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EPPLER 593 AIRFOIL (e593-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 593 AIRFOIL (e593-il)
Reynolds number: 200,000
Max Cl/Cd: 71.35 at α=11°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e593-il-200000.txt
Download as CSV file: xf-e593-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3602   0.11000   0.10535   0.0060   0.5772   0.0402
  -8.750  -0.3673   0.10702   0.10244   0.0008   0.5758   0.0409
  -8.500  -0.3697   0.10362   0.09910  -0.0032   0.5739   0.0411
  -8.250  -0.3568   0.09911   0.09459  -0.0022   0.5707   0.0416
  -8.000  -0.3419   0.09600   0.09146  -0.0012   0.5677   0.0425
  -7.750  -0.3334   0.09315   0.08859  -0.0020   0.5654   0.0433
  -7.500  -0.3274   0.09016   0.08560  -0.0032   0.5635   0.0442
  -7.250  -0.3236   0.08709   0.08252  -0.0049   0.5618   0.0456
  -7.000  -0.3242   0.08398   0.07946  -0.0073   0.5602   0.0469
  -6.750  -0.3278   0.07940   0.07492  -0.0173   0.5591   0.0487
  -6.500  -0.3209   0.07327   0.06872  -0.0259   0.5577   0.0492
  -6.250  -0.3101   0.07013   0.06563  -0.0237   0.5552   0.0499
  -6.000  -0.2964   0.06741   0.06290  -0.0237   0.5528   0.0508
  -5.750  -0.2816   0.06437   0.05982  -0.0251   0.5504   0.0521
  -5.500  -0.2768   0.04158   0.03621  -0.0387   0.5513   0.0292
  -5.250  -0.2543   0.04156   0.03619  -0.0386   0.5486   0.0302
  -5.000  -0.2418   0.02784   0.02087  -0.0403   0.5478   0.0252
  -4.750  -0.2175   0.02522   0.01767  -0.0399   0.5457   0.0258
  -4.500  -0.1911   0.02326   0.01527  -0.0396   0.5434   0.0273
  -4.250  -0.1642   0.02212   0.01393  -0.0394   0.5409   0.0304
  -4.000  -0.1362   0.02131   0.01283  -0.0390   0.5384   0.0345
  -3.750  -0.1091   0.02031   0.01178  -0.0388   0.5360   0.0398
  -3.500  -0.0813   0.01983   0.01116  -0.0385   0.5338   0.0493
  -3.250  -0.0541   0.01937   0.01069  -0.0383   0.5316   0.0608
  -3.000  -0.0267   0.01923   0.01048  -0.0380   0.5295   0.0725
  -2.750   0.0015   0.01894   0.01017  -0.0380   0.5270   0.0841
  -2.500   0.0299   0.01888   0.01003  -0.0379   0.5246   0.0949
  -2.250   0.0575   0.01848   0.00970  -0.0378   0.5223   0.1069
  -2.000   0.0852   0.01818   0.00941  -0.0376   0.5201   0.1191
  -1.750   0.1128   0.01794   0.00916  -0.0375   0.5181   0.1323
  -1.500   0.1403   0.01773   0.00893  -0.0372   0.5162   0.1467
  -1.250   0.1676   0.01760   0.00877  -0.0370   0.5143   0.1627
  -1.000   0.1951   0.01752   0.00877  -0.0369   0.5121   0.1814
  -0.750   0.2228   0.01745   0.00880  -0.0369   0.5097   0.2050
  -0.500   0.2500   0.01733   0.00886  -0.0369   0.5074   0.2373
  -0.250   0.2765   0.01709   0.00893  -0.0368   0.5053   0.2989
   0.000   0.3319   0.01516   0.00895  -0.0419   0.5030   1.0000
   0.250   0.3584   0.01539   0.00900  -0.0414   0.5010   1.0000
   0.500   0.3847   0.01564   0.00908  -0.0410   0.4992   1.0000
   0.750   0.4108   0.01603   0.00931  -0.0406   0.4975   1.0000
   1.000   0.4376   0.01644   0.00973  -0.0406   0.4951   1.0000
   1.250   0.4641   0.01688   0.01016  -0.0406   0.4926   1.0000
   1.500   0.4906   0.01727   0.01052  -0.0405   0.4901   1.0000
   1.750   0.5171   0.01757   0.01077  -0.0402   0.4877   1.0000
   2.000   0.5437   0.01784   0.01096  -0.0399   0.4857   1.0000
   2.250   0.5703   0.01815   0.01119  -0.0397   0.4841   1.0000
   2.500   0.5968   0.01852   0.01148  -0.0394   0.4825   1.0000
   2.750   0.6227   0.01908   0.01206  -0.0393   0.4802   1.0000
   3.000   0.6483   0.01977   0.01287  -0.0396   0.4765   1.0000
   3.250   0.6742   0.02033   0.01346  -0.0396   0.4737   1.0000
   3.500   0.7005   0.02068   0.01380  -0.0394   0.4712   1.0000
   3.750   0.7271   0.02090   0.01398  -0.0391   0.4692   1.0000
   4.000   0.7539   0.02113   0.01414  -0.0387   0.4675   1.0000
   4.250   0.7804   0.02146   0.01442  -0.0383   0.4659   1.0000
   4.500   0.8032   0.02264   0.01583  -0.0388   0.4606   1.0000
   4.750   0.8283   0.02321   0.01647  -0.0388   0.4570   1.0000
   5.000   0.8548   0.02337   0.01663  -0.0385   0.4545   1.0000
   5.250   0.8822   0.02338   0.01660  -0.0381   0.4526   1.0000
   5.500   0.9096   0.02341   0.01657  -0.0376   0.4508   1.0000
   5.750   0.9308   0.02465   0.01802  -0.0379   0.4453   1.0000
   6.000   0.9553   0.02515   0.01862  -0.0378   0.4410   1.0000
   6.250   0.9828   0.02503   0.01849  -0.0373   0.4385   1.0000
   6.500   1.0113   0.02475   0.01817  -0.0368   0.4365   1.0000
   6.750   1.0400   0.02450   0.01787  -0.0363   0.4347   1.0000
   7.000   1.0582   0.02589   0.01955  -0.0365   0.4270   1.0000
   7.250   1.0863   0.02558   0.01925  -0.0361   0.4239   1.0000
   7.500   1.1161   0.02498   0.01862  -0.0355   0.4215   1.0000
   7.750   1.1464   0.02438   0.01796  -0.0351   0.4195   1.0000
   8.000   1.1653   0.02537   0.01923  -0.0349   0.4119   1.0000
   8.250   1.1943   0.02483   0.01871  -0.0345   0.4084   1.0000
   8.500   1.2254   0.02398   0.01781  -0.0341   0.4058   1.0000
   8.750   1.2487   0.02418   0.01818  -0.0337   0.3995   1.0000
   9.000   1.2767   0.02362   0.01769  -0.0333   0.3942   1.0000
   9.250   1.3086   0.02258   0.01658  -0.0329   0.3907   1.0000
   9.500   1.3309   0.02273   0.01697  -0.0325   0.3828   1.0000
   9.750   1.3608   0.02186   0.01610  -0.0321   0.3774   1.0000
  10.000   1.3846   0.02175   0.01617  -0.0316   0.3689   1.0000
  10.250   1.4140   0.02092   0.01532  -0.0312   0.3617   1.0000
  10.500   1.4367   0.02088   0.01550  -0.0307   0.3500   1.0000
  10.750   1.4602   0.02078   0.01552  -0.0302   0.3367   1.0000
  11.000   1.4827   0.02078   0.01556  -0.0296   0.3207   1.0000
  11.250   1.5014   0.02120   0.01605  -0.0289   0.2998   1.0000
  11.500   1.5155   0.02196   0.01675  -0.0278   0.2757   1.0000
  11.750   1.5219   0.02335   0.01803  -0.0265   0.2512   1.0000
  12.000   1.5199   0.02528   0.01992  -0.0248   0.2308   1.0000
  12.250   1.5045   0.02803   0.02266  -0.0231   0.2178   1.0000
  12.500   1.4870   0.03213   0.02674  -0.0236   0.2056   1.0000
  12.750   1.4708   0.03632   0.03088  -0.0242   0.1939   1.0000
  13.000   1.4568   0.04032   0.03488  -0.0246   0.1824   1.0000
  13.250   1.4437   0.04420   0.03875  -0.0250   0.1716   1.0000
  13.500   1.4314   0.04801   0.04253  -0.0253   0.1617   1.0000
  13.750   1.4190   0.05185   0.04628  -0.0257   0.1526   1.0000
  14.000   1.4094   0.05555   0.05002  -0.0262   0.1427   1.0000
  14.250   1.4007   0.05920   0.05367  -0.0267   0.1339   1.0000
  14.500   1.3923   0.06296   0.05735  -0.0273   0.1257   1.0000
  14.750   1.3865   0.06672   0.06116  -0.0282   0.1169   1.0000
  15.000   1.3811   0.07042   0.06486  -0.0290   0.1091   1.0000
  15.250   1.3750   0.07427   0.06866  -0.0299   0.1017   1.0000
  15.500   1.3714   0.07801   0.07248  -0.0309   0.0945   1.0000
  15.750   1.3673   0.08165   0.07603  -0.0317   0.0882   1.0000
  16.000   1.3640   0.08555   0.08005  -0.0329   0.0821   1.0000
  16.250   1.3605   0.08923   0.08366  -0.0339   0.0764   1.0000
  16.500   1.3574   0.09322   0.08777  -0.0352   0.0711   1.0000
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