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EPPLER 593 AIRFOIL (e593-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 593 AIRFOIL (e593-il)
Reynolds number: 1,000,000
Max Cl/Cd: 140.64 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e593-il-1000000-n5.txt
Download as CSV file: xf-e593-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 593 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4273   0.12708   0.12366   0.0190   0.4624   0.0049
  -9.000  -0.6683   0.02771   0.02333  -0.0379   0.4650   0.0036
  -8.750  -0.6501   0.02468   0.01997  -0.0382   0.4637   0.0036
  -8.500  -0.6290   0.02260   0.01762  -0.0382   0.4623   0.0036
  -8.250  -0.6062   0.02098   0.01577  -0.0380   0.4605   0.0036
  -8.000  -0.5825   0.01958   0.01415  -0.0377   0.4586   0.0037
  -7.750  -0.5578   0.01847   0.01285  -0.0374   0.4566   0.0037
  -7.500  -0.5326   0.01746   0.01166  -0.0371   0.4545   0.0037
  -7.250  -0.5069   0.01658   0.01062  -0.0368   0.4526   0.0037
  -7.000  -0.4807   0.01581   0.00968  -0.0365   0.4507   0.0037
  -6.750  -0.4542   0.01512   0.00887  -0.0362   0.4492   0.0037
  -6.500  -0.4274   0.01449   0.00812  -0.0360   0.4481   0.0037
  -6.250  -0.4004   0.01392   0.00745  -0.0357   0.4468   0.0038
  -6.000  -0.3731   0.01340   0.00684  -0.0354   0.4453   0.0038
  -5.750  -0.3457   0.01292   0.00627  -0.0352   0.4437   0.0038
  -5.500  -0.3183   0.01236   0.00560  -0.0349   0.4420   0.0039
  -5.250  -0.2907   0.01191   0.00506  -0.0347   0.4401   0.0040
  -5.000  -0.2629   0.01153   0.00460  -0.0344   0.4384   0.0042
  -4.750  -0.2350   0.01121   0.00421  -0.0342   0.4368   0.0044
  -4.500  -0.2069   0.01094   0.00388  -0.0340   0.4352   0.0046
  -4.250  -0.1788   0.01070   0.00358  -0.0339   0.4338   0.0049
  -4.000  -0.1505   0.01047   0.00332  -0.0337   0.4329   0.0053
  -3.750  -0.1222   0.01023   0.00305  -0.0335   0.4317   0.0061
  -3.500  -0.0939   0.01001   0.00281  -0.0333   0.4304   0.0075
  -3.250  -0.0657   0.00979   0.00259  -0.0332   0.4289   0.0106
  -3.000  -0.0374   0.00959   0.00240  -0.0330   0.4273   0.0163
  -2.750  -0.0091   0.00942   0.00224  -0.0329   0.4257   0.0216
  -2.500   0.0193   0.00928   0.00210  -0.0328   0.4243   0.0276
  -2.250   0.0477   0.00915   0.00198  -0.0327   0.4229   0.0346
  -2.000   0.0760   0.00899   0.00188  -0.0326   0.4215   0.0471
  -1.750   0.1044   0.00889   0.00180  -0.0325   0.4200   0.0576
  -1.500   0.1329   0.00880   0.00173  -0.0324   0.4187   0.0677
  -1.250   0.1615   0.00871   0.00167  -0.0324   0.4177   0.0764
  -1.000   0.1901   0.00864   0.00161  -0.0323   0.4165   0.0840
  -0.750   0.2188   0.00856   0.00156  -0.0323   0.4151   0.0938
  -0.500   0.2474   0.00849   0.00152  -0.0322   0.4137   0.1040
  -0.250   0.2760   0.00845   0.00149  -0.0322   0.4123   0.1135
   0.000   0.3047   0.00840   0.00146  -0.0321   0.4110   0.1237
   0.250   0.3333   0.00835   0.00144  -0.0321   0.4096   0.1369
   0.500   0.3618   0.00831   0.00142  -0.0321   0.4083   0.1527
   0.750   0.3904   0.00827   0.00142  -0.0321   0.4068   0.1707
   1.000   0.4188   0.00822   0.00143  -0.0320   0.4051   0.1975
   1.250   0.4473   0.00816   0.00145  -0.0320   0.4037   0.2277
   1.750   0.5039   0.00794   0.00151  -0.0321   0.4015   0.3310
   2.000   0.5236   0.00664   0.00160  -0.0307   0.4004   0.8193
   2.500   0.6049   0.00640   0.00167  -0.0357   0.3970   1.0000
   2.750   0.6323   0.00646   0.00170  -0.0354   0.3954   1.0000
   3.000   0.6598   0.00653   0.00175  -0.0352   0.3938   1.0000
   3.250   0.6873   0.00660   0.00179  -0.0350   0.3921   1.0000
   3.500   0.7148   0.00669   0.00185  -0.0348   0.3901   1.0000
   3.750   0.7425   0.00675   0.00191  -0.0347   0.3886   1.0000
   4.000   0.7703   0.00680   0.00198  -0.0345   0.3865   1.0000
   4.250   0.7980   0.00686   0.00204  -0.0344   0.3838   1.0000
   4.500   0.8258   0.00693   0.00210  -0.0343   0.3809   1.0000
   4.750   0.8535   0.00701   0.00216  -0.0342   0.3780   1.0000
   5.000   0.8812   0.00711   0.00225  -0.0342   0.3752   1.0000
   5.250   0.9091   0.00717   0.00234  -0.0341   0.3727   1.0000
   5.500   0.9370   0.00725   0.00242  -0.0341   0.3693   1.0000
   5.750   0.9647   0.00734   0.00251  -0.0340   0.3652   1.0000
   6.000   0.9924   0.00745   0.00261  -0.0340   0.3611   1.0000
   6.250   1.0202   0.00753   0.00272  -0.0340   0.3574   1.0000
   6.500   1.0479   0.00764   0.00284  -0.0340   0.3528   1.0000
   6.750   1.0754   0.00778   0.00297  -0.0339   0.3476   1.0000
   7.000   1.1031   0.00788   0.00311  -0.0339   0.3420   1.0000
   7.250   1.1302   0.00806   0.00326  -0.0339   0.3333   1.0000
   7.500   1.1575   0.00823   0.00343  -0.0339   0.3231   1.0000
   7.750   1.1844   0.00845   0.00364  -0.0339   0.3116   1.0000
   8.000   1.2107   0.00876   0.00389  -0.0339   0.2958   1.0000
   8.250   1.2361   0.00921   0.00425  -0.0338   0.2742   1.0000
   8.500   1.2607   0.00976   0.00470  -0.0336   0.2506   1.0000
   8.750   1.2847   0.01037   0.00521  -0.0335   0.2262   1.0000
   9.000   1.3082   0.01102   0.00577  -0.0333   0.2035   1.0000
   9.250   1.3316   0.01166   0.00632  -0.0331   0.1832   1.0000
   9.500   1.3545   0.01231   0.00690  -0.0328   0.1653   1.0000
   9.750   1.3770   0.01299   0.00750  -0.0326   0.1473   1.0000
  10.000   1.3988   0.01369   0.00814  -0.0323   0.1311   1.0000
  10.250   1.4201   0.01442   0.00882  -0.0319   0.1167   1.0000
  10.500   1.4406   0.01517   0.00952  -0.0315   0.1039   1.0000
  10.750   1.4589   0.01609   0.01037  -0.0310   0.0892   1.0000
  11.250   1.4937   0.01787   0.01210  -0.0297   0.0691   1.0000
  11.500   1.5092   0.01881   0.01305  -0.0290   0.0617   1.0000
  11.750   1.5211   0.01994   0.01418  -0.0280   0.0551   1.0000
  12.000   1.5296   0.02122   0.01549  -0.0269   0.0503   1.0000
  12.250   1.5161   0.02422   0.01859  -0.0259   0.0464   1.0000
  12.500   1.5142   0.02745   0.02191  -0.0269   0.0447   1.0000
  12.750   1.5057   0.03114   0.02565  -0.0275   0.0414   1.0000
  13.000   1.4994   0.03440   0.02896  -0.0276   0.0395   1.0000
  13.250   1.4917   0.03772   0.03234  -0.0277   0.0366   1.0000
  13.500   1.4800   0.04141   0.03606  -0.0277   0.0332   1.0000
  13.750   1.4732   0.04465   0.03934  -0.0279   0.0306   1.0000
  14.000   1.4618   0.04838   0.04308  -0.0281   0.0267   1.0000
  14.250   1.4597   0.05116   0.04591  -0.0282   0.0258   1.0000
  14.500   1.4532   0.05457   0.04935  -0.0286   0.0231   1.0000
  14.750   1.4485   0.05791   0.05271  -0.0291   0.0199   1.0000
  15.000   1.4500   0.06066   0.05553  -0.0295   0.0197   1.0000
  15.250   1.4496   0.06365   0.05856  -0.0300   0.0185   1.0000
  15.500   1.4473   0.06698   0.06193  -0.0307   0.0166   1.0000
  15.750   1.4461   0.07019   0.06517  -0.0314   0.0148   1.0000
  16.000   1.4459   0.07336   0.06840  -0.0322   0.0143   1.0000
  16.250   1.4431   0.07689   0.07195  -0.0330   0.0118   1.0000
  16.500   1.4436   0.08010   0.07523  -0.0339   0.0116   1.0000
  16.750   1.4434   0.08340   0.07857  -0.0348   0.0105   1.0000
  17.000   1.4425   0.08686   0.08209  -0.0358   0.0096   1.0000
  17.250   1.4409   0.09049   0.08577  -0.0370   0.0089   1.0000
  17.500   1.4405   0.09399   0.08932  -0.0381   0.0080   1.0000
  17.750   1.4386   0.09776   0.09316  -0.0394   0.0074   1.0000
  18.000   1.4377   0.10144   0.09689  -0.0407   0.0070   1.0000
  18.250   1.4359   0.10534   0.10087  -0.0422   0.0067   1.0000
  18.500   1.4352   0.10905   0.10464  -0.0437   0.0061   1.0000
  18.750   1.4330   0.11311   0.10878  -0.0453   0.0059   1.0000
  19.000   1.4313   0.11708   0.11281  -0.0470   0.0054   1.0000
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