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EPPLER 593 AIRFOIL (e593-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 593 AIRFOIL (e593-il)
Reynolds number: 200,000
Max Cl/Cd: 74.23 at α=10°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e593-il-200000-n5.txt
Download as CSV file: xf-e593-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3917   0.11438   0.10941   0.0109   0.5237   0.0159
  -9.500  -0.3828   0.11145   0.10647   0.0101   0.5214   0.0154
  -9.000  -0.3829   0.10126   0.09630   0.0051   0.5187   0.0129
  -8.750  -0.3777   0.09795   0.09299   0.0036   0.5170   0.0128
  -8.500  -0.3731   0.09457   0.08960   0.0020   0.5154   0.0126
  -8.250  -0.3689   0.09122   0.08624   0.0004   0.5139   0.0124
  -8.000  -0.3674   0.08728   0.08232  -0.0016   0.5126   0.0123
  -7.750  -0.3654   0.08368   0.07875  -0.0035   0.5110   0.0121
  -7.500  -0.3668   0.07972   0.07484  -0.0057   0.5095   0.0119
  -7.250  -0.3706   0.07550   0.07066  -0.0086   0.5081   0.0118
  -7.000  -0.3697   0.07017   0.06534  -0.0134   0.5066   0.0116
  -6.750  -0.4192   0.03292   0.02677  -0.0375   0.5105   0.0101
  -6.500  -0.4015   0.02815   0.02124  -0.0382   0.5085   0.0102
  -6.250  -0.3788   0.02609   0.01885  -0.0382   0.5060   0.0105
  -6.000  -0.3546   0.02449   0.01695  -0.0381   0.5035   0.0108
  -5.750  -0.3296   0.02307   0.01523  -0.0379   0.5011   0.0113
  -5.500  -0.3041   0.02176   0.01359  -0.0376   0.4990   0.0119
  -5.250  -0.2781   0.02060   0.01210  -0.0372   0.4971   0.0126
  -5.000  -0.2516   0.01972   0.01108  -0.0370   0.4950   0.0135
  -4.750  -0.2245   0.01909   0.01031  -0.0368   0.4928   0.0153
  -4.500  -0.1974   0.01847   0.00959  -0.0366   0.4906   0.0175
  -4.250  -0.1701   0.01781   0.00877  -0.0363   0.4885   0.0203
  -4.000  -0.1428   0.01722   0.00806  -0.0361   0.4865   0.0240
  -3.750  -0.1154   0.01679   0.00758  -0.0359   0.4845   0.0303
  -3.500  -0.0878   0.01646   0.00717  -0.0357   0.4826   0.0382
  -3.250  -0.0600   0.01622   0.00687  -0.0355   0.4808   0.0473
  -3.000  -0.0320   0.01599   0.00663  -0.0354   0.4788   0.0564
  -2.750  -0.0041   0.01576   0.00639  -0.0352   0.4769   0.0651
  -2.500   0.0239   0.01554   0.00615  -0.0350   0.4750   0.0739
  -2.250   0.0518   0.01537   0.00593  -0.0349   0.4731   0.0832
  -2.000   0.0798   0.01523   0.00574  -0.0347   0.4712   0.0934
  -1.750   0.1076   0.01507   0.00556  -0.0346   0.4694   0.1039
  -1.500   0.1354   0.01493   0.00539  -0.0344   0.4677   0.1151
  -1.250   0.1633   0.01484   0.00524  -0.0342   0.4661   0.1274
  -1.000   0.1912   0.01476   0.00516  -0.0341   0.4645   0.1411
  -0.750   0.2192   0.01467   0.00512  -0.0340   0.4627   0.1574
  -0.500   0.2470   0.01457   0.00510  -0.0339   0.4609   0.1772
  -0.250   0.2748   0.01448   0.00509  -0.0339   0.4591   0.2042
   0.000   0.3024   0.01436   0.00509  -0.0338   0.4572   0.2423
   0.500   0.3538   0.01354   0.00508  -0.0331   0.4537   0.4993
   0.750   0.4083   0.01245   0.00507  -0.0377   0.4519   1.0000
   1.000   0.4352   0.01260   0.00509  -0.0374   0.4506   1.0000
   1.250   0.4622   0.01278   0.00517  -0.0371   0.4493   1.0000
   1.500   0.4893   0.01295   0.00532  -0.0369   0.4475   1.0000
   1.750   0.5164   0.01313   0.00546  -0.0367   0.4454   1.0000
   2.000   0.5436   0.01330   0.00560  -0.0364   0.4433   1.0000
   2.250   0.5707   0.01346   0.00572  -0.0362   0.4413   1.0000
   2.500   0.5979   0.01364   0.00585  -0.0360   0.4397   1.0000
   2.750   0.6251   0.01381   0.00599  -0.0358   0.4382   1.0000
   3.000   0.6523   0.01398   0.00610  -0.0356   0.4367   1.0000
   3.250   0.6795   0.01415   0.00622  -0.0354   0.4353   1.0000
   3.500   0.7066   0.01435   0.00639  -0.0353   0.4337   1.0000
   3.750   0.7336   0.01461   0.00672  -0.0352   0.4314   1.0000
   4.000   0.7605   0.01485   0.00702  -0.0351   0.4291   1.0000
   4.250   0.7875   0.01507   0.00727  -0.0350   0.4268   1.0000
   4.500   0.8146   0.01525   0.00747  -0.0348   0.4247   1.0000
   4.750   0.8417   0.01543   0.00764  -0.0347   0.4229   1.0000
   5.000   0.8689   0.01557   0.00778  -0.0345   0.4211   1.0000
   5.250   0.8961   0.01571   0.00790  -0.0343   0.4194   1.0000
   5.500   0.9225   0.01600   0.00830  -0.0343   0.4164   1.0000
   5.750   0.9490   0.01624   0.00865  -0.0342   0.4130   1.0000
   6.000   0.9758   0.01639   0.00886  -0.0340   0.4100   1.0000
   6.250   1.0029   0.01647   0.00896  -0.0339   0.4074   1.0000
   6.500   1.0301   0.01652   0.00901  -0.0337   0.4051   1.0000
   6.750   1.0562   0.01677   0.00938  -0.0336   0.4015   1.0000
   7.000   1.0823   0.01698   0.00971  -0.0334   0.3972   1.0000
   7.250   1.1091   0.01703   0.00983  -0.0333   0.3936   1.0000
   7.500   1.1363   0.01699   0.00980  -0.0331   0.3904   1.0000
   7.750   1.1617   0.01726   0.01023  -0.0329   0.3853   1.0000
   8.000   1.1878   0.01738   0.01047  -0.0328   0.3803   1.0000
   8.250   1.2146   0.01735   0.01047  -0.0325   0.3763   1.0000
   8.500   1.2397   0.01762   0.01092  -0.0324   0.3699   1.0000
   8.750   1.2658   0.01765   0.01103  -0.0322   0.3635   1.0000
   9.000   1.2909   0.01784   0.01136  -0.0320   0.3556   1.0000
   9.250   1.3166   0.01787   0.01144  -0.0317   0.3477   1.0000
   9.500   1.3409   0.01815   0.01188  -0.0315   0.3371   1.0000
   9.750   1.3649   0.01840   0.01221  -0.0312   0.3251   1.0000
  10.000   1.3881   0.01870   0.01256  -0.0308   0.3100   1.0000
  10.250   1.4093   0.01914   0.01298  -0.0303   0.2912   1.0000
  10.500   1.4275   0.01987   0.01368  -0.0297   0.2679   1.0000
  10.750   1.4414   0.02096   0.01470  -0.0289   0.2444   1.0000
  11.000   1.4507   0.02240   0.01607  -0.0279   0.2232   1.0000
  11.250   1.4553   0.02411   0.01776  -0.0267   0.2053   1.0000
  11.500   1.4518   0.02622   0.01989  -0.0253   0.1914   1.0000
  11.750   1.4374   0.02971   0.02343  -0.0253   0.1817   1.0000
  12.000   1.4264   0.03353   0.02730  -0.0260   0.1721   1.0000
  12.250   1.4141   0.03744   0.03122  -0.0266   0.1630   1.0000
  12.500   1.4029   0.04117   0.03496  -0.0269   0.1543   1.0000
  12.750   1.3934   0.04473   0.03854  -0.0272   0.1456   1.0000
  13.000   1.3830   0.04839   0.04220  -0.0275   0.1378   1.0000
  13.250   1.3756   0.05180   0.04562  -0.0279   0.1296   1.0000
  13.500   1.3681   0.05526   0.04910  -0.0283   0.1222   1.0000
  13.750   1.3613   0.05872   0.05257  -0.0287   0.1151   1.0000
  14.000   1.3574   0.06205   0.05594  -0.0293   0.1078   1.0000
  14.250   1.3516   0.06574   0.05962  -0.0301   0.1012   1.0000
  14.500   1.3503   0.06896   0.06290  -0.0308   0.0943   1.0000
  14.750   1.3453   0.07274   0.06668  -0.0317   0.0882   1.0000
  15.000   1.3443   0.07606   0.07006  -0.0325   0.0820   1.0000
  15.250   1.3398   0.07993   0.07395  -0.0335   0.0766   1.0000
  15.500   1.3389   0.08336   0.07744  -0.0345   0.0710   1.0000
  15.750   1.3339   0.08747   0.08156  -0.0357   0.0667   1.0000
  16.000   1.3342   0.09082   0.08500  -0.0367   0.0619   1.0000
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