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EPPLER 748 AIRFOIL (e748-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 748 AIRFOIL (e748-il)
Reynolds number: 50,000
Max Cl/Cd: 21.54 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e748-il-50000-n5.txt
Download as CSV file: xf-e748-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 748 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.3761   0.11035   0.10288  -0.0602   1.0000   0.0635
 -12.500  -0.4142   0.09907   0.09155  -0.0653   1.0000   0.0634
 -12.250  -0.4513   0.08962   0.08198  -0.0695   1.0000   0.0632
 -12.000  -0.4805   0.08262   0.07484  -0.0722   1.0000   0.0632
 -11.750  -0.5049   0.07699   0.06904  -0.0739   1.0000   0.0635
 -11.500  -0.5232   0.07259   0.06448  -0.0745   1.0000   0.0640
 -11.250  -0.5217   0.07079   0.06277  -0.0733   1.0000   0.0652
 -11.000  -0.5249   0.06869   0.06066  -0.0722   1.0000   0.0663
 -10.750  -0.5300   0.06660   0.05858  -0.0709   1.0000   0.0677
 -10.500  -0.5383   0.06448   0.05643  -0.0695   1.0000   0.0694
 -10.250  -0.5476   0.06253   0.05441  -0.0677   1.0000   0.0711
 -10.000  -0.5600   0.06065   0.05243  -0.0655   1.0000   0.0729
  -9.750  -0.5667   0.05978   0.05172  -0.0626   1.0000   0.0747
  -9.500  -0.5624   0.05846   0.05046  -0.0623   0.9966   0.0776
  -9.250  -0.5366   0.05622   0.04807  -0.0658   0.9864   0.0841
  -9.000  -0.5137   0.05432   0.04622  -0.0689   0.9751   0.0915
  -8.750  -0.4957   0.05232   0.04429  -0.0714   0.9618   0.1000
  -8.500  -0.4831   0.05017   0.04217  -0.0735   0.9467   0.1103
  -8.250  -0.4704   0.04785   0.03993  -0.0759   0.9315   0.1229
  -8.000  -0.4577   0.04529   0.03751  -0.0788   0.9162   0.1388
  -7.750  -0.4446   0.04250   0.03489  -0.0821   0.9011   0.1601
  -7.500  -0.4285   0.03997   0.03263  -0.0854   0.8865   0.1880
  -7.250  -0.4040   0.03900   0.03206  -0.0870   0.8738   0.2272
  -7.000  -0.3558   0.04178   0.03510  -0.0851   0.8660   0.2661
  -6.750  -0.3236   0.04244   0.03559  -0.0856   0.8531   0.2950
  -6.250  -0.2503   0.04303   0.03565  -0.0892   0.8324   0.3431
  -6.000  -0.2179   0.04343   0.03582  -0.0898   0.8208   0.3604
  -5.750  -0.1775   0.04355   0.03569  -0.0916   0.8123   0.3774
  -5.500  -0.1531   0.04309   0.03500  -0.0924   0.7994   0.3930
  -5.000  -0.0877   0.04343   0.03497  -0.0920   0.7789   0.4144
  -4.750  -0.0615   0.04237   0.03365  -0.0941   0.7679   0.4289
  -4.500  -0.0280   0.04270   0.03385  -0.0929   0.7584   0.4350
  -4.250  -0.0059   0.04150   0.03240  -0.0949   0.7467   0.4476
  -4.000   0.0283   0.04147   0.03221  -0.0945   0.7383   0.4530
  -3.750   0.0485   0.04059   0.03114  -0.0955   0.7265   0.4628
  -3.500   0.0826   0.04000   0.03034  -0.0967   0.7188   0.4690
  -3.250   0.1006   0.03982   0.03008  -0.0954   0.7074   0.4743
  -2.750   0.1541   0.03844   0.02834  -0.0979   0.6889   0.4873
  -2.500   0.1872   0.03796   0.02767  -0.0990   0.6819   0.4919
  -2.250   0.2071   0.03755   0.02715  -0.0993   0.6717   0.4975
  -2.000   0.2431   0.03670   0.02605  -0.1025   0.6645   0.5033
  -1.750   0.2622   0.03663   0.02595  -0.1014   0.6554   0.5062
  -1.500   0.2910   0.03632   0.02551  -0.1020   0.6480   0.5100
  -1.250   0.3192   0.03599   0.02504  -0.1031   0.6407   0.5144
  -1.000   0.3479   0.03560   0.02450  -0.1051   0.6324   0.5189
  -0.750   0.3836   0.03516   0.02388  -0.1071   0.6267   0.5224
  -0.500   0.4001   0.03533   0.02407  -0.1058   0.6182   0.5250
  -0.250   0.4287   0.03519   0.02384  -0.1064   0.6117   0.5283
   0.000   0.4614   0.03497   0.02347  -0.1080   0.6061   0.5316
   0.250   0.4821   0.03511   0.02359  -0.1082   0.5980   0.5347
   0.500   0.5186   0.03486   0.02315  -0.1109   0.5922   0.5391
   0.750   0.5437   0.03496   0.02322  -0.1107   0.5865   0.5417
   1.000   0.5613   0.03531   0.02362  -0.1098   0.5792   0.5443
   1.250   0.5918   0.03527   0.02350  -0.1106   0.5740   0.5472
   1.500   0.6204   0.03538   0.02353  -0.1114   0.5687   0.5501
   1.750   0.6376   0.03591   0.02410  -0.1109   0.5615   0.5533
   2.000   0.6709   0.03598   0.02404  -0.1127   0.5564   0.5576
   2.250   0.7051   0.03589   0.02388  -0.1137   0.5526   0.5607
   2.500   0.7092   0.03697   0.02513  -0.1112   0.5447   0.5632
   2.750   0.7346   0.03729   0.02544  -0.1113   0.5395   0.5665
   3.000   0.7706   0.03727   0.02531  -0.1130   0.5357   0.5702
   3.250   0.7801   0.03839   0.02652  -0.1116   0.5290   0.5733
   3.500   0.7989   0.03915   0.02729  -0.1113   0.5231   0.5770
   3.750   0.8284   0.03930   0.02744  -0.1116   0.5191   0.5806
   4.000   0.8548   0.03971   0.02785  -0.1118   0.5150   0.5848
   4.250   0.8453   0.04179   0.03010  -0.1082   0.5071   0.5877
   4.500   0.8720   0.04228   0.03057  -0.1087   0.5027   0.5925
   4.750   0.9093   0.04221   0.03047  -0.1101   0.4996   0.5970
   5.000   0.8756   0.04548   0.03394  -0.1041   0.4906   0.5987
   5.250   0.8887   0.04662   0.03513  -0.1030   0.4855   0.6024
   5.500   0.9241   0.04664   0.03513  -0.1041   0.4825   0.6081
   6.000   0.8897   0.05338   0.04208  -0.0984   0.4669   0.6147
   6.250   0.9235   0.05315   0.04190  -0.0987   0.4644   0.6209
   8.250   0.8472   0.08603   0.07551  -0.0961   0.4022   0.6551
   8.500   0.8611   0.08783   0.07740  -0.0961   0.3974   0.6636
   8.750   0.8852   0.08838   0.07806  -0.0959   0.3946   0.6744
   9.250   0.8749   0.09653   0.08644  -0.0968   0.3803   0.6904
   9.500   0.8987   0.09704   0.08708  -0.0964   0.3774   0.7072
  10.000   0.8885   0.10512   0.09547  -0.0974   0.3636   0.7328
  10.250   0.9096   0.10548   0.09603  -0.0965   0.3607   0.7654
  10.750   0.8895   0.11228   0.10325  -0.0955   0.3473   0.9903
  11.000   0.9169   0.11329   0.10422  -0.0963   0.3442   1.0000
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