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EPPLER 341 AIRFOIL (e341-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 341 AIRFOIL (e341-il)
Reynolds number: 1,000,000
Max Cl/Cd: 102.78 at α=10.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e341-il-1000000.txt
Download as CSV file: xf-e341-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 341 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3765   0.08362   0.08138  -0.0106   0.6936   0.0106
  -9.500  -0.3873   0.07754   0.07528  -0.0132   0.6843   0.0109
  -9.250  -0.4015   0.07089   0.06862  -0.0169   0.6770   0.0109
  -9.000  -0.4277   0.06297   0.06066  -0.0233   0.6726   0.0106
  -8.750  -0.4536   0.05719   0.05479  -0.0250   0.6656   0.0104
  -8.500  -0.4766   0.05250   0.05001  -0.0242   0.6572   0.0105
  -8.250  -0.4948   0.04828   0.04565  -0.0220   0.6480   0.0106
  -8.000  -0.5071   0.04379   0.04102  -0.0195   0.6388   0.0108
  -7.750  -0.5247   0.03385   0.03062  -0.0151   0.6363   0.0116
  -7.500  -0.5443   0.02702   0.02349  -0.0107   0.6296   0.0119
  -7.250  -0.5343   0.02501   0.02137  -0.0091   0.6170   0.0120
  -7.000  -0.5236   0.02288   0.01910  -0.0074   0.6057   0.0121
  -6.750  -0.5111   0.02090   0.01696  -0.0057   0.5948   0.0123
  -6.500  -0.4974   0.01893   0.01483  -0.0041   0.5838   0.0126
  -6.250  -0.4833   0.01679   0.01248  -0.0023   0.5735   0.0129
  -6.000  -0.4686   0.01447   0.00989  -0.0001   0.5641   0.0137
  -5.750  -0.4603   0.01085   0.00564   0.0039   0.5564   0.0152
  -5.500  -0.4391   0.00989   0.00462   0.0046   0.5465   0.0155
  -5.250  -0.4178   0.00901   0.00362   0.0055   0.5368   0.0159
  -5.000  -0.4135   0.01591   0.00924   0.0117   0.5390   0.0092
  -4.750  -0.3866   0.01557   0.00879   0.0121   0.5293   0.0090
  -4.500  -0.3600   0.01453   0.00766   0.0125   0.5195   0.0088
  -4.250  -0.3341   0.01362   0.00666   0.0130   0.5105   0.0087
  -4.000  -0.3088   0.01295   0.00590   0.0136   0.5011   0.0086
  -3.750  -0.2836   0.01240   0.00528   0.0143   0.4929   0.0086
  -3.500  -0.2586   0.01195   0.00476   0.0149   0.4845   0.0086
  -3.250  -0.2332   0.01157   0.00432   0.0155   0.4772   0.0087
  -3.000  -0.2078   0.01125   0.00394   0.0161   0.4694   0.0089
  -2.750  -0.1830   0.01084   0.00346   0.0168   0.4626   0.0093
  -2.500  -0.1574   0.01057   0.00316   0.0174   0.4552   0.0099
  -2.250  -0.1312   0.01039   0.00294   0.0178   0.4483   0.0113
  -2.000  -0.1052   0.01017   0.00270   0.0182   0.4416   0.0137
  -1.750  -0.0798   0.00995   0.00249   0.0188   0.4350   0.0264
  -1.500  -0.0549   0.00964   0.00235   0.0194   0.4299   0.0672
  -1.250  -0.0299   0.00939   0.00225   0.0199   0.4241   0.1173
  -1.000  -0.0109   0.00873   0.00209   0.0213   0.4184   0.2761
  -0.750  -0.0152   0.00682   0.00170   0.0272   0.4154   0.6856
  -0.500  -0.0027   0.00654   0.00208   0.0312   0.4108   0.8755
  -0.250   0.0226   0.00706   0.00259   0.0325   0.4055   0.8964
   0.000   0.0488   0.00746   0.00295   0.0333   0.4009   0.9065
   0.250   0.0770   0.00777   0.00323   0.0338   0.3967   0.9114
   0.500   0.1064   0.00830   0.00372   0.0343   0.3921   0.9185
   0.750   0.1326   0.00857   0.00392   0.0349   0.3871   0.9241
   1.000   0.1692   0.00895   0.00428   0.0337   0.3834   0.9269
   1.250   0.2042   0.00917   0.00445   0.0325   0.3793   0.9288
   1.500   0.2326   0.00921   0.00444   0.0323   0.3753   0.9300
   1.750   0.2592   0.00927   0.00443   0.0325   0.3707   0.9314
   2.000   0.2849   0.00925   0.00440   0.0329   0.3681   0.9332
   2.250   0.3070   0.00921   0.00434   0.0340   0.3652   0.9356
   2.500   0.3281   0.00919   0.00429   0.0351   0.3621   0.9377
   2.750   0.3555   0.00917   0.00423   0.0352   0.3588   0.9385
   3.000   0.3827   0.00921   0.00423   0.0352   0.3548   0.9391
   3.250   0.4108   0.00919   0.00421   0.0350   0.3524   0.9397
   3.500   0.4390   0.00920   0.00421   0.0349   0.3494   0.9403
   3.750   0.4667   0.00923   0.00422   0.0348   0.3462   0.9410
   4.000   0.4936   0.00928   0.00424   0.0348   0.3429   0.9417
   4.250   0.5201   0.00936   0.00429   0.0349   0.3394   0.9424
   4.500   0.5478   0.00937   0.00432   0.0348   0.3373   0.9432
   4.750   0.5748   0.00938   0.00433   0.0348   0.3346   0.9440
   5.000   0.6012   0.00940   0.00435   0.0349   0.3315   0.9448
   5.250   0.6271   0.00944   0.00438   0.0351   0.3284   0.9456
   5.500   0.6522   0.00953   0.00444   0.0354   0.3245   0.9465
   5.750   0.6787   0.00955   0.00449   0.0354   0.3224   0.9476
   6.000   0.7053   0.00956   0.00452   0.0354   0.3197   0.9485
   6.250   0.7321   0.00959   0.00456   0.0354   0.3164   0.9493
   6.500   0.7588   0.00965   0.00462   0.0353   0.3128   0.9500
   6.750   0.7852   0.00978   0.00472   0.0352   0.3087   0.9506
   7.000   0.8134   0.00981   0.00479   0.0348   0.3063   0.9511
   7.250   0.8405   0.00982   0.00484   0.0347   0.3031   0.9516
   7.500   0.8671   0.00988   0.00490   0.0347   0.2990   0.9521
   7.750   0.8927   0.01001   0.00501   0.0348   0.2945   0.9527
   8.000   0.9196   0.01006   0.00512   0.0347   0.2915   0.9534
   8.250   0.9465   0.01012   0.00521   0.0346   0.2873   0.9541
   8.500   0.9729   0.01024   0.00533   0.0345   0.2825   0.9547
   8.750   0.9992   0.01036   0.00547   0.0344   0.2778   0.9553
   9.000   1.0262   0.01044   0.00559   0.0342   0.2733   0.9560
   9.250   1.0522   0.01059   0.00574   0.0341   0.2673   0.9567
   9.500   1.0786   0.01073   0.00591   0.0340   0.2620   0.9574
   9.750   1.1049   0.01087   0.00607   0.0338   0.2560   0.9581
  10.000   1.1305   0.01108   0.00628   0.0337   0.2489   0.9590
  10.250   1.1565   0.01126   0.00648   0.0335   0.2411   0.9597
  10.500   1.1820   0.01150   0.00672   0.0334   0.2335   0.9605
  11.000   1.2316   0.01211   0.00731   0.0331   0.2126   0.9621
  11.250   1.2546   0.01246   0.00765   0.0333   0.2011   0.9629
  11.500   1.2743   0.01286   0.00803   0.0341   0.1892   0.9642
  11.750   1.2933   0.01333   0.00847   0.0349   0.1768   0.9655
  12.000   1.3118   0.01387   0.00898   0.0357   0.1639   0.9668
  12.250   1.3289   0.01449   0.00957   0.0366   0.1502   0.9683
  12.500   1.3448   0.01517   0.01021   0.0376   0.1373   0.9700
  12.750   1.3582   0.01588   0.01090   0.0388   0.1260   0.9720
  13.000   1.3651   0.01671   0.01171   0.0411   0.1151   0.9746
  13.250   1.3695   0.01773   0.01271   0.0434   0.1041   0.9779
  13.500   1.3741   0.01897   0.01394   0.0449   0.0941   0.9816
  13.750   1.3791   0.02041   0.01540   0.0458   0.0858   0.9864
  14.000   1.3847   0.02233   0.01734   0.0454   0.0778   0.9913
  14.250   1.3897   0.02487   0.01989   0.0439   0.0697   0.9959
  14.500   1.3975   0.02754   0.02260   0.0416   0.0634   0.9980
  14.750   1.3970   0.03056   0.02568   0.0401   0.0582   1.0000
  15.000   1.3942   0.03394   0.02911   0.0386   0.0537   1.0000
  15.250   1.3891   0.03760   0.03282   0.0371   0.0499   1.0000
  15.500   1.3833   0.04135   0.03663   0.0356   0.0466   1.0000
  15.750   1.3726   0.04561   0.04095   0.0342   0.0438   1.0000
  16.000   1.3642   0.04958   0.04501   0.0328   0.0415   1.0000
  16.250   1.3542   0.05374   0.04924   0.0315   0.0393   1.0000
  16.500   1.3425   0.05824   0.05380   0.0300   0.0372   1.0000
  16.750   1.3308   0.06278   0.05840   0.0284   0.0351   1.0000
  17.000   1.3231   0.06692   0.06262   0.0270   0.0334   1.0000
  17.250   1.3128   0.07140   0.06716   0.0254   0.0316   1.0000
  17.500   1.3008   0.07615   0.07196   0.0238   0.0298   1.0000
  17.750   1.2928   0.08045   0.07633   0.0223   0.0283   1.0000
  18.000   1.2860   0.08460   0.08054   0.0208   0.0267   1.0000
  18.250   1.2757   0.08927   0.08526   0.0191   0.0252   1.0000
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