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EPPLER 551 AIRFOIL (e551-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 551 AIRFOIL (e551-il)
Reynolds number: 50,000
Max Cl/Cd: 14.32 at α=13.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e551-il-50000-n5.txt
Download as CSV file: xf-e551-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 551 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
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.4458   0.10642   0.09904  -0.0654   1.0000   0.0412
 -13.250  -0.4659   0.09882   0.09141  -0.0690   1.0000   0.0408
 -13.000  -0.4868   0.09198   0.08451  -0.0722   1.0000   0.0404
 -12.750  -0.5088   0.08566   0.07810  -0.0751   1.0000   0.0399
 -12.500  -0.5313   0.07995   0.07227  -0.0773   1.0000   0.0398
 -12.250  -0.5509   0.07509   0.06727  -0.0788   1.0000   0.0398
 -12.000  -0.5678   0.07088   0.06292  -0.0795   1.0000   0.0399
 -11.750  -0.5826   0.06720   0.05909  -0.0796   1.0000   0.0401
 -11.500  -0.5963   0.06394   0.05566  -0.0791   1.0000   0.0405
 -11.250  -0.6084   0.06107   0.05261  -0.0780   1.0000   0.0411
 -11.000  -0.6212   0.05855   0.04987  -0.0763   1.0000   0.0417
 -10.750  -0.6195   0.05697   0.04837  -0.0743   1.0000   0.0429
 -10.500  -0.6222   0.05551   0.04689  -0.0717   1.0000   0.0439
 -10.250  -0.6257   0.05421   0.04553  -0.0688   1.0000   0.0449
 -10.000  -0.6303   0.05306   0.04430  -0.0655   1.0000   0.0462
  -9.750  -0.6340   0.05205   0.04316  -0.0620   1.0000   0.0477
  -9.500  -0.6368   0.05120   0.04223  -0.0585   1.0000   0.0496
  -9.250  -0.6038   0.04993   0.04091  -0.0595   0.9945   0.0548
  -9.000  -0.5715   0.04863   0.03956  -0.0604   0.9873   0.0613
  -8.750  -0.5439   0.04728   0.03814  -0.0615   0.9789   0.0693
  -8.500  -0.5215   0.04566   0.03652  -0.0630   0.9697   0.0797
  -8.250  -0.5064   0.04389   0.03478  -0.0640   0.9584   0.0915
  -8.000  -0.4978   0.04191   0.03290  -0.0648   0.9463   0.1055
  -7.750  -0.4937   0.03968   0.03081  -0.0656   0.9337   0.1223
  -7.500  -0.4888   0.03706   0.02838  -0.0670   0.9222   0.1491
  -7.250  -0.4882   0.03425   0.02597  -0.0677   0.9102   0.1935
  -7.000  -0.4859   0.03326   0.02614  -0.0650   0.8983   0.2936
  -6.750  -0.4488   0.03466   0.02752  -0.0655   0.8923   0.4087
  -6.500  -0.4363   0.03481   0.02734  -0.0643   0.8804   0.4440
  -6.250  -0.3946   0.03660   0.02883  -0.0644   0.8755   0.4755
  -6.000  -0.3759   0.03764   0.02969  -0.0618   0.8649   0.4942
  -5.750  -0.3341   0.03920   0.03101  -0.0612   0.8601   0.5127
  -5.500  -0.3175   0.03953   0.03115  -0.0591   0.8501   0.5277
  -5.250  -0.2780   0.04044   0.03184  -0.0586   0.8449   0.5386
  -5.000  -0.2580   0.04028   0.03148  -0.0576   0.8364   0.5484
  -4.750  -0.2348   0.03980   0.03079  -0.0576   0.8289   0.5577
  -4.500  -0.2110   0.03940   0.03018  -0.0575   0.8218   0.5646
  -4.250  -0.1905   0.03912   0.02973  -0.0567   0.8135   0.5707
  -4.000  -0.1627   0.03804   0.02839  -0.0586   0.8085   0.5790
  -3.750  -0.1506   0.03805   0.02832  -0.0562   0.7982   0.5828
  -3.500  -0.1199   0.03748   0.02753  -0.0573   0.7931   0.5879
  -3.250  -0.1116   0.03678   0.02665  -0.0566   0.7834   0.5950
  -3.000  -0.0821   0.03651   0.02625  -0.0568   0.7779   0.5981
  -2.750  -0.0612   0.03629   0.02590  -0.0563   0.7709   0.6018
  -2.500  -0.0415   0.03596   0.02544  -0.0560   0.7635   0.6064
  -2.250  -0.0095   0.03520   0.02445  -0.0583   0.7592   0.6122
  -2.000   0.0009   0.03533   0.02454  -0.0561   0.7499   0.6149
  -1.750   0.0294   0.03507   0.02417  -0.0566   0.7448   0.6183
  -1.500   0.0532   0.03489   0.02387  -0.0567   0.7389   0.6225
  -1.250   0.0700   0.03479   0.02366  -0.0564   0.7311   0.6273
  -1.000   0.1019   0.03447   0.02322  -0.0576   0.7269   0.6308
  -0.750   0.1147   0.03473   0.02345  -0.0559   0.7190   0.6340
  -0.500   0.1386   0.03470   0.02335  -0.0559   0.7132   0.6380
  -0.250   0.1725   0.03440   0.02293  -0.0576   0.7096   0.6428
   0.000   0.1812   0.03484   0.02334  -0.0560   0.7007   0.6469
   0.250   0.2074   0.03484   0.02330  -0.0561   0.6958   0.6501
   0.500   0.2412   0.03464   0.02304  -0.0572   0.6926   0.6542
   0.750   0.2447   0.03541   0.02381  -0.0550   0.6831   0.6588
   1.000   0.2744   0.03538   0.02371  -0.0560   0.6788   0.6637
   1.250   0.3080   0.03523   0.02354  -0.0568   0.6758   0.6677
   1.500   0.3061   0.03631   0.02466  -0.0539   0.6658   0.6718
   1.750   0.3374   0.03632   0.02463  -0.0550   0.6619   0.6770
   2.000   0.3690   0.03631   0.02460  -0.0559   0.6584   0.6819
   2.250   0.3644   0.03757   0.02592  -0.0525   0.6484   0.6862
   2.500   0.3968   0.03760   0.02594  -0.0536   0.6449   0.6921
   3.000   0.4201   0.03919   0.02761  -0.0509   0.6310   0.7025
   3.250   0.4542   0.03914   0.02757  -0.0520   0.6279   0.7089
   3.750   0.4751   0.04115   0.02970  -0.0494   0.6135   0.7211
   4.000   0.5113   0.04097   0.02954  -0.0506   0.6108   0.7293
   4.250   0.4999   0.04330   0.03198  -0.0477   0.5993   0.7352
   4.500   0.5316   0.04324   0.03197  -0.0482   0.5958   0.7437
   5.000   0.5542   0.04558   0.03450  -0.0463   0.5810   0.7608
   5.250   0.5871   0.04528   0.03431  -0.0464   0.5782   0.7709
   5.500   0.5785   0.04777   0.03690  -0.0444   0.5663   0.7812
   5.750   0.6089   0.04760   0.03686  -0.0444   0.5628   0.7943
   6.250   0.6303   0.04974   0.03929  -0.0420   0.5474   0.8238
   6.500   0.6641   0.04910   0.03883  -0.0417   0.5448   0.8457
   6.750   0.6532   0.05168   0.04160  -0.0396   0.5319   0.8738
   7.000   0.6930   0.05076   0.04091  -0.0406   0.5288   1.0000
   7.250   0.6907   0.05360   0.04376  -0.0406   0.5158   1.0000
   7.500   0.7326   0.05304   0.04326  -0.0420   0.5127   1.0000
   7.750   0.7293   0.05584   0.04607  -0.0415   0.4995   1.0000
   8.000   0.7701   0.05509   0.04539  -0.0423   0.4964   1.0000
   8.500   0.7686   0.06025   0.05064  -0.0412   0.4714   1.0000
   8.750   0.8018   0.05985   0.05033  -0.0413   0.4662   1.0000
   9.000   0.8017   0.06238   0.05292  -0.0408   0.4537   1.0000
   9.250   0.8383   0.06146   0.05212  -0.0406   0.4493   1.0000
   9.500   0.8365   0.06415   0.05488  -0.0401   0.4359   1.0000
  10.000   0.8737   0.06541   0.05634  -0.0391   0.4183   1.0000
  10.250   0.8739   0.06798   0.05901  -0.0387   0.4051   1.0000
  10.500   0.9140   0.06598   0.05716  -0.0378   0.4011   1.0000
  10.750   0.9126   0.06870   0.05997  -0.0374   0.3871   1.0000
  11.000   0.9139   0.07121   0.06257  -0.0371   0.3738   1.0000
  11.500   0.9554   0.07119   0.06283  -0.0355   0.3557   1.0000
  11.750   0.9575   0.07359   0.06533  -0.0352   0.3423   1.0000
  12.000   0.9647   0.07538   0.06723  -0.0349   0.3301   1.0000
  12.250   1.0084   0.07200   0.06404  -0.0332   0.3237   1.0000
  12.500   1.0109   0.07436   0.06649  -0.0329   0.3101   1.0000
  12.750   1.0175   0.07619   0.06843  -0.0326   0.2970   1.0000
  13.000   1.0311   0.07704   0.06938  -0.0320   0.2847   1.0000
  13.250   1.0539   0.07649   0.06892  -0.0309   0.2726   1.0000
  13.500   1.0764   0.07596   0.06841  -0.0298   0.2596   1.0000
  13.750   1.0931   0.07631   0.06877  -0.0290   0.2457   1.0000
  14.000   1.0960   0.07874   0.07126  -0.0289   0.2318   1.0000
  14.250   1.0965   0.08165   0.07423  -0.0291   0.2184   1.0000
  14.500   1.0976   0.08451   0.07714  -0.0292   0.2055   1.0000
  14.750   1.1003   0.08721   0.07987  -0.0294   0.1932   1.0000
  15.000   1.1049   0.08958   0.08223  -0.0295   0.1813   1.0000
  15.250   1.1121   0.09153   0.08412  -0.0295   0.1698   1.0000
  15.500   1.1068   0.09574   0.08846  -0.0306   0.1595   1.0000
  15.750   1.1041   0.09962   0.09241  -0.0316   0.1500   1.0000
  16.000   1.1100   0.10189   0.09462  -0.0319   0.1405   1.0000
  16.250   1.1034   0.10661   0.09949  -0.0334   0.1322   1.0000
  16.500   1.1028   0.11025   0.10318  -0.0345   0.1244   1.0000
  16.750   1.1035   0.11366   0.10663  -0.0357   0.1168   1.0000
  17.000   1.0965   0.11874   0.11185  -0.0377   0.1107   1.0000
  17.250   1.0955   0.12261   0.11578  -0.0393   0.1042   1.0000
  17.500   1.0906   0.12742   0.12068  -0.0414   0.0990   1.0000
  17.750   1.0730   0.13512   0.12860  -0.0453   0.0948   1.0000
  18.000   1.0896   0.13528   0.12863  -0.0449   0.0887   1.0000
  18.250   1.0554   0.14718   0.14083  -0.0516   0.0866   1.0000
  18.500   1.0001   0.16588   0.15964  -0.0625   0.0848   1.0000
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