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EPPLER 393 AIRFOIL (e393-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 393 AIRFOIL (e393-il)
Reynolds number: 50,000
Max Cl/Cd: 35.28 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e393-il-50000-n5.txt
Download as CSV file: xf-e393-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 393 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3147   0.11840   0.11143  -0.0415   1.0000   0.0994
  -9.750  -0.3176   0.11526   0.10838  -0.0426   1.0000   0.0971
  -9.500  -0.3256   0.10771   0.10087  -0.0468   1.0000   0.0525
  -9.250  -0.3216   0.10457   0.09776  -0.0462   1.0000   0.0512
  -9.000  -0.3216   0.10149   0.09477  -0.0461   1.0000   0.0499
  -8.750  -0.3243   0.09837   0.09175  -0.0461   1.0000   0.0488
  -8.500  -0.3293   0.09532   0.08881  -0.0460   1.0000   0.0478
  -8.250  -0.3370   0.09236   0.08599  -0.0456   1.0000   0.0470
  -8.000  -0.3479   0.08963   0.08341  -0.0449   1.0000   0.0461
  -7.750  -0.3634   0.08721   0.08115  -0.0436   1.0000   0.0453
  -7.500  -0.3839   0.08499   0.07910  -0.0417   1.0000   0.0447
  -7.000  -0.4212   0.07340   0.06762  -0.0514   0.9964   0.0413
  -6.750  -0.4025   0.06691   0.06096  -0.0596   0.9860   0.0410
  -6.500  -0.3830   0.06058   0.05433  -0.0673   0.9753   0.0408
  -6.250  -0.3603   0.05433   0.04761  -0.0746   0.9650   0.0410
  -6.000  -0.3331   0.04951   0.04242  -0.0801   0.9569   0.0430
  -5.750  -0.3072   0.04656   0.03924  -0.0831   0.9473   0.0457
  -5.500  -0.2759   0.04233   0.03441  -0.0873   0.9393   0.0477
  -5.250  -0.2422   0.03840   0.02980  -0.0906   0.9319   0.0492
  -5.000  -0.2088   0.03533   0.02603  -0.0928   0.9243   0.0518
  -4.750  -0.1745   0.03320   0.02361  -0.0950   0.9176   0.0578
  -4.500  -0.1426   0.03138   0.02137  -0.0960   0.9100   0.0635
  -4.250  -0.1081   0.02973   0.01953  -0.0974   0.9036   0.0718
  -4.000  -0.0774   0.02844   0.01805  -0.0980   0.8961   0.0830
  -3.750  -0.0431   0.02718   0.01670  -0.0993   0.8897   0.0997
  -3.500  -0.0117   0.02605   0.01557  -0.1005   0.8823   0.1283
  -3.250   0.0241   0.02469   0.01447  -0.1029   0.8761   0.1973
  -3.000   0.0564   0.02344   0.01400  -0.1046   0.8694   0.3474
  -2.750   0.0846   0.02314   0.01407  -0.1043   0.8620   0.4877
  -2.500   0.1105   0.02314   0.01409  -0.1034   0.8542   0.5701
  -2.250   0.1368   0.02312   0.01404  -0.1023   0.8472   0.6296
  -2.000   0.1587   0.02315   0.01400  -0.1004   0.8390   0.6760
  -1.750   0.1839   0.02308   0.01385  -0.0990   0.8324   0.7192
  -1.500   0.2037   0.02310   0.01381  -0.0970   0.8240   0.7577
  -1.250   0.2275   0.02296   0.01360  -0.0953   0.8178   0.7958
  -1.000   0.2451   0.02295   0.01353  -0.0929   0.8093   0.8342
  -0.750   0.2726   0.02273   0.01323  -0.0922   0.8035   0.8797
  -0.500   0.3086   0.02267   0.01305  -0.0939   0.7961   0.9415
  -0.250   0.3519   0.02262   0.01275  -0.0976   0.7900   1.0000
   0.000   0.3817   0.02292   0.01282  -0.0990   0.7823   1.0000
   0.250   0.4152   0.02311   0.01279  -0.1007   0.7760   1.0000
   0.500   0.4439   0.02345   0.01295  -0.1015   0.7688   1.0000
   0.750   0.4747   0.02372   0.01306  -0.1025   0.7622   1.0000
   1.000   0.5033   0.02407   0.01328  -0.1031   0.7554   1.0000
   1.250   0.5314   0.02444   0.01354  -0.1036   0.7485   1.0000
   1.500   0.5614   0.02474   0.01374  -0.1043   0.7424   1.0000
   1.750   0.5863   0.02523   0.01416  -0.1043   0.7347   1.0000
   2.000   0.6195   0.02542   0.01427  -0.1053   0.7300   1.0000
   2.250   0.6395   0.02611   0.01496  -0.1047   0.7210   1.0000
   2.500   0.6734   0.02626   0.01506  -0.1056   0.7165   1.0000
   2.750   0.6914   0.02706   0.01587  -0.1047   0.7072   1.0000
   3.000   0.7246   0.02722   0.01602  -0.1055   0.7025   1.0000
   3.250   0.7420   0.02807   0.01694  -0.1046   0.6932   1.0000
   3.500   0.7750   0.02823   0.01711  -0.1052   0.6883   1.0000
   3.750   0.7917   0.02914   0.01808  -0.1042   0.6789   1.0000
   4.000   0.8251   0.02925   0.01823  -0.1048   0.6739   1.0000
   4.250   0.8407   0.03020   0.01932  -0.1036   0.6640   1.0000
   4.500   0.8758   0.03020   0.01938  -0.1043   0.6591   1.0000
   4.750   0.8902   0.03119   0.02048  -0.1029   0.6485   1.0000
   5.000   0.9127   0.03178   0.02117  -0.1023   0.6400   1.0000
   5.250   0.9419   0.03196   0.02152  -0.1022   0.6324   1.0000
   5.500   0.9591   0.03276   0.02245  -0.1009   0.6219   1.0000
   5.750   0.9884   0.03287   0.02270  -0.1008   0.6139   1.0000
   6.000   1.0126   0.03320   0.02319  -0.1000   0.6040   1.0000
   6.250   1.0305   0.03384   0.02399  -0.0986   0.5924   1.0000
   6.500   1.0525   0.03417   0.02454  -0.0975   0.5810   1.0000
   6.750   1.0794   0.03413   0.02469  -0.0967   0.5699   1.0000
   7.000   1.1087   0.03386   0.02460  -0.0960   0.5582   1.0000
   7.250   1.1323   0.03382   0.02476  -0.0948   0.5445   1.0000
   7.500   1.1490   0.03411   0.02530  -0.0928   0.5288   1.0000
   7.750   1.1643   0.03439   0.02579  -0.0906   0.5117   1.0000
   8.000   1.1820   0.03443   0.02603  -0.0885   0.4935   1.0000
   8.250   1.2037   0.03412   0.02589  -0.0866   0.4739   1.0000
   8.500   1.2082   0.03484   0.02679  -0.0833   0.4520   1.0000
   8.750   1.2185   0.03518   0.02726  -0.0804   0.4274   1.0000
   9.000   1.2270   0.03574   0.02791  -0.0776   0.3995   1.0000
   9.250   1.2334   0.03653   0.02880  -0.0747   0.3678   1.0000
   9.500   1.2394   0.03750   0.02966  -0.0720   0.3331   1.0000
   9.750   1.2404   0.03909   0.03115  -0.0694   0.2982   1.0000
  10.000   1.2387   0.04112   0.03298  -0.0669   0.2654   1.0000
  10.250   1.2352   0.04358   0.03527  -0.0649   0.2366   1.0000
  10.500   1.2308   0.04635   0.03793  -0.0632   0.2102   1.0000
  10.750   1.2267   0.04928   0.04079  -0.0619   0.1869   1.0000
  11.000   1.2221   0.05240   0.04379  -0.0608   0.1673   1.0000
  11.250   1.2189   0.05559   0.04696  -0.0599   0.1479   1.0000
  11.500   1.2158   0.05886   0.05021  -0.0592   0.1315   1.0000
  11.750   1.2126   0.06226   0.05358  -0.0587   0.1167   1.0000
  12.000   1.2103   0.06567   0.05699  -0.0583   0.1036   1.0000
  12.250   1.2081   0.06919   0.06054  -0.0580   0.0916   1.0000
  12.500   1.2063   0.07278   0.06418  -0.0579   0.0808   1.0000
  12.750   1.2046   0.07644   0.06795  -0.0578   0.0718   1.0000
  13.000   1.2024   0.08018   0.07168  -0.0581   0.0644   1.0000
  13.250   1.2032   0.08388   0.07561  -0.0581   0.0570   1.0000
  13.500   1.2016   0.08763   0.07926  -0.0585   0.0520   1.0000
  13.750   1.2039   0.09148   0.08351  -0.0586   0.0470   1.0000
  14.000   1.2032   0.09543   0.08756  -0.0593   0.0433   1.0000
  14.250   1.2030   0.09943   0.09164  -0.0600   0.0404   1.0000
  14.500   1.1996   0.10445   0.09704  -0.0613   0.0380   1.0000
  14.750   1.1951   0.10963   0.10250  -0.0630   0.0363   1.0000
  15.000   1.1897   0.11511   0.10823  -0.0650   0.0352   1.0000
  15.250   1.1823   0.12110   0.11444  -0.0676   0.0345   1.0000
  15.500   1.1728   0.12771   0.12128  -0.0709   0.0339   1.0000
  15.750   1.1606   0.13530   0.12910  -0.0752   0.0337   1.0000
  16.000   1.1428   0.14489   0.13894  -0.0811   0.0340   1.0000
  16.250   1.1176   0.15787   0.15213  -0.0896   0.0350   1.0000
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