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

E209 (13.72%) (e209-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: E209 (13.72%) (e209-il)
Reynolds number: 1,000,000
Max Cl/Cd: 121.64 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e209-il-1000000.txt
Download as CSV file: xf-e209-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E209  (13.72%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -16.000  -0.7738   0.10041   0.09824  -0.0336   1.0000   0.0069
 -15.750  -0.8197   0.08706   0.08470  -0.0410   1.0000   0.0068
 -15.500  -0.8391   0.07927   0.07679  -0.0456   1.0000   0.0068
 -15.250  -0.8546   0.07257   0.06998  -0.0496   1.0000   0.0068
 -15.000  -0.8771   0.06521   0.06248  -0.0539   1.0000   0.0068
 -14.750  -0.9020   0.05805   0.05515  -0.0579   1.0000   0.0067
 -14.500  -0.9205   0.05218   0.04912  -0.0611   1.0000   0.0067
 -14.250  -0.9234   0.04858   0.04543  -0.0632   1.0000   0.0068
 -14.000  -0.9390   0.04355   0.04024  -0.0655   1.0000   0.0067
 -13.750  -0.9390   0.04062   0.03722  -0.0669   1.0000   0.0069
 -13.500  -0.9470   0.03696   0.03341  -0.0682   1.0000   0.0069
 -13.250  -0.9537   0.03373   0.03003  -0.0689   1.0000   0.0069
 -13.000  -0.9479   0.03206   0.02829  -0.0690   1.0000   0.0071
 -12.750  -0.9541   0.02953   0.02562  -0.0683   1.0000   0.0071
 -12.500  -0.9551   0.02788   0.02386  -0.0668   1.0000   0.0072
 -12.250  -0.9601   0.02637   0.02225  -0.0640   1.0000   0.0072
 -12.000  -0.9675   0.02531   0.02110  -0.0597   1.0000   0.0073
 -11.750  -0.9680   0.02469   0.02040  -0.0556   1.0000   0.0074
 -11.500  -0.9679   0.02353   0.01913  -0.0520   1.0000   0.0074
 -11.250  -0.9596   0.02285   0.01837  -0.0493   1.0000   0.0075
 -11.000  -0.9521   0.02202   0.01745  -0.0464   1.0000   0.0076
 -10.750  -0.9545   0.02031   0.01559  -0.0423   1.0000   0.0078
 -10.500  -0.9407   0.01914   0.01435  -0.0409   0.9994   0.0082
 -10.250  -0.9090   0.01834   0.01349  -0.0426   0.9975   0.0085
 -10.000  -0.8756   0.01775   0.01286  -0.0444   0.9957   0.0089
  -9.750  -0.8419   0.01703   0.01208  -0.0463   0.9940   0.0092
  -9.500  -0.8113   0.01642   0.01141  -0.0475   0.9912   0.0097
  -9.250  -0.7776   0.01608   0.01101  -0.0490   0.9887   0.0102
  -9.000  -0.7477   0.01477   0.00961  -0.0505   0.9858   0.0109
  -8.750  -0.7126   0.01413   0.00894  -0.0525   0.9840   0.0115
  -8.500  -0.6809   0.01366   0.00844  -0.0537   0.9806   0.0123
  -8.250  -0.6494   0.01316   0.00789  -0.0547   0.9763   0.0130
  -8.000  -0.6151   0.01254   0.00721  -0.0564   0.9729   0.0139
  -7.750  -0.5867   0.01192   0.00656  -0.0569   0.9665   0.0151
  -7.500  -0.5566   0.01152   0.00614  -0.0575   0.9580   0.0164
  -7.250  -0.5275   0.01123   0.00580  -0.0579   0.9453   0.0174
  -7.000  -0.4988   0.01062   0.00512  -0.0582   0.9278   0.0195
  -6.750  -0.4709   0.01031   0.00473  -0.0583   0.9013   0.0213
  -6.500  -0.4455   0.01012   0.00439  -0.0577   0.8707   0.0226
  -6.250  -0.4222   0.00982   0.00398  -0.0568   0.8420   0.0262
  -6.000  -0.3980   0.00962   0.00368  -0.0561   0.8161   0.0310
  -5.500  -0.3505   0.00903   0.00309  -0.0546   0.7710   0.0653
  -5.250  -0.3257   0.00879   0.00286  -0.0541   0.7517   0.0859
  -5.000  -0.3006   0.00858   0.00265  -0.0537   0.7341   0.1080
  -4.750  -0.2755   0.00833   0.00245  -0.0532   0.7179   0.1364
  -4.500  -0.2502   0.00807   0.00226  -0.0529   0.7031   0.1689
  -4.250  -0.2247   0.00781   0.00208  -0.0525   0.6895   0.2055
  -4.000  -0.1991   0.00754   0.00192  -0.0522   0.6769   0.2477
  -3.750  -0.1742   0.00720   0.00175  -0.0519   0.6654   0.3064
  -3.500  -0.1486   0.00695   0.00163  -0.0515   0.6546   0.3613
  -3.250  -0.1218   0.00680   0.00157  -0.0514   0.6446   0.4035
  -3.000  -0.0946   0.00674   0.00153  -0.0512   0.6351   0.4296
  -2.750  -0.0669   0.00672   0.00148  -0.0512   0.6261   0.4431
  -2.500  -0.0389   0.00669   0.00144  -0.0511   0.6179   0.4559
  -2.250  -0.0113   0.00669   0.00141  -0.0511   0.6097   0.4690
  -2.000   0.0169   0.00668   0.00138  -0.0511   0.6023   0.4813
  -1.750   0.0447   0.00668   0.00136  -0.0510   0.5950   0.4911
  -1.500   0.0728   0.00667   0.00133  -0.0511   0.5882   0.4999
  -1.250   0.1008   0.00668   0.00132  -0.0510   0.5812   0.5089
  -1.000   0.1288   0.00667   0.00131  -0.0510   0.5751   0.5179
  -0.750   0.1570   0.00668   0.00130  -0.0511   0.5686   0.5270
  -0.500   0.1847   0.00669   0.00130  -0.0510   0.5625   0.5367
  -0.250   0.2130   0.00667   0.00130  -0.0511   0.5565   0.5458
   0.000   0.2409   0.00670   0.00130  -0.0511   0.5506   0.5558
   0.250   0.2689   0.00669   0.00132  -0.0510   0.5450   0.5664
   0.500   0.2969   0.00668   0.00133  -0.0511   0.5389   0.5776
   0.750   0.3245   0.00672   0.00136  -0.0510   0.5333   0.5896
   1.000   0.3527   0.00670   0.00138  -0.0510   0.5280   0.6027
   1.250   0.3804   0.00670   0.00141  -0.0510   0.5221   0.6165
   1.500   0.4080   0.00672   0.00145  -0.0509   0.5167   0.6311
   1.750   0.4359   0.00670   0.00149  -0.0509   0.5112   0.6470
   2.000   0.4633   0.00672   0.00154  -0.0509   0.5053   0.6646
   2.250   0.4908   0.00671   0.00159  -0.0508   0.4997   0.6841
   2.500   0.5181   0.00670   0.00165  -0.0506   0.4931   0.7056
   2.750   0.5450   0.00671   0.00171  -0.0504   0.4863   0.7294
   3.000   0.5721   0.00669   0.00178  -0.0503   0.4791   0.7571
   3.250   0.5982   0.00669   0.00186  -0.0499   0.4723   0.7875
   3.500   0.6245   0.00665   0.00194  -0.0495   0.4654   0.8208
   3.750   0.6493   0.00666   0.00204  -0.0488   0.4580   0.8586
   4.000   0.6740   0.00661   0.00214  -0.0479   0.4510   0.9024
   4.250   0.7009   0.00667   0.00226  -0.0476   0.4429   0.9461
   4.500   0.7353   0.00675   0.00236  -0.0489   0.4339   0.9706
   4.750   0.7718   0.00687   0.00247  -0.0509   0.4243   0.9834
   5.000   0.8103   0.00702   0.00259  -0.0533   0.4131   0.9902
   5.250   0.8476   0.00715   0.00270  -0.0555   0.4014   0.9963
   5.500   0.8826   0.00730   0.00283  -0.0572   0.3886   1.0000
   5.750   0.9053   0.00745   0.00296  -0.0562   0.3762   1.0000
   6.000   0.9281   0.00763   0.00310  -0.0553   0.3631   1.0000
   6.250   0.9505   0.00783   0.00326  -0.0543   0.3469   1.0000
   6.500   0.9721   0.00811   0.00346  -0.0531   0.3262   1.0000
   6.750   0.9925   0.00849   0.00370  -0.0518   0.2954   1.0000
   7.000   1.0121   0.00895   0.00400  -0.0505   0.2597   1.0000
   7.250   1.0306   0.00951   0.00438  -0.0489   0.2232   1.0000
   7.500   1.0498   0.01004   0.00476  -0.0476   0.1928   1.0000
   7.750   1.0686   0.01059   0.00516  -0.0462   0.1636   1.0000
   8.000   1.0872   0.01116   0.00559  -0.0447   0.1370   1.0000
   8.250   1.1055   0.01173   0.00602  -0.0433   0.1134   1.0000
   8.500   1.1240   0.01227   0.00647  -0.0419   0.0933   1.0000
   8.750   1.1419   0.01282   0.00693  -0.0404   0.0770   1.0000
   9.000   1.1604   0.01332   0.00737  -0.0390   0.0652   1.0000
   9.250   1.1783   0.01382   0.00783  -0.0375   0.0548   1.0000
   9.500   1.1956   0.01433   0.00830  -0.0359   0.0459   1.0000
   9.750   1.2118   0.01486   0.00881  -0.0341   0.0383   1.0000
  10.000   1.2252   0.01542   0.00933  -0.0319   0.0318   1.0000
  10.250   1.2364   0.01598   0.00987  -0.0292   0.0270   1.0000
  10.500   1.2485   0.01652   0.01043  -0.0268   0.0234   1.0000
  10.750   1.2580   0.01721   0.01111  -0.0241   0.0199   1.0000
  11.000   1.2704   0.01780   0.01173  -0.0220   0.0180   1.0000
  11.250   1.2789   0.01860   0.01254  -0.0195   0.0158   1.0000
  11.500   1.2897   0.01931   0.01331  -0.0174   0.0144   1.0000
  11.750   1.2988   0.02016   0.01420  -0.0153   0.0131   1.0000
  12.000   1.3033   0.02133   0.01540  -0.0128   0.0115   1.0000
  12.250   1.3130   0.02226   0.01640  -0.0112   0.0109   1.0000
  12.500   1.3206   0.02339   0.01758  -0.0095   0.0102   1.0000
  12.750   1.3237   0.02493   0.01916  -0.0077   0.0092   1.0000
  13.000   1.3261   0.02665   0.02096  -0.0062   0.0087   1.0000
  13.250   1.3349   0.02797   0.02234  -0.0052   0.0082   1.0000
  13.500   1.3413   0.02955   0.02400  -0.0043   0.0077   1.0000
  13.750   1.3451   0.03145   0.02596  -0.0035   0.0075   1.0000
  14.000   1.3492   0.03338   0.02795  -0.0029   0.0070   1.0000
  14.250   1.3500   0.03571   0.03036  -0.0024   0.0069   1.0000
  14.500   1.3452   0.03870   0.03344  -0.0019   0.0066   1.0000
  14.750   1.3451   0.04130   0.03613  -0.0017   0.0063   1.0000
  15.000   1.3448   0.04399   0.03892  -0.0017   0.0062   1.0000
  15.250   1.3448   0.04672   0.04173  -0.0018   0.0061   1.0000
  15.500   1.3475   0.04920   0.04429  -0.0020   0.0059   1.0000
  15.750   1.3457   0.05230   0.04748  -0.0023   0.0058   1.0000
  16.000   1.3425   0.05564   0.05090  -0.0028   0.0056   1.0000
  16.250   1.3397   0.05904   0.05440  -0.0035   0.0055   1.0000
  16.500   1.3373   0.06250   0.05794  -0.0043   0.0054   1.0000
  16.750   1.3316   0.06650   0.06205  -0.0054   0.0054   1.0000
  17.000   1.3270   0.07044   0.06608  -0.0065   0.0053   1.0000
  17.250   1.3213   0.07467   0.07040  -0.0079   0.0052   1.0000
  17.500   1.3174   0.07872   0.07453  -0.0093   0.0051   1.0000
  17.750   1.3066   0.08393   0.07985  -0.0113   0.0050   1.0000
  18.000   1.2991   0.08876   0.08477  -0.0132   0.0049   1.0000
  18.250   1.2832   0.09511   0.09123  -0.0159   0.0048   1.0000
  18.500   1.2778   0.09983   0.09605  -0.0180   0.0048   1.0000
  18.750   1.2639   0.10610   0.10244  -0.0208   0.0048   1.0000
  19.000   1.2513   0.11232   0.10877  -0.0238   0.0047   1.0000
  19.250   1.2451   0.11750   0.11404  -0.0264   0.0047   1.0000
<< Back to E209 (13.72%) (e209-il)

Polar data table (+)

Polar graphs


<< Back to E209 (13.72%) (e209-il)