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EPPLER 1210 AIRFOIL (e1210-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 1210 AIRFOIL (e1210-il)
Reynolds number: 200,000
Max Cl/Cd: 60.33 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e1210-il-200000.txt
Download as CSV file: xf-e1210-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 1210 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.1955   0.10792   0.10463  -0.0340   1.0000   0.0743
  -9.750  -0.1878   0.10564   0.10241  -0.0337   1.0000   0.0760
  -9.500  -0.5009   0.03527   0.03094  -0.0931   0.9543   0.0554
  -9.000  -0.3437   0.05300   0.04981  -0.0793   0.9377   0.0607
  -8.750  -0.3805   0.03061   0.02577  -0.1050   0.8962   0.0648
  -8.500  -0.3499   0.02887   0.02370  -0.1071   0.8700   0.0679
  -8.250  -0.3207   0.02864   0.02335  -0.1073   0.8447   0.0708
  -8.000  -0.3036   0.02696   0.02123  -0.1067   0.8214   0.0741
  -7.750  -0.2759   0.02755   0.02189  -0.1059   0.8005   0.0765
  -7.500  -0.2601   0.02557   0.01928  -0.1051   0.7828   0.0807
  -7.250  -0.2332   0.02596   0.01982  -0.1043   0.7647   0.0829
  -7.000  -0.2107   0.02528   0.01890  -0.1035   0.7483   0.0865
  -6.750  -0.1888   0.02426   0.01760  -0.1028   0.7336   0.0898
  -6.500  -0.1628   0.02430   0.01761  -0.1021   0.7197   0.0926
  -6.250  -0.1405   0.02320   0.01604  -0.1014   0.7056   0.0969
  -6.000  -0.1153   0.02272   0.01558  -0.1008   0.6927   0.0996
  -5.750  -0.0895   0.02243   0.01519  -0.1002   0.6802   0.1029
  -5.500  -0.0651   0.02163   0.01399  -0.0995   0.6679   0.1072
  -5.250  -0.0391   0.02119   0.01353  -0.0990   0.6570   0.1102
  -5.000  -0.0131   0.02084   0.01313  -0.0985   0.6447   0.1140
  -4.750   0.0130   0.02032   0.01223  -0.0979   0.6347   0.1182
  -4.500   0.0390   0.01978   0.01177  -0.0975   0.6233   0.1217
  -4.250   0.0658   0.01954   0.01138  -0.0969   0.6135   0.1259
  -4.000   0.0927   0.01925   0.01084  -0.0964   0.6027   0.1301
  -3.750   0.1190   0.01865   0.01024  -0.0960   0.5938   0.1342
  -3.500   0.1459   0.01839   0.00993  -0.0955   0.5834   0.1388
  -3.250   0.1734   0.01826   0.00952  -0.0950   0.5748   0.1434
  -3.000   0.1997   0.01767   0.00902  -0.0946   0.5649   0.1480
  -2.750   0.2270   0.01751   0.00875  -0.0942   0.5567   0.1532
  -2.500   0.2544   0.01738   0.00850  -0.0937   0.5477   0.1583
  -2.250   0.2811   0.01693   0.00805  -0.0933   0.5392   0.1637
  -2.000   0.3084   0.01681   0.00788  -0.0929   0.5310   0.1698
  -1.750   0.3357   0.01669   0.00765  -0.0925   0.5224   0.1756
  -1.500   0.3628   0.01643   0.00737  -0.0921   0.5155   0.1824
  -1.250   0.3898   0.01630   0.00726  -0.0916   0.5070   0.1898
  -1.000   0.4167   0.01608   0.00701  -0.0912   0.4995   0.1976
  -0.750   0.4439   0.01604   0.00694  -0.0908   0.4923   0.2067
  -0.500   0.4706   0.01586   0.00681  -0.0904   0.4845   0.2167
  -0.250   0.4980   0.01584   0.00672  -0.0900   0.4781   0.2290
   0.000   0.5245   0.01573   0.00670  -0.0896   0.4709   0.2440
   0.250   0.5512   0.01560   0.00665  -0.0891   0.4638   0.2643
   0.500   0.5783   0.01555   0.00661  -0.0888   0.4577   0.2957
   0.750   0.6039   0.01533   0.00671  -0.0883   0.4511   0.3555
   1.000   0.6281   0.01494   0.00682  -0.0876   0.4447   0.4925
   1.250   0.6475   0.01444   0.00698  -0.0854   0.4395   0.7127
   1.500   0.6906   0.01411   0.00707  -0.0874   0.4321   1.0000
   1.750   0.7169   0.01430   0.00712  -0.0869   0.4260   1.0000
   2.000   0.7439   0.01456   0.00719  -0.0865   0.4208   1.0000
   2.250   0.7698   0.01481   0.00738  -0.0860   0.4151   1.0000
   2.500   0.7958   0.01501   0.00752  -0.0855   0.4091   1.0000
   2.750   0.8225   0.01524   0.00761  -0.0851   0.4041   1.0000
   3.000   0.8492   0.01558   0.00783  -0.0848   0.3992   1.0000
   3.250   0.8746   0.01582   0.00807  -0.0842   0.3939   1.0000
   3.500   0.9008   0.01605   0.00823  -0.0838   0.3888   1.0000
   3.750   0.9277   0.01635   0.00839  -0.0835   0.3842   1.0000
   4.000   0.9532   0.01668   0.00870  -0.0830   0.3794   1.0000
   4.250   0.9784   0.01694   0.00896  -0.0824   0.3744   1.0000
   4.500   1.0045   0.01722   0.00917  -0.0820   0.3701   1.0000
   4.750   1.0314   0.01758   0.00940  -0.0818   0.3661   1.0000
   5.000   1.0563   0.01796   0.00979  -0.0813   0.3618   1.0000
   5.250   1.0807   0.01825   0.01011  -0.0806   0.3571   1.0000
   5.500   1.1061   0.01853   0.01035  -0.0801   0.3528   1.0000
   5.750   1.1326   0.01889   0.01060  -0.0799   0.3490   1.0000
   6.000   1.1579   0.01937   0.01106  -0.0795   0.3453   1.0000
   6.250   1.1809   0.01973   0.01150  -0.0787   0.3413   1.0000
   6.500   1.2052   0.02007   0.01184  -0.0781   0.3372   1.0000
   6.750   1.2307   0.02040   0.01211  -0.0777   0.3336   1.0000
   7.000   1.2582   0.02094   0.01252  -0.0777   0.3300   1.0000
   7.250   1.2789   0.02135   0.01306  -0.0766   0.3264   1.0000
   7.500   1.3011   0.02178   0.01355  -0.0758   0.3226   1.0000
   7.750   1.3248   0.02218   0.01396  -0.0752   0.3192   1.0000
   8.000   1.3500   0.02258   0.01430  -0.0748   0.3161   1.0000
   8.250   1.3779   0.02323   0.01483  -0.0750   0.3128   1.0000
   8.500   1.3951   0.02370   0.01548  -0.0735   0.3095   1.0000
   8.750   1.4149   0.02419   0.01606  -0.0724   0.3059   1.0000
   9.000   1.4369   0.02465   0.01654  -0.0716   0.3027   1.0000
   9.250   1.4610   0.02510   0.01696  -0.0712   0.2999   1.0000
   9.500   1.4880   0.02569   0.01747  -0.0713   0.2971   1.0000
   9.750   1.5059   0.02643   0.01831  -0.0701   0.2943   1.0000
  10.000   1.5207   0.02707   0.01910  -0.0684   0.2911   1.0000
  10.250   1.5382   0.02764   0.01975  -0.0671   0.2880   1.0000
  10.500   1.5588   0.02815   0.02027  -0.0662   0.2852   1.0000
  10.750   1.5829   0.02866   0.02075  -0.0659   0.2827   1.0000
  11.000   1.6123   0.02948   0.02147  -0.0665   0.2800   1.0000
  11.250   1.6190   0.03031   0.02252  -0.0639   0.2777   1.0000
  11.500   1.6260   0.03116   0.02354  -0.0614   0.2749   1.0000
  11.750   1.6363   0.03191   0.02438  -0.0593   0.2721   1.0000
  12.000   1.6504   0.03256   0.02508  -0.0577   0.2697   1.0000
  12.250   1.6716   0.03309   0.02559  -0.0570   0.2674   1.0000
  12.500   1.7052   0.03372   0.02612  -0.0582   0.2647   1.0000
  12.750   1.7035   0.03487   0.02744  -0.0548   0.2626   1.0000
  13.000   1.6933   0.03624   0.02901  -0.0506   0.2604   1.0000
  13.250   1.6874   0.03768   0.03061  -0.0476   0.2580   1.0000
  13.500   1.6890   0.03895   0.03198  -0.0455   0.2555   1.0000
  13.750   1.7019   0.03976   0.03282  -0.0444   0.2532   1.0000
  14.000   1.7305   0.04001   0.03300  -0.0446   0.2508   1.0000
  14.250   1.7532   0.04093   0.03391  -0.0445   0.2483   1.0000
  14.500   1.7226   0.04388   0.03713  -0.0409   0.2463   1.0000
  14.750   1.6912   0.04765   0.04115  -0.0386   0.2439   1.0000
  15.000   1.6674   0.05145   0.04514  -0.0374   0.2412   1.0000
  15.250   1.6657   0.05370   0.04747  -0.0369   0.2387   1.0000
  15.500   1.6995   0.05300   0.04670  -0.0366   0.2365   1.0000
  15.750   1.7562   0.05111   0.04464  -0.0369   0.2338   1.0000
  16.000   1.6423   0.06335   0.05740  -0.0367   0.2313   1.0000
  17.000   1.6011   0.07899   0.07339  -0.0396   0.2199   1.0000
  17.250   0.7813   0.19737   0.19343  -0.0991   0.1721   1.0000
  17.500   0.7959   0.19848   0.19456  -0.0991   0.1691   1.0000
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