Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

EPPLER 551 AIRFOIL (e551-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 551 AIRFOIL (e551-il)
Reynolds number: 1,000,000
Max Cl/Cd: 125.33 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e551-il-1000000.txt
Download as CSV file: xf-e551-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -18.000  -0.6137   0.13534   0.13325  -0.0401   1.0000   0.0048
 -17.750  -0.6630   0.11985   0.11753  -0.0476   1.0000   0.0047
 -17.500  -0.6981   0.10852   0.10600  -0.0533   1.0000   0.0046
 -17.250  -0.7259   0.09927   0.09657  -0.0579   1.0000   0.0045
 -17.000  -0.7405   0.09286   0.09004  -0.0611   1.0000   0.0045
 -16.750  -0.7589   0.08609   0.08312  -0.0643   1.0000   0.0044
 -16.500  -0.7725   0.08044   0.07734  -0.0668   1.0000   0.0044
 -16.250  -0.7862   0.07502   0.07178  -0.0691   1.0000   0.0044
 -16.000  -0.7940   0.07068   0.06733  -0.0707   1.0000   0.0044
 -15.750  -0.8012   0.06659   0.06313  -0.0722   1.0000   0.0043
 -15.500  -0.8088   0.06261   0.05903  -0.0734   1.0000   0.0043
 -15.250  -0.8124   0.05924   0.05557  -0.0744   1.0000   0.0044
 -15.000  -0.8176   0.05586   0.05208  -0.0751   1.0000   0.0043
 -14.750  -0.8195   0.05297   0.04910  -0.0756   1.0000   0.0043
 -14.500  -0.8231   0.05000   0.04605  -0.0759   1.0000   0.0044
 -14.250  -0.8234   0.04751   0.04348  -0.0760   1.0000   0.0043
 -14.000  -0.8240   0.04510   0.04099  -0.0760   1.0000   0.0044
 -13.750  -0.8243   0.04292   0.03874  -0.0757   1.0000   0.0043
 -13.500  -0.8253   0.04073   0.03649  -0.0752   1.0000   0.0044
 -13.250  -0.8259   0.03872   0.03441  -0.0746   1.0000   0.0044
 -13.000  -0.8256   0.03688   0.03251  -0.0737   1.0000   0.0044
 -12.750  -0.8263   0.03509   0.03067  -0.0726   1.0000   0.0044
 -12.500  -0.8172   0.03304   0.02855  -0.0736   0.9992   0.0045
 -12.250  -0.7940   0.03089   0.02632  -0.0773   0.9965   0.0046
 -12.000  -0.7727   0.02894   0.02431  -0.0802   0.9907   0.0046
 -11.750  -0.7585   0.02710   0.02240  -0.0815   0.9742   0.0047
 -11.500  -0.7320   0.02525   0.02047  -0.0851   0.9601   0.0049
 -11.250  -0.6939   0.02333   0.01845  -0.0912   0.9500   0.0050
 -11.000  -0.6442   0.02162   0.01664  -0.0991   0.9417   0.0052
 -10.750  -0.5974   0.01922   0.01409  -0.1082   0.9234   0.0058
 -10.500  -0.5702   0.01806   0.01276  -0.1110   0.8950   0.0061
 -10.250  -0.5613   0.01708   0.01163  -0.1100   0.8710   0.0059
 -10.000  -0.5543   0.01631   0.01075  -0.1081   0.8518   0.0067
  -9.750  -0.5545   0.01559   0.00991  -0.1048   0.8351   0.0068
  -9.500  -0.5442   0.01511   0.00933  -0.1026   0.8223   0.0070
  -9.250  -0.5310   0.01459   0.00871  -0.1008   0.8103   0.0073
  -9.000  -0.5170   0.01399   0.00806  -0.0992   0.8000   0.0083
  -8.750  -0.4984   0.01361   0.00759  -0.0981   0.7906   0.0088
  -8.500  -0.4794   0.01314   0.00707  -0.0971   0.7813   0.0100
  -8.250  -0.4586   0.01277   0.00664  -0.0963   0.7727   0.0113
  -8.000  -0.4377   0.01235   0.00619  -0.0956   0.7639   0.0139
  -7.750  -0.4157   0.01198   0.00578  -0.0949   0.7561   0.0177
  -7.500  -0.3931   0.01159   0.00540  -0.0944   0.7482   0.0241
  -7.250  -0.3701   0.01124   0.00504  -0.0940   0.7407   0.0326
  -7.000  -0.3461   0.01088   0.00471  -0.0937   0.7331   0.0435
  -6.750  -0.3227   0.01051   0.00438  -0.0933   0.7255   0.0601
  -6.500  -0.2986   0.01008   0.00404  -0.0930   0.7183   0.0835
  -6.250  -0.2752   0.00960   0.00368  -0.0928   0.7111   0.1201
  -6.000  -0.2522   0.00896   0.00327  -0.0925   0.7046   0.1773
  -5.750  -0.2313   0.00796   0.00269  -0.0922   0.6976   0.2817
  -5.500  -0.2078   0.00732   0.00239  -0.0921   0.6910   0.3822
  -5.250  -0.1796   0.00723   0.00234  -0.0923   0.6843   0.4093
  -5.000  -0.1515   0.00722   0.00230  -0.0924   0.6775   0.4236
  -4.750  -0.1227   0.00722   0.00225  -0.0926   0.6712   0.4317
  -4.500  -0.0941   0.00723   0.00222  -0.0928   0.6648   0.4392
  -4.250  -0.0656   0.00729   0.00218  -0.0929   0.6587   0.4451
  -4.000  -0.0368   0.00726   0.00216  -0.0931   0.6527   0.4512
  -3.750  -0.0082   0.00731   0.00215  -0.0933   0.6463   0.4567
  -3.500   0.0203   0.00735   0.00215  -0.0935   0.6404   0.4641
  -3.250   0.0492   0.00742   0.00220  -0.0937   0.6345   0.4712
  -3.000   0.0777   0.00746   0.00218  -0.0938   0.6287   0.4742
  -2.750   0.1065   0.00748   0.00213  -0.0941   0.6234   0.4757
  -2.500   0.1353   0.00747   0.00209  -0.0943   0.6177   0.4773
  -2.250   0.1633   0.00744   0.00203  -0.0944   0.6120   0.4799
  -2.000   0.1919   0.00743   0.00200  -0.0947   0.6068   0.4821
  -1.750   0.2207   0.00743   0.00198  -0.0949   0.6015   0.4839
  -1.500   0.2490   0.00746   0.00196  -0.0950   0.5963   0.4858
  -1.250   0.2775   0.00748   0.00195  -0.0952   0.5915   0.4877
  -1.000   0.3063   0.00749   0.00195  -0.0955   0.5864   0.4897
  -0.750   0.3347   0.00753   0.00194  -0.0957   0.5813   0.4916
  -0.500   0.3629   0.00759   0.00196  -0.0958   0.5765   0.4932
  -0.250   0.3917   0.00755   0.00194  -0.0961   0.5722   0.4958
   0.000   0.4200   0.00756   0.00194  -0.0963   0.5674   0.4982
   0.250   0.4479   0.00761   0.00197  -0.0963   0.5625   0.5004
   0.500   0.4764   0.00763   0.00199  -0.0966   0.5584   0.5025
   0.750   0.5050   0.00766   0.00202  -0.0968   0.5541   0.5048
   1.000   0.5332   0.00771   0.00205  -0.0969   0.5495   0.5070
   1.250   0.5608   0.00780   0.00210  -0.0970   0.5447   0.5091
   1.500   0.5895   0.00780   0.00212  -0.0972   0.5411   0.5116
   1.750   0.6177   0.00781   0.00216  -0.0974   0.5367   0.5147
   2.000   0.6454   0.00786   0.00221  -0.0975   0.5323   0.5174
   2.250   0.6730   0.00794   0.00228  -0.0975   0.5277   0.5200
   2.500   0.7015   0.00796   0.00233  -0.0978   0.5236   0.5227
   2.750   0.7293   0.00802   0.00239  -0.0979   0.5190   0.5253
   3.000   0.7564   0.00811   0.00245  -0.0978   0.5139   0.5278
   3.250   0.7842   0.00814   0.00252  -0.0979   0.5096   0.5314
   3.500   0.8121   0.00817   0.00259  -0.0981   0.5048   0.5348
   3.750   0.8391   0.00825   0.00267  -0.0980   0.4999   0.5385
   4.000   0.8661   0.00835   0.00277  -0.0980   0.4952   0.5418
   4.250   0.8940   0.00839   0.00285  -0.0981   0.4907   0.5451
   4.500   0.9210   0.00844   0.00294  -0.0981   0.4857   0.5493
   4.750   0.9469   0.00857   0.00305  -0.0978   0.4800   0.5534
   5.000   0.9746   0.00860   0.00315  -0.0979   0.4751   0.5576
   5.250   1.0012   0.00869   0.00325  -0.0978   0.4694   0.5614
   5.500   1.0267   0.00880   0.00338  -0.0975   0.4635   0.5665
   5.750   1.0538   0.00886   0.00349  -0.0975   0.4578   0.5717
   6.000   1.0792   0.00898   0.00362  -0.0972   0.4510   0.5769
   6.250   1.1050   0.00907   0.00376  -0.0970   0.4441   0.5828
   6.500   1.1303   0.00918   0.00390  -0.0967   0.4365   0.5892
   6.750   1.1551   0.00932   0.00406  -0.0962   0.4287   0.5950
   7.000   1.1791   0.00946   0.00423  -0.0957   0.4191   0.6022
   7.250   1.2032   0.00960   0.00440  -0.0952   0.4088   0.6096
   7.500   1.2255   0.00980   0.00460  -0.0943   0.3962   0.6172
   7.750   1.2463   0.01005   0.00483  -0.0932   0.3801   0.6257
   8.000   1.2653   0.01034   0.00510  -0.0918   0.3615   0.6343
   8.250   1.2797   0.01071   0.00541  -0.0895   0.3404   0.6440
   8.500   1.2916   0.01114   0.00577  -0.0867   0.3173   0.6545
   8.750   1.3001   0.01172   0.00626  -0.0835   0.2920   0.6656
   9.000   1.3100   0.01227   0.00675  -0.0806   0.2688   0.6781
   9.250   1.3184   0.01288   0.00731  -0.0775   0.2478   0.6918
   9.500   1.3265   0.01350   0.00789  -0.0745   0.2284   0.7067
   9.750   1.3340   0.01417   0.00853  -0.0715   0.2097   0.7238
  10.000   1.3407   0.01488   0.00923  -0.0685   0.1927   0.7438
  10.250   1.3445   0.01573   0.01007  -0.0652   0.1746   0.7682
  10.500   1.3489   0.01657   0.01095  -0.0622   0.1596   0.8016
  10.750   1.3506   0.01736   0.01189  -0.0587   0.1461   0.8679
  11.000   1.3582   0.01823   0.01288  -0.0567   0.1329   1.0000
  11.250   1.3627   0.01943   0.01403  -0.0543   0.1202   1.0000
  11.500   1.3666   0.02073   0.01529  -0.0521   0.1082   1.0000
  11.750   1.3715   0.02205   0.01658  -0.0501   0.0987   1.0000
  12.000   1.3748   0.02354   0.01803  -0.0482   0.0891   1.0000
  12.250   1.3787   0.02507   0.01953  -0.0465   0.0803   1.0000
  12.500   1.3828   0.02665   0.02110  -0.0449   0.0722   1.0000
  12.750   1.3860   0.02836   0.02279  -0.0434   0.0650   1.0000
  13.000   1.3881   0.03021   0.02463  -0.0420   0.0583   1.0000
  13.250   1.3916   0.03203   0.02645  -0.0408   0.0523   1.0000
  13.500   1.3947   0.03395   0.02838  -0.0398   0.0474   1.0000
  13.750   1.3968   0.03603   0.03045  -0.0387   0.0426   1.0000
  14.000   1.4009   0.03799   0.03244  -0.0380   0.0388   1.0000
  14.250   1.4024   0.04026   0.03472  -0.0372   0.0350   1.0000
  14.500   1.4062   0.04238   0.03686  -0.0366   0.0317   1.0000
  14.750   1.4085   0.04470   0.03920  -0.0361   0.0289   1.0000
  15.000   1.4113   0.04703   0.04156  -0.0357   0.0263   1.0000
  15.250   1.4136   0.04948   0.04405  -0.0354   0.0242   1.0000
  15.500   1.4170   0.05187   0.04648  -0.0352   0.0223   1.0000
  15.750   1.4184   0.05451   0.04915  -0.0351   0.0204   1.0000
  16.000   1.4213   0.05707   0.05176  -0.0351   0.0188   1.0000
  16.250   1.4218   0.05995   0.05467  -0.0352   0.0172   1.0000
  16.500   1.4253   0.06254   0.05732  -0.0354   0.0160   1.0000
  16.750   1.4256   0.06555   0.06037  -0.0357   0.0147   1.0000
  17.000   1.4265   0.06856   0.06344  -0.0360   0.0138   1.0000
  17.250   1.4290   0.07142   0.06635  -0.0365   0.0127   1.0000
  17.500   1.4281   0.07478   0.06977  -0.0371   0.0117   1.0000
  17.750   1.4287   0.07798   0.07303  -0.0377   0.0109   1.0000
  18.000   1.4294   0.08123   0.07634  -0.0385   0.0101   1.0000
  18.250   1.4276   0.08487   0.08004  -0.0394   0.0094   1.0000
  18.500   1.4271   0.08841   0.08364  -0.0403   0.0087   1.0000
  18.750   1.4265   0.09199   0.08730  -0.0414   0.0082   1.0000
  19.000   1.4240   0.09589   0.09126  -0.0426   0.0076   1.0000
  19.250   1.4203   0.10003   0.09548  -0.0440   0.0072   1.0000
<< Back to EPPLER 551 AIRFOIL (e551-il)

Polar data table (+)

Polar graphs


<< Back to EPPLER 551 AIRFOIL (e551-il)