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EPPLER 343 AIRFOIL (e343-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 343 AIRFOIL (e343-il)
Reynolds number: 1,000,000
Max Cl/Cd: 113.42 at α=9°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e343-il-1000000-n5.txt
Download as CSV file: xf-e343-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.1823   0.09244   0.08931  -0.0438   0.5580   0.0073
  -9.500  -0.2517   0.07864   0.07535  -0.0592   0.5621   0.0065
  -9.000  -0.2053   0.06363   0.06047  -0.0548   0.5306   0.0060
  -8.500  -0.2427   0.05204   0.04887  -0.0626   0.5251   0.0057
  -7.500  -0.4626   0.02311   0.01793  -0.0388   0.5390   0.0041
  -7.250  -0.4537   0.01948   0.01373  -0.0356   0.5324   0.0040
  -7.000  -0.4339   0.01812   0.01211  -0.0342   0.5241   0.0041
  -6.750  -0.4128   0.01681   0.01055  -0.0329   0.5169   0.0041
  -6.500  -0.3898   0.01597   0.00952  -0.0320   0.5089   0.0041
  -6.250  -0.3665   0.01516   0.00854  -0.0310   0.5016   0.0042
  -6.000  -0.3424   0.01454   0.00780  -0.0303   0.4938   0.0042
  -5.500  -0.2933   0.01362   0.00665  -0.0289   0.4787   0.0043
  -5.250  -0.2687   0.01322   0.00616  -0.0282   0.4714   0.0044
  -5.000  -0.2455   0.01257   0.00541  -0.0272   0.4656   0.0046
  -4.750  -0.2207   0.01223   0.00501  -0.0265   0.4596   0.0047
  -4.500  -0.1958   0.01198   0.00470  -0.0259   0.4533   0.0050
  -4.250  -0.1706   0.01174   0.00443  -0.0253   0.4482   0.0052
  -4.000  -0.1454   0.01152   0.00416  -0.0247   0.4424   0.0054
  -3.750  -0.1203   0.01133   0.00392  -0.0240   0.4359   0.0057
  -3.500  -0.0949   0.01114   0.00369  -0.0235   0.4308   0.0060
  -3.250  -0.0695   0.01096   0.00347  -0.0229   0.4259   0.0061
  -3.000  -0.0440   0.01081   0.00328  -0.0223   0.4209   0.0064
  -2.750  -0.0188   0.01064   0.00307  -0.0217   0.4164   0.0066
  -2.500   0.0067   0.01047   0.00288  -0.0212   0.4127   0.0072
  -2.250   0.0325   0.01034   0.00274  -0.0207   0.4083   0.0077
  -2.000   0.0582   0.01024   0.00261  -0.0202   0.4037   0.0083
  -1.750   0.0839   0.01015   0.00249  -0.0197   0.3993   0.0095
  -1.500   0.1101   0.01005   0.00238  -0.0193   0.3959   0.0113
  -1.250   0.1360   0.00995   0.00229  -0.0188   0.3921   0.0150
  -1.000   0.1618   0.00986   0.00221  -0.0184   0.3883   0.0217
  -0.750   0.1873   0.00977   0.00215  -0.0179   0.3847   0.0348
  -0.500   0.2127   0.00964   0.00210  -0.0174   0.3819   0.0595
  -0.250   0.2380   0.00949   0.00205  -0.0169   0.3791   0.0946
   0.000   0.2610   0.00919   0.00201  -0.0160   0.3758   0.1843
   0.250   0.2442   0.00688   0.00186  -0.0074   0.3738   0.8217
   0.500   0.2684   0.00709   0.00212  -0.0063   0.3702   0.8705
   1.000   0.3212   0.00740   0.00235  -0.0053   0.3650   0.8908
   1.250   0.3474   0.00751   0.00244  -0.0048   0.3625   0.8978
   1.500   0.3733   0.00760   0.00250  -0.0043   0.3597   0.9046
   1.750   0.4004   0.00764   0.00251  -0.0040   0.3564   0.9071
   2.000   0.4282   0.00770   0.00252  -0.0041   0.3535   0.9077
   2.250   0.4558   0.00777   0.00254  -0.0041   0.3505   0.9084
   2.500   0.4840   0.00780   0.00255  -0.0042   0.3487   0.9092
   2.750   0.5120   0.00785   0.00257  -0.0043   0.3461   0.9098
   3.000   0.5400   0.00790   0.00260  -0.0044   0.3435   0.9104
   3.250   0.5678   0.00796   0.00263  -0.0045   0.3410   0.9110
   3.500   0.5954   0.00804   0.00268  -0.0046   0.3382   0.9116
   3.750   0.6227   0.00813   0.00273  -0.0046   0.3351   0.9122
   4.000   0.6506   0.00819   0.00279  -0.0048   0.3331   0.9127
   4.250   0.6784   0.00825   0.00284  -0.0049   0.3311   0.9133
   4.500   0.7061   0.00832   0.00290  -0.0050   0.3286   0.9140
   4.750   0.7335   0.00839   0.00297  -0.0051   0.3257   0.9146
   5.000   0.7606   0.00848   0.00304  -0.0051   0.3232   0.9151
   5.250   0.7874   0.00858   0.00313  -0.0051   0.3204   0.9156
   5.500   0.8145   0.00866   0.00321  -0.0051   0.3178   0.9161
   5.750   0.8418   0.00873   0.00330  -0.0052   0.3158   0.9166
   6.000   0.8689   0.00882   0.00340  -0.0053   0.3130   0.9172
   6.250   0.8956   0.00891   0.00350  -0.0053   0.3097   0.9177
   6.500   0.9219   0.00903   0.00361  -0.0052   0.3064   0.9183
   6.750   0.9480   0.00916   0.00374  -0.0051   0.3030   0.9189
   7.000   0.9748   0.00925   0.00385  -0.0052   0.3004   0.9195
   7.250   1.0013   0.00935   0.00397  -0.0051   0.2968   0.9201
   7.500   1.0272   0.00948   0.00411  -0.0051   0.2932   0.9207
   7.750   1.0523   0.00965   0.00426  -0.0048   0.2888   0.9214
   8.000   1.0783   0.00976   0.00440  -0.0048   0.2856   0.9220
   8.250   1.1040   0.00989   0.00456  -0.0047   0.2813   0.9226
   8.500   1.1286   0.01007   0.00473  -0.0044   0.2762   0.9234
   8.750   1.1529   0.01023   0.00491  -0.0040   0.2716   0.9243
   9.000   1.1773   0.01038   0.00509  -0.0037   0.2665   0.9252
   9.250   1.1998   0.01061   0.00531  -0.0031   0.2597   0.9260
   9.500   1.2232   0.01080   0.00552  -0.0027   0.2537   0.9268
   9.750   1.2447   0.01106   0.00578  -0.0019   0.2459   0.9277
  10.000   1.2667   0.01128   0.00602  -0.0012   0.2399   0.9287
  10.250   1.2855   0.01162   0.00634   0.0000   0.2299   0.9298
  10.500   1.3054   0.01190   0.00663   0.0010   0.2220   0.9310
  11.000   1.3334   0.01262   0.00735   0.0053   0.2039   0.9346
  11.250   1.3461   0.01299   0.00775   0.0076   0.1961   0.9370
  11.500   1.3541   0.01351   0.00826   0.0107   0.1858   0.9401
  11.750   1.3613   0.01403   0.00878   0.0139   0.1763   0.9462
  12.000   1.3714   0.01462   0.00936   0.0161   0.1664   0.9569
  12.250   1.3786   0.01531   0.01003   0.0187   0.1569   0.9633
  12.500   1.3814   0.01614   0.01084   0.0218   0.1469   0.9687
  12.750   1.3881   0.01697   0.01168   0.0239   0.1382   0.9725
  13.000   1.3931   0.01808   0.01279   0.0258   0.1286   0.9765
  13.250   1.4018   0.01946   0.01418   0.0262   0.1194   0.9801
  13.500   1.4127   0.02102   0.01575   0.0258   0.1112   0.9833
  14.000   1.4282   0.02506   0.01983   0.0244   0.0949   1.0000
  14.250   1.4252   0.02737   0.02216   0.0252   0.0890   1.0000
  14.500   1.4177   0.03022   0.02503   0.0258   0.0816   1.0000
  14.750   1.4145   0.03280   0.02767   0.0262   0.0783   1.0000
  15.000   1.4020   0.03634   0.03124   0.0265   0.0712   1.0000
  15.250   1.3980   0.03916   0.03412   0.0266   0.0692   1.0000
  15.500   1.3875   0.04267   0.03768   0.0266   0.0659   1.0000
  15.750   1.3826   0.04569   0.04077   0.0264   0.0639   1.0000
  16.000   1.3558   0.05113   0.04621   0.0260   0.0547   1.0000
  16.250   1.3596   0.05341   0.04860   0.0257   0.0575   1.0000
  16.500   1.3324   0.05921   0.05438   0.0248   0.0478   1.0000
  16.750   1.3259   0.06279   0.05802   0.0242   0.0459   1.0000
  17.000   1.3170   0.06672   0.06201   0.0234   0.0436   1.0000
  17.250   1.3173   0.06958   0.06497   0.0227   0.0440   1.0000
  17.500   1.3033   0.07424   0.06964   0.0216   0.0394   1.0000
  17.750   1.2907   0.07886   0.07429   0.0203   0.0358   1.0000
  18.000   1.2865   0.08247   0.07797   0.0193   0.0348   1.0000
  18.250   1.2751   0.08704   0.08256   0.0179   0.0303   1.0000
  18.500   1.2677   0.09121   0.08677   0.0165   0.0281   1.0000
  18.750   1.2679   0.09437   0.09000   0.0154   0.0281   1.0000
  19.000   1.2642   0.09813   0.09383   0.0141   0.0274   1.0000
  19.250   1.2554   0.10260   0.09832   0.0124   0.0240   1.0000
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