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EPPLER 479 AIRFOIL (e479-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 479 AIRFOIL (e479-il)
Reynolds number: 50,000
Max Cl/Cd: 23.78 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e479-il-50000-n5.txt
Download as CSV file: xf-e479-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 479 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.7269   0.09398   0.08516  -0.0116   1.0000   0.1802
 -12.250  -0.6971   0.09561   0.08674  -0.0095   1.0000   0.1828
 -12.000  -0.7935   0.07570   0.06686  -0.0203   1.0000   0.1950
 -11.750  -0.7412   0.08082   0.07194  -0.0160   1.0000   0.1971
 -11.500  -0.7174   0.08142   0.07251  -0.0145   1.0000   0.2008
 -11.250  -0.8421   0.06002   0.05107  -0.0259   1.0000   0.2128
 -11.000  -0.8178   0.06025   0.05129  -0.0246   1.0000   0.2178
 -10.750  -0.9099   0.04905   0.03986  -0.0269   1.0000   0.2235
 -10.500  -0.9060   0.04754   0.03834  -0.0255   1.0000   0.2288
 -10.250  -0.8989   0.04641   0.03717  -0.0238   1.0000   0.2348
 -10.000  -0.9273   0.04270   0.03317  -0.0209   1.0000   0.2411
  -9.750  -0.8974   0.04291   0.03350  -0.0202   1.0000   0.2469
  -9.500  -0.8977   0.04107   0.03151  -0.0182   1.0000   0.2542
  -9.250  -0.8850   0.04005   0.03044  -0.0168   1.0000   0.2608
  -9.000  -0.8714   0.03911   0.02944  -0.0153   1.0000   0.2679
  -8.750  -0.8640   0.03769   0.02787  -0.0136   1.0000   0.2755
  -8.500  -0.8443   0.03720   0.02740  -0.0124   1.0000   0.2826
  -8.250  -0.8370   0.03572   0.02574  -0.0106   1.0000   0.2908
  -8.000  -0.8146   0.03540   0.02546  -0.0095   1.0000   0.2977
  -7.750  -0.8061   0.03405   0.02392  -0.0077   1.0000   0.3067
  -7.500  -0.7829   0.03377   0.02373  -0.0067   1.0000   0.3133
  -7.250  -0.7734   0.03252   0.02227  -0.0049   1.0000   0.3227
  -7.000  -0.7499   0.03231   0.02216  -0.0038   1.0000   0.3293
  -6.750  -0.7377   0.03129   0.02099  -0.0020   1.0000   0.3385
  -6.500  -0.7166   0.03094   0.02073  -0.0008   1.0000   0.3452
  -6.250  -0.7025   0.03017   0.01987   0.0009   1.0000   0.3543
  -6.000  -0.6840   0.02972   0.01947   0.0024   1.0000   0.3613
  -5.750  -0.6687   0.02913   0.01885   0.0041   1.0000   0.3698
  -5.500  -0.6532   0.02863   0.01837   0.0058   1.0000   0.3774
  -5.250  -0.6389   0.02821   0.01796   0.0076   1.0000   0.3852
  -5.000  -0.6277   0.02770   0.01743   0.0097   1.0000   0.3930
  -4.750  -0.6004   0.02743   0.01719   0.0091   0.9911   0.4018
  -4.500  -0.5551   0.02703   0.01674   0.0053   0.9692   0.4126
  -4.250  -0.5124   0.02653   0.01611   0.0018   0.9466   0.4249
  -4.000  -0.4664   0.02629   0.01596  -0.0014   0.9258   0.4344
  -3.750  -0.4234   0.02586   0.01546  -0.0043   0.9044   0.4456
  -3.500  -0.3837   0.02552   0.01507  -0.0063   0.8814   0.4567
  -3.250  -0.3469   0.02524   0.01477  -0.0076   0.8577   0.4663
  -3.000  -0.3139   0.02489   0.01430  -0.0084   0.8346   0.4779
  -2.750  -0.2826   0.02473   0.01412  -0.0084   0.8116   0.4869
  -2.500  -0.2556   0.02449   0.01379  -0.0080   0.7886   0.4974
  -2.250  -0.2286   0.02434   0.01358  -0.0073   0.7671   0.5077
  -2.000  -0.2024   0.02418   0.01336  -0.0065   0.7468   0.5176
  -1.750  -0.1775   0.02402   0.01307  -0.0057   0.7275   0.5293
  -1.500  -0.1515   0.02395   0.01300  -0.0048   0.7091   0.5391
  -1.250  -0.1265   0.02383   0.01280  -0.0040   0.6912   0.5506
  -1.000  -0.1014   0.02375   0.01268  -0.0032   0.6740   0.5625
  -0.750  -0.0758   0.02371   0.01264  -0.0024   0.6576   0.5738
  -0.500  -0.0506   0.02365   0.01255  -0.0016   0.6418   0.5865
  -0.250  -0.0256   0.02362   0.01247  -0.0009   0.6269   0.6005
   0.000   0.0000   0.02363   0.01250   0.0000   0.6131   0.6132
   0.250   0.0255   0.02362   0.01247   0.0009   0.6004   0.6269
   0.500   0.0506   0.02365   0.01255   0.0016   0.5865   0.6418
   0.750   0.0758   0.02371   0.01264   0.0024   0.5738   0.6576
   1.000   0.1014   0.02375   0.01268   0.0032   0.5625   0.6740
   1.250   0.1265   0.02383   0.01280   0.0040   0.5506   0.6912
   1.500   0.1515   0.02395   0.01300   0.0048   0.5391   0.7091
   1.750   0.1776   0.02402   0.01307   0.0057   0.5294   0.7275
   2.000   0.2024   0.02418   0.01336   0.0065   0.5176   0.7468
   2.250   0.2286   0.02434   0.01358   0.0073   0.5076   0.7671
   2.500   0.2556   0.02449   0.01379   0.0080   0.4975   0.7886
   2.750   0.2826   0.02473   0.01412   0.0084   0.4869   0.8116
   3.000   0.3139   0.02489   0.01430   0.0084   0.4779   0.8347
   3.250   0.3469   0.02524   0.01477   0.0076   0.4663   0.8577
   3.500   0.3837   0.02552   0.01507   0.0063   0.4567   0.8815
   3.750   0.4234   0.02586   0.01546   0.0043   0.4456   0.9043
   4.000   0.4664   0.02628   0.01595   0.0014   0.4343   0.9258
   4.250   0.5124   0.02653   0.01611  -0.0018   0.4248   0.9467
   4.500   0.5551   0.02702   0.01674  -0.0053   0.4126   0.9693
   4.750   0.6004   0.02743   0.01719  -0.0091   0.4018   0.9912
   5.000   0.6276   0.02770   0.01743  -0.0097   0.3930   1.0000
   5.250   0.6388   0.02821   0.01796  -0.0076   0.3852   1.0000
   5.500   0.6531   0.02864   0.01838  -0.0058   0.3774   1.0000
   5.750   0.6687   0.02913   0.01884  -0.0041   0.3698   1.0000
   6.000   0.6839   0.02972   0.01947  -0.0024   0.3614   1.0000
   6.250   0.7025   0.03017   0.01987  -0.0009   0.3543   1.0000
   6.500   0.7166   0.03094   0.02073   0.0008   0.3453   1.0000
   6.750   0.7377   0.03129   0.02098   0.0020   0.3385   1.0000
   7.000   0.7499   0.03230   0.02216   0.0038   0.3293   1.0000
   7.250   0.7734   0.03252   0.02227   0.0049   0.3227   1.0000
   7.500   0.7829   0.03377   0.02372   0.0067   0.3133   1.0000
   7.750   0.8061   0.03406   0.02392   0.0077   0.3067   1.0000
   8.000   0.8147   0.03540   0.02546   0.0095   0.2977   1.0000
   8.250   0.8371   0.03572   0.02573   0.0106   0.2908   1.0000
   8.500   0.8444   0.03719   0.02739   0.0124   0.2826   1.0000
   8.750   0.8640   0.03769   0.02788   0.0136   0.2755   1.0000
   9.000   0.8716   0.03911   0.02943   0.0153   0.2679   1.0000
   9.250   0.8853   0.04004   0.03043   0.0167   0.2608   1.0000
   9.500   0.8979   0.04107   0.03151   0.0182   0.2542   1.0000
   9.750   0.8977   0.04291   0.03351   0.0201   0.2469   1.0000
  10.000   0.9277   0.04269   0.03315   0.0208   0.2411   1.0000
  10.250   0.8994   0.04640   0.03716   0.0237   0.2347   1.0000
  10.500   0.9061   0.04759   0.03839   0.0254   0.2289   1.0000
  10.750   0.9103   0.04906   0.03987   0.0269   0.2235   1.0000
  11.000   0.8197   0.06011   0.05114   0.0245   0.2178   1.0000
  11.250   0.8469   0.05952   0.05057   0.0261   0.2127   1.0000
  11.500   0.7198   0.08116   0.07224   0.0145   0.2008   1.0000
  11.750   0.7440   0.08051   0.07163   0.0161   0.1971   1.0000
  12.000   0.7966   0.07535   0.06651   0.0204   0.1950   1.0000
  12.250   0.6991   0.09545   0.08658   0.0094   0.1828   1.0000
  12.500   0.7288   0.09386   0.08504   0.0115   0.1802   1.0000
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