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EPPLER 342 AIRFOIL (e342-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 342 AIRFOIL (e342-il)
Reynolds number: 500,000
Max Cl/Cd: 88.27 at α=10.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e342-il-500000.txt
Download as CSV file: xf-e342-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3737   0.08738   0.08530  -0.0330   1.0000   0.0172
  -9.500  -0.3752   0.08360   0.08155  -0.0345   1.0000   0.0173
  -9.250  -0.3860   0.07744   0.07540  -0.0401   1.0000   0.0173
  -9.000  -0.3923   0.07434   0.07231  -0.0405   1.0000   0.0174
  -8.750  -0.3680   0.06710   0.06492  -0.0523   0.9161   0.0175
  -8.500  -0.3605   0.06322   0.06055  -0.0556   0.8117   0.0177
  -8.250  -0.3747   0.06083   0.05792  -0.0523   0.7711   0.0178
  -8.000  -0.3820   0.05852   0.05542  -0.0496   0.7419   0.0180
  -7.750  -0.3854   0.05587   0.05258  -0.0473   0.7199   0.0181
  -7.500  -0.3859   0.05323   0.04976  -0.0450   0.7013   0.0184
  -7.250  -0.3845   0.05048   0.04682  -0.0427   0.6848   0.0188
  -7.000  -0.3823   0.04727   0.04337  -0.0399   0.6706   0.0196
  -6.750  -0.3890   0.04152   0.03705  -0.0344   0.6610   0.0207
  -6.500  -0.3777   0.03961   0.03504  -0.0329   0.6471   0.0210
  -6.250  -0.3654   0.03797   0.03327  -0.0311   0.6339   0.0212
  -6.000  -0.3521   0.03627   0.03142  -0.0293   0.6213   0.0217
  -5.750  -0.3381   0.03442   0.02938  -0.0273   0.6097   0.0223
  -5.500  -0.3303   0.03101   0.02532  -0.0226   0.6005   0.0248
  -5.250  -0.3117   0.02938   0.02365  -0.0216   0.5888   0.0252
  -5.000  -0.2930   0.02803   0.02215  -0.0202   0.5784   0.0258
  -4.750  -0.2736   0.02666   0.02057  -0.0186   0.5682   0.0272
  -4.500  -0.2500   0.01902   0.01169  -0.0138   0.5623   0.0138
  -4.250  -0.2227   0.01739   0.00992  -0.0135   0.5524   0.0133
  -4.000  -0.1943   0.01601   0.00832  -0.0132   0.5432   0.0128
  -3.750  -0.1674   0.01508   0.00724  -0.0127   0.5338   0.0125
  -3.500  -0.1419   0.01438   0.00643  -0.0120   0.5252   0.0125
  -3.250  -0.1178   0.01380   0.00576  -0.0111   0.5163   0.0128
  -3.000  -0.0942   0.01334   0.00524  -0.0101   0.5084   0.0132
  -2.750  -0.0707   0.01297   0.00478  -0.0090   0.5007   0.0140
  -2.500  -0.0484   0.01255   0.00435  -0.0078   0.4938   0.0159
  -2.250  -0.0250   0.01222   0.00399  -0.0068   0.4867   0.0180
  -2.000  -0.0016   0.01199   0.00370  -0.0058   0.4801   0.0216
  -1.750   0.0214   0.01164   0.00341  -0.0047   0.4738   0.0369
  -1.500   0.0423   0.01120   0.00324  -0.0033   0.4675   0.1001
  -1.250   0.0530   0.01022   0.00303  -0.0004   0.4623   0.3260
  -1.000   0.0414   0.00849   0.00336   0.0081   0.4588   0.8345
  -0.750   0.0598   0.00915   0.00400   0.0113   0.4535   0.8879
  -0.500   0.0928   0.01013   0.00487   0.0117   0.4479   0.9089
  -0.250   0.2027   0.01157   0.00612  -0.0037   0.4390   0.9159
   0.000   0.2589   0.01220   0.00660  -0.0088   0.4327   0.9261
   0.250   0.3240   0.01267   0.00693  -0.0159   0.4266   0.9319
   0.500   0.3406   0.01280   0.00703  -0.0135   0.4227   0.9393
   0.750   0.3764   0.01274   0.00690  -0.0153   0.4182   0.9403
   1.000   0.4106   0.01276   0.00680  -0.0167   0.4138   0.9416
   1.250   0.4433   0.01274   0.00675  -0.0178   0.4097   0.9433
   1.500   0.4740   0.01273   0.00671  -0.0185   0.4057   0.9453
   1.750   0.5009   0.01275   0.00669  -0.0184   0.4022   0.9480
   2.000   0.5146   0.01289   0.00678  -0.0156   0.3992   0.9527
   2.250   0.5480   0.01288   0.00671  -0.0170   0.3952   0.9536
   2.500   0.5812   0.01282   0.00665  -0.0182   0.3919   0.9548
   2.750   0.6126   0.01279   0.00661  -0.0191   0.3883   0.9562
   3.000   0.6418   0.01280   0.00659  -0.0196   0.3850   0.9577
   3.250   0.6689   0.01287   0.00661  -0.0197   0.3818   0.9597
   3.500   0.6921   0.01299   0.00669  -0.0189   0.3786   0.9619
   3.750   0.7089   0.01307   0.00681  -0.0168   0.3761   0.9647
   4.000   0.7414   0.01301   0.00676  -0.0180   0.3728   0.9655
   4.250   0.7716   0.01299   0.00674  -0.0187   0.3695   0.9664
   4.500   0.7999   0.01303   0.00675  -0.0191   0.3664   0.9674
   4.750   0.8282   0.01316   0.00684  -0.0195   0.3629   0.9685
   5.000   0.8558   0.01317   0.00691  -0.0197   0.3603   0.9700
   5.250   0.8806   0.01320   0.00698  -0.0193   0.3573   0.9711
   5.500   0.9039   0.01326   0.00705  -0.0186   0.3542   0.9724
   5.750   0.9248   0.01337   0.00716  -0.0175   0.3513   0.9742
   6.000   0.9423   0.01358   0.00734  -0.0156   0.3481   0.9754
   6.250   0.9700   0.01359   0.00740  -0.0159   0.3453   0.9760
   6.500   0.9983   0.01359   0.00746  -0.0164   0.3419   0.9766
   6.750   1.0270   0.01362   0.00753  -0.0169   0.3384   0.9775
   7.000   1.0529   0.01370   0.00762  -0.0168   0.3350   0.9783
   7.250   1.0768   0.01389   0.00779  -0.0164   0.3313   0.9789
   7.500   1.1006   0.01392   0.00792  -0.0160   0.3282   0.9797
   7.750   1.1245   0.01398   0.00804  -0.0155   0.3243   0.9806
   8.000   1.1483   0.01407   0.00817  -0.0151   0.3207   0.9817
   8.250   1.1690   0.01427   0.00834  -0.0140   0.3167   0.9825
   8.500   1.1892   0.01435   0.00852  -0.0128   0.3130   0.9833
   8.750   1.2083   0.01443   0.00868  -0.0115   0.3090   0.9841
   9.000   1.2248   0.01457   0.00885  -0.0095   0.3048   0.9852
   9.250   1.2498   0.01475   0.00903  -0.0095   0.3001   0.9860
   9.500   1.2744   0.01479   0.00920  -0.0093   0.2952   0.9866
   9.750   1.2972   0.01491   0.00936  -0.0089   0.2900   0.9872
  10.000   1.3187   0.01511   0.00958  -0.0082   0.2845   0.9879
  10.250   1.3409   0.01522   0.00980  -0.0076   0.2784   0.9887
  10.500   1.3602   0.01546   0.01004  -0.0065   0.2723   0.9897
  10.750   1.3805   0.01564   0.01032  -0.0056   0.2660   0.9906
  11.000   1.3990   0.01591   0.01062  -0.0045   0.2588   0.9919
  11.250   1.4172   0.01618   0.01096  -0.0033   0.2515   0.9932
  11.500   1.4307   0.01656   0.01134  -0.0013   0.2431   0.9944
  11.750   1.4512   0.01688   0.01173  -0.0008   0.2334   0.9953
  12.000   1.4680   0.01733   0.01221   0.0003   0.2231   0.9965
  12.250   1.4787   0.01787   0.01275   0.0023   0.2122   0.9982
  12.500   1.4868   0.01851   0.01340   0.0045   0.2016   1.0000
  12.750   1.4772   0.01903   0.01396   0.0103   0.1941   1.0000
  13.000   1.4600   0.01983   0.01477   0.0169   0.1877   1.0000
  13.250   1.4471   0.02062   0.01561   0.0223   0.1813   1.0000
  13.500   1.4268   0.02166   0.01669   0.0284   0.1762   1.0000
  13.750   1.4062   0.02287   0.01792   0.0341   0.1715   1.0000
  14.000   1.3953   0.02450   0.01958   0.0373   0.1642   1.0000
  14.250   1.3877   0.02666   0.02176   0.0389   0.1559   1.0000
  14.750   1.3709   0.03211   0.02726   0.0405   0.1396   1.0000
  15.000   1.3596   0.03538   0.03056   0.0408   0.1335   1.0000
  15.250   1.3487   0.03873   0.03395   0.0409   0.1258   1.0000
  15.500   1.3356   0.04240   0.03766   0.0408   0.1205   1.0000
  15.750   1.3237   0.04603   0.04134   0.0406   0.1142   1.0000
  16.000   1.3080   0.05022   0.04557   0.0401   0.1096   1.0000
  16.250   1.2975   0.05400   0.04940   0.0395   0.1036   1.0000
  16.500   1.2818   0.05850   0.05392   0.0386   0.0989   1.0000
  16.750   1.2737   0.06221   0.05770   0.0378   0.0943   1.0000
  17.000   1.2604   0.06667   0.06218   0.0366   0.0894   1.0000
  17.250   1.2512   0.07071   0.06628   0.0355   0.0856   1.0000
  17.500   1.2417   0.07486   0.07047   0.0343   0.0808   1.0000
  17.750   1.2297   0.07944   0.07506   0.0329   0.0770   1.0000
  18.000   1.2235   0.08335   0.07904   0.0316   0.0722   1.0000
  18.250   1.2137   0.08778   0.08349   0.0300   0.0690   1.0000
  18.500   1.2084   0.09166   0.08744   0.0286   0.0655   1.0000
  18.750   1.2010   0.09594   0.09176   0.0270   0.0620   1.0000
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