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EPPLER 551 AIRFOIL (e551-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 551 AIRFOIL (e551-il)
Reynolds number: 200,000
Max Cl/Cd: 72.4 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e551-il-200000.txt
Download as CSV file: xf-e551-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.6551   0.06340   0.05850  -0.0846   1.0000   0.0212
 -12.750  -0.6636   0.05998   0.05500  -0.0846   1.0000   0.0210
 -12.500  -0.6809   0.05645   0.05131  -0.0844   1.0000   0.0210
 -12.250  -0.6911   0.05354   0.04831  -0.0835   1.0000   0.0209
 -12.000  -0.7036   0.05094   0.04560  -0.0821   1.0000   0.0208
 -11.750  -0.7197   0.04883   0.04339  -0.0795   1.0000   0.0207
 -11.500  -0.7448   0.04773   0.04224  -0.0748   1.0000   0.0207
 -11.250  -0.7625   0.04651   0.04097  -0.0713   0.9986   0.0206
 -11.000  -0.7455   0.04272   0.03679  -0.0753   0.9919   0.0207
 -10.750  -0.7245   0.03954   0.03323  -0.0784   0.9844   0.0209
 -10.500  -0.7034   0.03694   0.03026  -0.0807   0.9757   0.0214
 -10.250  -0.6651   0.03474   0.02805  -0.0830   0.9730   0.0221
 -10.000  -0.6350   0.03328   0.02654  -0.0857   0.9662   0.0241
  -9.750  -0.6015   0.03147   0.02448  -0.0877   0.9604   0.0251
  -9.500  -0.5602   0.02984   0.02290  -0.0889   0.9587   0.0263
  -9.250  -0.5239   0.02845   0.02152  -0.0911   0.9550   0.0282
  -9.000  -0.4952   0.02702   0.02004  -0.0922   0.9471   0.0307
  -8.750  -0.4600   0.02545   0.01849  -0.0959   0.9421   0.0344
  -8.500  -0.4383   0.02373   0.01680  -0.0978   0.9308   0.0394
  -8.250  -0.4192   0.02196   0.01499  -0.0994   0.9194   0.0450
  -8.000  -0.3980   0.02040   0.01339  -0.1008   0.9093   0.0572
  -7.750  -0.3895   0.01901   0.01208  -0.0996   0.8953   0.0730
  -7.500  -0.3803   0.01768   0.01089  -0.0982   0.8827   0.1051
  -7.250  -0.3731   0.01592   0.00955  -0.0969   0.8717   0.1829
  -7.000  -0.3673   0.01419   0.00875  -0.0952   0.8609   0.3549
  -6.750  -0.3432   0.01446   0.00905  -0.0944   0.8514   0.4214
  -6.500  -0.3139   0.01490   0.00934  -0.0942   0.8437   0.4494
  -6.250  -0.2878   0.01540   0.00975  -0.0934   0.8348   0.4667
  -6.000  -0.2588   0.01581   0.01002  -0.0932   0.8274   0.4806
  -5.750  -0.2330   0.01617   0.01022  -0.0926   0.8188   0.4931
  -5.500  -0.2032   0.01666   0.01074  -0.0921   0.8113   0.5015
  -5.250  -0.1771   0.01686   0.01078  -0.0916   0.8035   0.5115
  -5.000  -0.1485   0.01730   0.01124  -0.0910   0.7960   0.5186
  -4.750  -0.1211   0.01751   0.01130  -0.0908   0.7893   0.5286
  -4.500  -0.0938   0.01813   0.01199  -0.0896   0.7812   0.5363
  -4.250  -0.0655   0.01806   0.01169  -0.0899   0.7752   0.5448
  -4.000  -0.0405   0.01807   0.01170  -0.0892   0.7668   0.5479
  -3.750  -0.0121   0.01800   0.01154  -0.0892   0.7606   0.5512
  -3.500   0.0142   0.01785   0.01128  -0.0892   0.7538   0.5548
  -3.250   0.0410   0.01756   0.01083  -0.0896   0.7467   0.5589
  -3.000   0.0699   0.01729   0.01038  -0.0901   0.7412   0.5620
  -2.750   0.0949   0.01717   0.01027  -0.0897   0.7335   0.5642
  -2.500   0.1233   0.01705   0.01005  -0.0899   0.7278   0.5666
  -2.250   0.1506   0.01694   0.00987  -0.0901   0.7219   0.5691
  -2.000   0.1773   0.01682   0.00968  -0.0901   0.7151   0.5724
  -1.750   0.2068   0.01665   0.00935  -0.0908   0.7099   0.5759
  -1.500   0.2332   0.01652   0.00914  -0.0909   0.7035   0.5786
  -1.250   0.2604   0.01641   0.00901  -0.0910   0.6976   0.5806
  -1.000   0.2899   0.01635   0.00887  -0.0914   0.6930   0.5829
  -0.750   0.3155   0.01635   0.00887  -0.0912   0.6868   0.5859
  -0.500   0.3431   0.01629   0.00877  -0.0913   0.6810   0.5892
  -0.250   0.3733   0.01623   0.00858  -0.0920   0.6765   0.5924
   0.000   0.3995   0.01622   0.00854  -0.0921   0.6708   0.5954
   0.250   0.4263   0.01618   0.00852  -0.0921   0.6653   0.5977
   0.500   0.4556   0.01616   0.00846  -0.0925   0.6609   0.6004
   0.750   0.4823   0.01622   0.00853  -0.0925   0.6557   0.6037
   1.000   0.5088   0.01626   0.00857  -0.0925   0.6503   0.6075
   1.250   0.5382   0.01627   0.00850  -0.0930   0.6458   0.6113
   1.500   0.5672   0.01629   0.00850  -0.0934   0.6417   0.6142
   1.750   0.5914   0.01636   0.00867  -0.0930   0.6359   0.6171
   2.000   0.6191   0.01641   0.00873  -0.0931   0.6313   0.6207
   2.250   0.6494   0.01645   0.00872  -0.0937   0.6274   0.6249
   2.500   0.6750   0.01659   0.00888  -0.0937   0.6222   0.6293
   2.750   0.7005   0.01666   0.00904  -0.0934   0.6171   0.6329
   3.000   0.7292   0.01671   0.00911  -0.0937   0.6129   0.6370
   3.250   0.7584   0.01682   0.00920  -0.0941   0.6088   0.6418
   3.500   0.7821   0.01697   0.00943  -0.0937   0.6030   0.6465
   3.750   0.8090   0.01701   0.00955  -0.0936   0.5982   0.6505
   4.000   0.8397   0.01708   0.00959  -0.0942   0.5943   0.6556
   4.250   0.8628   0.01727   0.00989  -0.0937   0.5884   0.6617
   4.500   0.8884   0.01733   0.01004  -0.0934   0.5830   0.6668
   4.750   0.9186   0.01736   0.01007  -0.0939   0.5785   0.6730
   5.000   0.9421   0.01755   0.01035  -0.0934   0.5726   0.6798
   5.250   0.9668   0.01759   0.01051  -0.0929   0.5666   0.6854
   5.500   0.9978   0.01761   0.01050  -0.0935   0.5619   0.6930
   5.750   1.0187   0.01778   0.01085  -0.0924   0.5553   0.7000
   6.000   1.0444   0.01782   0.01096  -0.0921   0.5492   0.7085
   6.250   1.0739   0.01785   0.01101  -0.0924   0.5439   0.7174
   6.500   1.0930   0.01798   0.01133  -0.0910   0.5363   0.7274
   6.750   1.1214   0.01792   0.01130  -0.0911   0.5301   0.7374
   7.000   1.1412   0.01804   0.01159  -0.0897   0.5225   0.7489
   7.250   1.1665   0.01801   0.01163  -0.0893   0.5153   0.7619
   7.500   1.1868   0.01806   0.01184  -0.0879   0.5076   0.7757
   7.750   1.2088   0.01802   0.01191  -0.0868   0.4994   0.7921
   8.000   1.2271   0.01806   0.01211  -0.0851   0.4910   0.8118
   8.250   1.2459   0.01796   0.01213  -0.0832   0.4823   0.8351
   8.500   1.2579   0.01796   0.01234  -0.0802   0.4731   0.8695
   8.750   1.2792   0.01771   0.01223  -0.0788   0.4635   1.0000
   9.000   1.2960   0.01790   0.01250  -0.0774   0.4515   1.0000
   9.250   1.3111   0.01813   0.01276  -0.0755   0.4392   1.0000
   9.500   1.3233   0.01835   0.01300  -0.0730   0.4262   1.0000
   9.750   1.3316   0.01865   0.01330  -0.0699   0.4124   1.0000
  10.000   1.3378   0.01906   0.01372  -0.0665   0.3972   1.0000
  10.250   1.3421   0.01961   0.01428  -0.0631   0.3805   1.0000
  10.500   1.3445   0.02033   0.01498  -0.0597   0.3621   1.0000
  10.750   1.3449   0.02127   0.01586  -0.0563   0.3425   1.0000
  11.000   1.3429   0.02247   0.01697  -0.0529   0.3225   1.0000
  11.250   1.3403   0.02388   0.01832  -0.0498   0.3015   1.0000
  11.500   1.3358   0.02555   0.01991  -0.0468   0.2814   1.0000
  11.750   1.3302   0.02746   0.02173  -0.0441   0.2625   1.0000
  12.000   1.3253   0.02950   0.02371  -0.0418   0.2445   1.0000
  12.250   1.3206   0.03168   0.02585  -0.0398   0.2271   1.0000
  12.500   1.3156   0.03402   0.02814  -0.0380   0.2106   1.0000
  12.750   1.3108   0.03648   0.03056  -0.0365   0.1956   1.0000
  13.000   1.3058   0.03908   0.03313  -0.0352   0.1812   1.0000
  13.250   1.3009   0.04181   0.03582  -0.0341   0.1677   1.0000
  13.500   1.2955   0.04470   0.03866  -0.0332   0.1552   1.0000
  13.750   1.2912   0.04763   0.04157  -0.0326   0.1431   1.0000
  14.000   1.2883   0.05055   0.04450  -0.0321   0.1315   1.0000
  14.250   1.2852   0.05358   0.04754  -0.0318   0.1209   1.0000
  14.500   1.2811   0.05680   0.05074  -0.0316   0.1114   1.0000
  14.750   1.2764   0.06019   0.05409  -0.0316   0.1027   1.0000
  15.000   1.2753   0.06329   0.05725  -0.0317   0.0940   1.0000
  15.250   1.2716   0.06673   0.06067  -0.0318   0.0870   1.0000
  15.500   1.2692   0.07014   0.06409  -0.0322   0.0802   1.0000
  15.750   1.2675   0.07350   0.06749  -0.0325   0.0738   1.0000
  16.000   1.2643   0.07713   0.07110  -0.0331   0.0686   1.0000
  16.250   1.2637   0.08049   0.07454  -0.0336   0.0633   1.0000
  16.500   1.2616   0.08410   0.07816  -0.0344   0.0590   1.0000
  16.750   1.2609   0.08758   0.08171  -0.0350   0.0547   1.0000
  17.000   1.2600   0.09116   0.08533  -0.0360   0.0512   1.0000
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