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EPPLER 1211 AIRFOIL (e1211-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 1211 AIRFOIL (e1211-il)
Reynolds number: 50,000
Max Cl/Cd: 24.18 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e1211-il-50000-n5.txt
Download as CSV file: xf-e1211-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 1211 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.2717   0.11139   0.10378  -0.0392   1.0000   0.1250
 -10.750  -0.2678   0.10891   0.10136  -0.0393   1.0000   0.1291
 -10.500  -0.2854   0.10397   0.09648  -0.0418   1.0000   0.1329
 -10.250  -0.2710   0.10287   0.09545  -0.0405   1.0000   0.1361
 -10.000  -0.2692   0.10046   0.09311  -0.0405   1.0000   0.1399
  -9.750  -0.2840   0.09631   0.08905  -0.0419   1.0000   0.1432
  -9.500  -0.2880   0.09366   0.08651  -0.0419   1.0000   0.1463
  -9.250  -0.2826   0.09238   0.08534  -0.0405   1.0000   0.1494
  -9.000  -0.2939   0.08999   0.08309  -0.0398   1.0000   0.1521
  -8.750  -0.3163   0.08523   0.07845  -0.0430   0.9913   0.1559
  -8.500  -0.2897   0.08218   0.07538  -0.0474   0.9676   0.1602
  -8.000  -0.2878   0.06969   0.06276  -0.0636   0.9177   0.1715
  -7.750  -0.2426   0.06912   0.06212  -0.0652   0.9014   0.1760
  -7.500  -0.2830   0.05565   0.04824  -0.0816   0.8771   0.1855
  -7.250  -0.2349   0.05661   0.04921  -0.0812   0.8612   0.1888
  -7.000  -0.2176   0.05366   0.04608  -0.0842   0.8428   0.1942
  -6.750  -0.2278   0.04711   0.03900  -0.0898   0.8244   0.2021
  -6.500  -0.1963   0.04686   0.03871  -0.0895   0.8085   0.2056
  -6.250  -0.1743   0.04510   0.03672  -0.0906   0.7940   0.2111
  -6.000  -0.1692   0.04122   0.03227  -0.0928   0.7780   0.2184
  -5.750  -0.1434   0.04090   0.03195  -0.0919   0.7632   0.2218
  -5.500  -0.1176   0.04006   0.03094  -0.0918   0.7506   0.2265
  -5.250  -0.1003   0.03844   0.02902  -0.0920   0.7360   0.2323
  -5.000  -0.0792   0.03694   0.02719  -0.0924   0.7234   0.2379
  -4.750  -0.0544   0.03643   0.02661  -0.0917   0.7109   0.2419
  -4.500  -0.0318   0.03573   0.02577  -0.0912   0.6983   0.2469
  -4.250  -0.0067   0.03451   0.02414  -0.0917   0.6874   0.2535
  -4.000   0.0161   0.03384   0.02336  -0.0913   0.6749   0.2579
  -3.750   0.0434   0.03338   0.02280  -0.0909   0.6650   0.2626
  -3.500   0.0663   0.03290   0.02218  -0.0905   0.6528   0.2682
  -3.250   0.0941   0.03208   0.02097  -0.0908   0.6435   0.2746
  -3.000   0.1172   0.03177   0.02068  -0.0901   0.6318   0.2790
  -2.750   0.1447   0.03140   0.02021  -0.0898   0.6228   0.2844
  -2.500   0.1687   0.03109   0.01978  -0.0893   0.6119   0.2903
  -2.250   0.1964   0.03062   0.01902  -0.0893   0.6028   0.2968
  -2.000   0.2207   0.03047   0.01891  -0.0886   0.5931   0.3017
  -1.750   0.2466   0.03026   0.01862  -0.0882   0.5839   0.3080
  -1.500   0.2737   0.03001   0.01816  -0.0880   0.5755   0.3149
  -1.250   0.2980   0.02991   0.01805  -0.0874   0.5657   0.3209
  -1.000   0.3265   0.02970   0.01774  -0.0871   0.5587   0.3281
  -0.750   0.3492   0.02978   0.01777  -0.0865   0.5489   0.3357
  -0.500   0.3758   0.02965   0.01757  -0.0860   0.5411   0.3429
  -0.250   0.4011   0.02966   0.01754  -0.0854   0.5335   0.3511
   0.000   0.4255   0.02979   0.01759  -0.0849   0.5248   0.3610
   0.250   0.4534   0.02968   0.01745  -0.0845   0.5183   0.3701
   0.500   0.4764   0.02993   0.01768  -0.0839   0.5100   0.3810
   0.750   0.5010   0.03001   0.01782  -0.0832   0.5025   0.3922
   1.000   0.5302   0.02994   0.01764  -0.0830   0.4969   0.4073
   1.250   0.5496   0.03037   0.01822  -0.0820   0.4886   0.4215
   1.500   0.5742   0.03049   0.01840  -0.0813   0.4818   0.4392
   1.750   0.6028   0.03039   0.01830  -0.0810   0.4767   0.4631
   2.000   0.6198   0.03096   0.01909  -0.0797   0.4686   0.4877
   2.250   0.6423   0.03112   0.01943  -0.0788   0.4623   0.5218
   2.500   0.6682   0.03100   0.01946  -0.0779   0.4576   0.5725
   2.750   0.6819   0.03146   0.02030  -0.0757   0.4508   0.6357
   3.000   0.6950   0.03163   0.02088  -0.0727   0.4446   0.7372
   3.250   0.7303   0.03144   0.02081  -0.0732   0.4392   1.0000
   3.500   0.7529   0.03214   0.02135  -0.0727   0.4338   1.0000
   3.750   0.7670   0.03327   0.02246  -0.0715   0.4269   1.0000
   4.000   0.7915   0.03380   0.02283  -0.0711   0.4217   1.0000
   4.250   0.8224   0.03401   0.02281  -0.0712   0.4178   1.0000
   4.500   0.8274   0.03567   0.02457  -0.0692   0.4110   1.0000
   4.750   0.8427   0.03673   0.02561  -0.0680   0.4053   1.0000
   5.000   0.8692   0.03715   0.02588  -0.0677   0.4011   1.0000
   5.250   0.8977   0.03751   0.02608  -0.0676   0.3974   1.0000
   5.500   0.8845   0.04023   0.02901  -0.0643   0.3900   1.0000
   5.750   0.8976   0.04142   0.03019  -0.0630   0.3852   1.0000
   6.000   0.9262   0.04173   0.03037  -0.0628   0.3816   1.0000
   6.250   0.9441   0.04272   0.03130  -0.0619   0.3777   1.0000
   6.500   0.8822   0.04836   0.03725  -0.0561   0.3689   1.0000
   6.750   0.8970   0.04951   0.03835  -0.0552   0.3648   1.0000
   7.000   0.9309   0.04939   0.03813  -0.0551   0.3623   1.0000
   7.500   0.8323   0.06390   0.05292  -0.0535   0.3445   1.0000
   7.750   0.8646   0.06334   0.05229  -0.0526   0.3429   1.0000
   9.250   0.7526   0.09975   0.08901  -0.0612   0.3023   1.0000
   9.500   0.7485   0.10403   0.09332  -0.0623   0.2971   1.0000
   9.750   0.7609   0.10621   0.09549  -0.0624   0.2939   1.0000
  10.000   0.7780   0.10785   0.09711  -0.0623   0.2918   1.0000
  10.500   0.7592   0.11825   0.10760  -0.0657   0.2823   1.0000
  10.750   0.7670   0.12108   0.11044  -0.0663   0.2787   1.0000
  11.000   0.7802   0.12331   0.11269  -0.0665   0.2763   1.0000
  11.250   0.7981   0.12495   0.11431  -0.0664   0.2745   1.0000
  11.500   0.7846   0.13075   0.12018  -0.0688   0.2699   1.0000
  11.750   0.7812   0.13503   0.12451  -0.0705   0.2656   1.0000
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