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EPPLER 593 AIRFOIL (e593-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 593 AIRFOIL (e593-il)
Reynolds number: 500,000
Max Cl/Cd: 115.24 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e593-il-500000.txt
Download as CSV file: xf-e593-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3766   0.10315   0.09932   0.0042   0.5097   0.0196
  -8.750  -0.3763   0.09866   0.09486   0.0012   0.5085   0.0197
  -8.500  -0.3729   0.09469   0.09091  -0.0001   0.5070   0.0198
  -8.250  -0.3659   0.09183   0.08804  -0.0009   0.5051   0.0200
  -8.000  -0.3577   0.08931   0.08552  -0.0014   0.5035   0.0203
  -7.750  -0.3514   0.08654   0.08275  -0.0026   0.5019   0.0205
  -7.500  -0.3473   0.08356   0.07977  -0.0039   0.5005   0.0208
  -7.250  -0.3453   0.08056   0.07678  -0.0053   0.4990   0.0212
  -7.000  -0.3461   0.07747   0.07370  -0.0072   0.4975   0.0215
  -6.750  -0.3410   0.07356   0.06981  -0.0110   0.4965   0.0220
  -6.500  -0.3863   0.03615   0.03178  -0.0365   0.4997   0.0134
  -6.250  -0.3766   0.02752   0.02232  -0.0382   0.4985   0.0118
  -6.000  -0.3613   0.02064   0.01416  -0.0377   0.4971   0.0106
  -5.750  -0.3362   0.01903   0.01224  -0.0373   0.4955   0.0106
  -5.500  -0.3103   0.01776   0.01076  -0.0369   0.4935   0.0107
  -5.250  -0.2839   0.01674   0.00957  -0.0365   0.4913   0.0108
  -5.000  -0.2571   0.01593   0.00863  -0.0362   0.4891   0.0111
  -4.750  -0.2300   0.01523   0.00781  -0.0358   0.4871   0.0115
  -4.500  -0.2027   0.01462   0.00708  -0.0355   0.4853   0.0121
  -4.250  -0.1751   0.01414   0.00646  -0.0352   0.4835   0.0129
  -4.000  -0.1480   0.01361   0.00585  -0.0349   0.4814   0.0143
  -3.750  -0.1202   0.01310   0.00531  -0.0346   0.4801   0.0175
  -3.500  -0.0924   0.01259   0.00482  -0.0343   0.4785   0.0259
  -3.250  -0.0643   0.01230   0.00456  -0.0341   0.4766   0.0370
  -3.000  -0.0361   0.01215   0.00443  -0.0340   0.4746   0.0467
  -2.750  -0.0079   0.01206   0.00434  -0.0339   0.4727   0.0565
  -2.500   0.0204   0.01197   0.00427  -0.0338   0.4710   0.0669
  -2.250   0.0486   0.01184   0.00413  -0.0337   0.4694   0.0767
  -2.000   0.0767   0.01174   0.00399  -0.0335   0.4678   0.0863
  -1.750   0.1050   0.01179   0.00398  -0.0334   0.4660   0.0950
  -1.500   0.1332   0.01167   0.00390  -0.0333   0.4646   0.1068
  -1.250   0.1615   0.01152   0.00380  -0.0332   0.4632   0.1189
  -1.000   0.1899   0.01141   0.00372  -0.0331   0.4614   0.1321
  -0.750   0.2182   0.01131   0.00366  -0.0330   0.4596   0.1473
  -0.500   0.2464   0.01121   0.00361  -0.0330   0.4579   0.1658
  -0.250   0.2746   0.01112   0.00357  -0.0329   0.4563   0.1917
   0.000   0.3026   0.01098   0.00356  -0.0328   0.4548   0.2347
   0.250   0.3302   0.01077   0.00356  -0.0327   0.4534   0.3102
   0.500   0.3528   0.00982   0.00360  -0.0321   0.4520   0.6372
   0.750   0.4104   0.00918   0.00374  -0.0377   0.4498   1.0000
   1.000   0.4375   0.00924   0.00376  -0.0374   0.4484   1.0000
   1.250   0.4646   0.00931   0.00380  -0.0370   0.4469   1.0000
   1.500   0.4918   0.00941   0.00387  -0.0368   0.4454   1.0000
   1.750   0.5189   0.00951   0.00394  -0.0365   0.4438   1.0000
   2.000   0.5462   0.00961   0.00401  -0.0362   0.4421   1.0000
   2.250   0.5735   0.00971   0.00406  -0.0360   0.4404   1.0000
   2.500   0.6009   0.00980   0.00411  -0.0357   0.4388   1.0000
   2.750   0.6283   0.00992   0.00418  -0.0355   0.4373   1.0000
   3.000   0.6557   0.01008   0.00429  -0.0353   0.4359   1.0000
   3.250   0.6829   0.01036   0.00453  -0.0351   0.4340   1.0000
   3.500   0.7104   0.01043   0.00463  -0.0350   0.4326   1.0000
   3.750   0.7380   0.01052   0.00475  -0.0349   0.4307   1.0000
   4.000   0.7655   0.01062   0.00488  -0.0347   0.4287   1.0000
   4.250   0.7931   0.01071   0.00497  -0.0346   0.4266   1.0000
   4.500   0.8208   0.01077   0.00503  -0.0345   0.4246   1.0000
   4.750   0.8485   0.01083   0.00506  -0.0344   0.4225   1.0000
   5.000   0.8761   0.01095   0.00514  -0.0343   0.4205   1.0000
   5.250   0.9035   0.01113   0.00534  -0.0342   0.4182   1.0000
   5.500   0.9310   0.01118   0.00546  -0.0341   0.4157   1.0000
   5.750   0.9586   0.01123   0.00556  -0.0340   0.4129   1.0000
   6.000   0.9863   0.01126   0.00561  -0.0339   0.4103   1.0000
   6.250   1.0140   0.01127   0.00561  -0.0339   0.4076   1.0000
   6.500   1.0415   0.01136   0.00568  -0.0338   0.4049   1.0000
   6.750   1.0688   0.01143   0.00584  -0.0337   0.4019   1.0000
   7.000   1.0963   0.01147   0.00595  -0.0337   0.3985   1.0000
   7.250   1.1238   0.01147   0.00600  -0.0336   0.3952   1.0000
   7.500   1.1514   0.01148   0.00602  -0.0335   0.3920   1.0000
   7.750   1.1786   0.01156   0.00613  -0.0335   0.3881   1.0000
   8.000   1.2058   0.01155   0.00624  -0.0334   0.3832   1.0000
   8.250   1.2332   0.01154   0.00627  -0.0333   0.3786   1.0000
   8.500   1.2602   0.01161   0.00637  -0.0333   0.3739   1.0000
   8.750   1.2873   0.01164   0.00652  -0.0332   0.3675   1.0000
   9.000   1.3140   0.01170   0.00658  -0.0331   0.3614   1.0000
   9.250   1.3410   0.01178   0.00679  -0.0331   0.3530   1.0000
   9.500   1.3673   0.01191   0.00697  -0.0330   0.3434   1.0000
   9.750   1.3932   0.01209   0.00718  -0.0329   0.3314   1.0000
  10.000   1.4184   0.01237   0.00748  -0.0328   0.3154   1.0000
  10.250   1.4418   0.01285   0.00792  -0.0326   0.2928   1.0000
  10.500   1.4625   0.01364   0.00860  -0.0322   0.2644   1.0000
  11.000   1.4975   0.01584   0.01059  -0.0310   0.2099   1.0000
  11.250   1.5122   0.01709   0.01177  -0.0303   0.1860   1.0000
  11.500   1.5240   0.01850   0.01310  -0.0294   0.1656   1.0000
  11.750   1.5343   0.01990   0.01447  -0.0284   0.1484   1.0000
  12.000   1.5390   0.02158   0.01614  -0.0272   0.1338   1.0000
  12.250   1.5301   0.02400   0.01862  -0.0255   0.1257   1.0000
  12.500   1.5181   0.02811   0.02282  -0.0268   0.1188   1.0000
  12.750   1.5037   0.03242   0.02717  -0.0274   0.1130   1.0000
  13.000   1.4931   0.03610   0.03090  -0.0276   0.1064   1.0000
  13.500   1.4692   0.04357   0.03843  -0.0279   0.0951   1.0000
  13.750   1.4568   0.04741   0.04227  -0.0281   0.0897   1.0000
  14.000   1.4496   0.05074   0.04565  -0.0284   0.0844   1.0000
  14.250   1.4395   0.05445   0.04937  -0.0287   0.0793   1.0000
  14.500   1.4352   0.05772   0.05267  -0.0292   0.0741   1.0000
  14.750   1.4288   0.06138   0.05634  -0.0298   0.0691   1.0000
  15.000   1.4254   0.06475   0.05975  -0.0304   0.0645   1.0000
  15.250   1.4209   0.06837   0.06338  -0.0312   0.0596   1.0000
  15.500   1.4173   0.07194   0.06698  -0.0320   0.0553   1.0000
  15.750   1.4147   0.07544   0.07052  -0.0329   0.0513   1.0000
  16.000   1.4085   0.07951   0.07459  -0.0339   0.0476   1.0000
  16.250   1.4085   0.08278   0.07793  -0.0348   0.0439   1.0000
  16.500   1.4028   0.08696   0.08213  -0.0361   0.0408   1.0000
  16.750   1.4013   0.09059   0.08583  -0.0372   0.0379   1.0000
  17.000   1.3977   0.09454   0.08982  -0.0384   0.0352   1.0000
  17.250   1.3911   0.09908   0.09438  -0.0400   0.0326   1.0000
  17.500   1.3914   0.10259   0.09797  -0.0412   0.0300   1.0000
  17.750   1.3857   0.10712   0.10253  -0.0430   0.0280   1.0000
  18.000   1.3819   0.11141   0.10688  -0.0446   0.0261   1.0000
  18.250   1.3797   0.11548   0.11103  -0.0462   0.0244   1.0000
  18.500   1.3744   0.12015   0.11574  -0.0482   0.0228   1.0000
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