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EPPLER 552 AIRFOIL (e552-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 552 AIRFOIL (e552-il)
Reynolds number: 50,000
Max Cl/Cd: 13.26 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e552-il-50000-n5.txt
Download as CSV file: xf-e552-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 552 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
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.4467   0.11601   0.10868  -0.0501   1.0000   0.0429
 -13.500  -0.4605   0.10836   0.10103  -0.0538   1.0000   0.0427
 -13.250  -0.4784   0.10063   0.09327  -0.0579   1.0000   0.0424
 -13.000  -0.4977   0.09347   0.08605  -0.0616   1.0000   0.0420
 -12.750  -0.5198   0.08660   0.07910  -0.0652   1.0000   0.0417
 -12.500  -0.5411   0.08048   0.07285  -0.0682   1.0000   0.0415
 -12.250  -0.5594   0.07522   0.06744  -0.0704   1.0000   0.0414
 -12.000  -0.5759   0.07052   0.06257  -0.0720   1.0000   0.0416
 -11.750  -0.5892   0.06639   0.05825  -0.0728   1.0000   0.0418
 -11.500  -0.5994   0.06273   0.05437  -0.0731   1.0000   0.0422
 -11.250  -0.6049   0.05952   0.05093  -0.0728   1.0000   0.0427
 -11.000  -0.6006   0.05698   0.04829  -0.0720   1.0000   0.0437
 -10.750  -0.5931   0.05507   0.04638  -0.0710   1.0000   0.0451
 -10.500  -0.5879   0.05319   0.04446  -0.0699   1.0000   0.0473
 -10.250  -0.5798   0.05137   0.04248  -0.0684   1.0000   0.0498
 -10.000  -0.5633   0.04988   0.04086  -0.0666   1.0000   0.0531
  -9.750  -0.5508   0.04879   0.03985  -0.0647   1.0000   0.0563
  -9.500  -0.5414   0.04770   0.03870  -0.0625   1.0000   0.0605
  -9.250  -0.5357   0.04677   0.03784  -0.0599   1.0000   0.0647
  -9.000  -0.5400   0.04606   0.03727  -0.0567   1.0000   0.0677
  -8.750  -0.5177   0.04457   0.03578  -0.0577   0.9846   0.0767
  -8.500  -0.4930   0.04266   0.03391  -0.0601   0.9600   0.0891
  -8.250  -0.4728   0.04037   0.03174  -0.0628   0.9383   0.1055
  -8.000  -0.4548   0.03777   0.02925  -0.0660   0.9184   0.1291
  -7.750  -0.4450   0.03457   0.02635  -0.0693   0.8983   0.1616
  -7.500  -0.4406   0.03165   0.02391  -0.0711   0.8789   0.2160
  -7.250  -0.4062   0.03346   0.02678  -0.0687   0.8647   0.3571
  -7.000  -0.3864   0.03342   0.02636  -0.0692   0.8482   0.4110
  -6.750  -0.3636   0.03414   0.02673  -0.0685   0.8331   0.4448
  -6.500  -0.3330   0.03565   0.02794  -0.0669   0.8197   0.4681
  -6.250  -0.3011   0.03702   0.02903  -0.0652   0.8076   0.4867
  -6.000  -0.2700   0.03799   0.02973  -0.0638   0.7968   0.5030
  -5.750  -0.2446   0.03849   0.02997  -0.0624   0.7856   0.5171
  -5.500  -0.2261   0.03838   0.02963  -0.0612   0.7746   0.5303
  -5.250  -0.1976   0.03852   0.02952  -0.0604   0.7661   0.5397
  -5.000  -0.1798   0.03820   0.02902  -0.0594   0.7558   0.5483
  -4.750  -0.1582   0.03783   0.02842  -0.0588   0.7476   0.5563
  -4.500  -0.1410   0.03728   0.02770  -0.0582   0.7388   0.5636
  -4.250  -0.1171   0.03702   0.02724  -0.0576   0.7316   0.5691
  -4.000  -0.1042   0.03612   0.02616  -0.0576   0.7233   0.5775
  -3.750  -0.0764   0.03591   0.02575  -0.0574   0.7173   0.5812
  -3.500  -0.0579   0.03563   0.02537  -0.0567   0.7093   0.5861
  -3.250  -0.0386   0.03475   0.02425  -0.0576   0.7035   0.5933
  -3.000  -0.0161   0.03467   0.02408  -0.0569   0.6970   0.5964
  -2.750   0.0062   0.03446   0.02376  -0.0566   0.6907   0.6002
  -2.500   0.0317   0.03399   0.02310  -0.0572   0.6860   0.6050
  -2.250   0.0488   0.03363   0.02263  -0.0573   0.6791   0.6103
  -2.000   0.0726   0.03355   0.02247  -0.0569   0.6738   0.6133
  -1.750   0.0995   0.03333   0.02211  -0.0572   0.6698   0.6170
  -1.500   0.1173   0.03330   0.02203  -0.0569   0.6636   0.6212
  -1.250   0.1404   0.03305   0.02165  -0.0576   0.6584   0.6261
  -1.000   0.1670   0.03298   0.02149  -0.0576   0.6545   0.6292
  -0.750   0.1863   0.03314   0.02162  -0.0570   0.6492   0.6328
  -0.500   0.2069   0.03324   0.02168  -0.0569   0.6440   0.6368
  -0.250   0.2337   0.03312   0.02144  -0.0579   0.6401   0.6417
   0.000   0.2617   0.03309   0.02133  -0.0580   0.6371   0.6450
   0.250   0.2734   0.03366   0.02198  -0.0566   0.6306   0.6488
   0.500   0.2962   0.03385   0.02212  -0.0567   0.6261   0.6532
   0.750   0.3248   0.03385   0.02202  -0.0578   0.6228   0.6582
   1.000   0.3437   0.03427   0.02247  -0.0570   0.6186   0.6615
   1.250   0.3567   0.03495   0.02322  -0.0559   0.6129   0.6657
   1.500   0.3810   0.03522   0.02345  -0.0561   0.6089   0.6709
   1.750   0.4100   0.03532   0.02351  -0.0569   0.6060   0.6758
   2.000   0.4172   0.03639   0.02467  -0.0551   0.6001   0.6798
   2.250   0.4334   0.03711   0.02542  -0.0546   0.5951   0.6847
   2.500   0.4615   0.03736   0.02565  -0.0554   0.5917   0.6907
   2.750   0.4900   0.03749   0.02579  -0.0555   0.5892   0.6954
   3.000   0.4804   0.03954   0.02797  -0.0527   0.5808   0.7007
   3.250   0.5042   0.04006   0.02849  -0.0530   0.5768   0.7072
   3.500   0.5330   0.04019   0.02868  -0.0531   0.5742   0.7126
   3.750   0.5206   0.04259   0.03118  -0.0504   0.5655   0.7185
   4.000   0.5401   0.04331   0.03195  -0.0502   0.5611   0.7252
   4.250   0.5699   0.04343   0.03212  -0.0504   0.5584   0.7324
   4.750   0.5689   0.04697   0.03584  -0.0468   0.5444   0.7471
   5.000   0.6022   0.04694   0.03586  -0.0473   0.5419   0.7564
   5.500   0.6042   0.05086   0.03998  -0.0447   0.5272   0.7747
   6.000   0.6129   0.05447   0.04382  -0.0429   0.5129   0.7975
   6.250   0.6428   0.05432   0.04380  -0.0425   0.5101   0.8127
   6.500   0.6250   0.05766   0.04728  -0.0409   0.4989   0.8278
   6.750   0.6515   0.05763   0.04742  -0.0402   0.4954   0.8507
   7.000   0.6413   0.06040   0.05036  -0.0390   0.4852   0.8814
   7.250   0.6691   0.06051   0.05063  -0.0395   0.4804   1.0000
   7.750   0.6987   0.06404   0.05420  -0.0413   0.4653   1.0000
   8.250   0.7262   0.06744   0.05766  -0.0422   0.4501   1.0000
   8.500   0.7627   0.06718   0.05745  -0.0426   0.4469   1.0000
   8.750   0.7531   0.07070   0.06102  -0.0426   0.4346   1.0000
   9.250   0.7800   0.07380   0.06423  -0.0427   0.4188   1.0000
   9.750   0.8074   0.07673   0.06729  -0.0427   0.4029   1.0000
  10.000   0.8046   0.07979   0.07043  -0.0428   0.3914   1.0000
  10.250   0.8363   0.07936   0.07010  -0.0424   0.3870   1.0000
  10.500   0.8310   0.08275   0.07356  -0.0427   0.3748   1.0000
  11.000   0.8594   0.08536   0.07636  -0.0425   0.3586   1.0000
  11.250   0.8576   0.08852   0.07961  -0.0429   0.3469   1.0000
  11.500   0.8894   0.08761   0.07883  -0.0421   0.3424   1.0000
  11.750   0.8847   0.09119   0.08249  -0.0427   0.3301   1.0000
  12.250   0.9146   0.09331   0.08485  -0.0422   0.3137   1.0000
  12.500   0.9111   0.09695   0.08857  -0.0429   0.3016   1.0000
  12.750   0.9445   0.09516   0.08692  -0.0417   0.2973   1.0000
  13.000   0.9399   0.09906   0.09092  -0.0425   0.2850   1.0000
  13.500   0.9716   0.10042   0.09252  -0.0419   0.2689   1.0000
  13.750   0.9647   0.10496   0.09716  -0.0431   0.2565   1.0000
  14.250   0.9964   0.10617   0.09861  -0.0424   0.2402   1.0000
  14.750   1.0355   0.10595   0.09862  -0.0412   0.2240   1.0000
  15.250   1.0100   0.11792   0.11073  -0.0455   0.2010   1.0000
  15.500   1.0628   0.11125   0.10419  -0.0419   0.1951   1.0000
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