9830
  12.750   1.3159   0.02004   0.01444   0.0378   0.1609   0.9871
  13.000   1.3264   0.02153   0.01595   0.0375   0.1497   0.9921
  13.250   1.3365   0.02331   0.01776   0.0367   0.1396   0.9964
  13.500   1.3401   0.02551   0.01998   0.0361   0.1293   1.0000
  13.750   1.3293   0.02768   0.02217   0.0383   0.1232   1.0000
  14.000   1.3229   0.03006   0.02460   0.0394   0.1167   1.0000
  14.250   1.3153   0.03284   0.02741   0.0400   0.1113   1.0000
  14.500   1.3074   0.03580   0.03042   0.0403   0.1052   1.0000
  14.750   1.2972   0.03911   0.03377   0.0404   0.1001   1.0000
  15.000   1.2884   0.04238   0.03710   0.0404   0.0955   1.0000
  15.250   1.2748   0.04621   0.04096   0.0401   0.0897   1.0000
  15.500   1.2647   0.04981   0.04462   0.0398   0.0865   1.0000
  15.750   1.2537   0.05361   0.04848   0.0392   0.0811   1.0000
  16.000   1.2435   0.05748   0.05240   0.0385   0.0780   1.0000
  16.250   1.2338   0.06138   0.05635   0.0377   0.0732   1.0000
  16.500   1.2244   0.06534   0.06036   0.0367   0.0695   1.0000
  16.750   1.2158   0.06932   0.06438   0.0357   0.0667   1.0000
  17.000   1.2099   0.07301   0.06814   0.0346   0.0632   1.0000
  17.250   1.2015   0.07708   0.07224   0.0334   0.0598   1.0000
  17.500   1.1946   0.08107   0.07629   0.0322   0.0565   1.0000
  17.750   1.1897   0.08484   0.08011   0.0309   0.0539   1.0000
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