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EPPLER 343 AIRFOIL (e343-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 343 AIRFOIL (e343-il)
Reynolds number: 100,000
Max Cl/Cd: 30.84 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e343-il-100000.txt
Download as CSV file: xf-e343-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 343 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3232   0.11804   0.11336  -0.0310   1.0000   0.0718
 -10.250  -0.3348   0.11535   0.11076  -0.0351   1.0000   0.0722
 -10.000  -0.3453   0.11215   0.10763  -0.0391   1.0000   0.0724
  -9.750  -0.3005   0.10640   0.10189  -0.0306   1.0000   0.0757
  -9.500  -0.2952   0.10332   0.09886  -0.0309   1.0000   0.0777
  -9.250  -0.2943   0.10016   0.09577  -0.0319   1.0000   0.0802
  -9.000  -0.2968   0.09701   0.09271  -0.0336   1.0000   0.0821
  -8.750  -0.2195   0.08573   0.08208  -0.0364   1.0000   0.0900
  -8.500  -0.2217   0.08303   0.07953  -0.0359   1.0000   0.0924
  -8.250  -0.2218   0.07909   0.07571  -0.0395   0.9864   0.0958
  -8.000  -0.2330   0.07241   0.06902  -0.0503   0.9573   0.0991
  -7.750  -0.3959   0.08366   0.07981  -0.0398   0.9849   0.0863
  -7.500  -0.3421   0.07747   0.07387  -0.0408   0.9768   0.0908
  -7.250  -0.3188   0.07226   0.06850  -0.0486   0.9419   0.0973
  -7.000  -0.3088   0.06705   0.06289  -0.0557   0.9136   0.1025
  -6.750  -0.2696   0.06220   0.05807  -0.0589   0.8879   0.1088
  -6.500  -0.2755   0.06072   0.05591  -0.0591   0.8585   0.1182
  -6.250  -0.2482   0.05604   0.05141  -0.0595   0.8331   0.1245
  -6.000  -0.2518   0.05491   0.04975  -0.0572   0.8115   0.1358
  -5.750  -0.2309   0.05147   0.04642  -0.0565   0.7917   0.1442
  -5.500  -0.2240   0.04926   0.04402  -0.0545   0.7742   0.1589
  -5.250  -0.2163   0.04725   0.04184  -0.0523   0.7580   0.1754
  -5.000  -0.2063   0.04525   0.03972  -0.0501   0.7431   0.1941
  -4.750  -0.1949   0.04338   0.03775  -0.0479   0.7298   0.2152
  -4.000  -0.1212   0.03396   0.02587  -0.0412   0.6980   0.0888
  -3.750  -0.0942   0.03130   0.02262  -0.0389   0.6864   0.0693
  -3.500  -0.0682   0.02906   0.01985  -0.0373   0.6765   0.0631
  -3.250  -0.0412   0.02809   0.01838  -0.0358   0.6663   0.0606
  -3.000  -0.0129   0.02641   0.01651  -0.0353   0.6564   0.0615
  -2.750   0.0159   0.02510   0.01517  -0.0352   0.6472   0.0660
  -2.500   0.0452   0.02413   0.01407  -0.0348   0.6374   0.0697
  -2.250   0.0760   0.02291   0.01278  -0.0346   0.6291   0.0746
  -2.000   0.3638   0.01995   0.01213  -0.0743   0.6089   1.0000
  -1.750   0.3840   0.02000   0.01207  -0.0735   0.5999   1.0000
  -1.500   0.4052   0.02005   0.01187  -0.0726   0.5932   1.0000
  -1.250   0.4261   0.02018   0.01188  -0.0718   0.5862   1.0000
  -1.000   0.4472   0.02031   0.01188  -0.0710   0.5794   1.0000
  -0.750   0.4691   0.02044   0.01180  -0.0702   0.5742   1.0000
  -0.500   0.4900   0.02067   0.01198  -0.0694   0.5675   1.0000
  -0.250   0.5114   0.02085   0.01205  -0.0686   0.5613   1.0000
   0.000   0.5337   0.02102   0.01204  -0.0678   0.5564   1.0000
   0.250   0.5545   0.02135   0.01236  -0.0670   0.5506   1.0000
   0.500   0.5757   0.02164   0.01261  -0.0662   0.5451   1.0000
   0.750   0.5979   0.02187   0.01272  -0.0654   0.5406   1.0000
   1.000   0.6196   0.02220   0.01297  -0.0646   0.5360   1.0000
   1.250   0.6396   0.02262   0.01344  -0.0637   0.5301   1.0000
   1.500   0.6611   0.02294   0.01371  -0.0629   0.5254   1.0000
   1.750   0.6837   0.02323   0.01390  -0.0621   0.5218   1.0000
   2.000   0.7036   0.02378   0.01447  -0.0612   0.5173   1.0000
   2.250   0.7226   0.02433   0.01509  -0.0602   0.5119   1.0000
   2.500   0.7439   0.02469   0.01542  -0.0593   0.5075   1.0000
   2.750   0.7665   0.02500   0.01564  -0.0585   0.5041   1.0000
   3.000   0.7845   0.02575   0.01648  -0.0574   0.4999   1.0000
   3.250   0.8008   0.02654   0.01739  -0.0560   0.4947   1.0000
   3.500   0.8210   0.02701   0.01785  -0.0550   0.4906   1.0000
   3.750   0.8433   0.02734   0.01811  -0.0542   0.4872   1.0000
   4.000   0.8609   0.02815   0.01897  -0.0529   0.4837   1.0000
   4.250   0.8706   0.02946   0.02049  -0.0510   0.4782   1.0000
   4.500   0.8881   0.03009   0.02116  -0.0496   0.4738   1.0000
   4.750   0.9106   0.03041   0.02143  -0.0487   0.4706   1.0000
   5.000   0.9340   0.03082   0.02176  -0.0480   0.4679   1.0000
   5.250   0.9274   0.03322   0.02452  -0.0444   0.4615   1.0000
   5.500   0.9396   0.03419   0.02558  -0.0425   0.4569   1.0000
   5.750   0.9624   0.03441   0.02578  -0.0415   0.4537   1.0000
   6.000   0.9893   0.03454   0.02583  -0.0411   0.4512   1.0000
   6.250   0.9553   0.03867   0.03035  -0.0348   0.4438   1.0000
   6.500   0.9598   0.04001   0.03177  -0.0321   0.4392   1.0000
   6.750   0.9890   0.03973   0.03147  -0.0316   0.4363   1.0000
   7.000   1.0271   0.03911   0.03076  -0.0321   0.4340   1.0000
   7.250   0.7655   0.05655   0.04857  -0.0081   0.4192   1.0000
   7.500   0.8892   0.05042   0.04246  -0.0135   0.4191   1.0000
   7.750   0.9729   0.04685   0.03889  -0.0174   0.4180   1.0000
   8.000   0.6661   0.07036   0.06231   0.0001   0.4017   1.0000
   8.250   0.7369   0.06638   0.05839   0.0012   0.4000   1.0000
   8.500   0.5953   0.08147   0.07343   0.0018   0.3926   1.0000
   8.750   0.6183   0.08181   0.07377   0.0029   0.3868   1.0000
   9.000   0.6345   0.08289   0.07489   0.0040   0.3809   1.0000
   9.250   0.6046   0.08866   0.08068   0.0035   0.3786   1.0000
   9.500   0.5934   0.09256   0.08461   0.0034   0.3755   1.0000
   9.750   0.6001   0.09496   0.08705   0.0036   0.3717   1.0000
  10.000   0.6035   0.09810   0.09022   0.0034   0.3704   1.0000
  10.250   0.6062   0.10144   0.09360   0.0031   0.3696   1.0000
  10.500   0.6157   0.10448   0.09668   0.0029   0.3685   1.0000
  10.750   0.6084   0.11178   0.10405   0.0007   0.3827   1.0000
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