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EPPLER E1212 AIRFOIL (e1212-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER E1212 AIRFOIL (e1212-il)
Reynolds number: 50,000
Max Cl/Cd: 23.18 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e1212-il-50000-n5.txt
Download as CSV file: xf-e1212-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E1212 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3844   0.10498   0.09704  -0.0305   1.0000   0.1449
 -11.000  -0.3710   0.10333   0.09541  -0.0302   1.0000   0.1489
 -10.750  -0.3801   0.09876   0.09087  -0.0324   1.0000   0.1538
 -10.500  -0.3821   0.09512   0.08727  -0.0337   1.0000   0.1577
 -10.250  -0.3698   0.09349   0.08566  -0.0334   1.0000   0.1617
 -10.000  -0.3826   0.08875   0.08097  -0.0356   1.0000   0.1667
  -9.750  -0.3916   0.08452   0.07680  -0.0373   1.0000   0.1709
  -9.500  -0.3776   0.08336   0.07568  -0.0364   1.0000   0.1746
  -9.250  -0.3893   0.07920   0.07160  -0.0380   1.0000   0.1793
  -9.000  -0.4343   0.07153   0.06406  -0.0419   1.0000   0.1844
  -8.750  -0.4162   0.07149   0.06409  -0.0398   1.0000   0.1875
  -8.500  -0.4341   0.06807   0.06080  -0.0398   1.0000   0.1913
  -8.250  -0.5322   0.05798   0.05083  -0.0421   1.0000   0.1960
  -8.000  -0.5194   0.05433   0.04706  -0.0465   0.9782   0.2017
  -7.750  -0.4854   0.05259   0.04521  -0.0501   0.9535   0.2075
  -7.500  -0.4780   0.04652   0.03865  -0.0568   0.9269   0.2163
  -7.250  -0.4336   0.04610   0.03823  -0.0591   0.9089   0.2212
  -7.000  -0.4098   0.04299   0.03471  -0.0628   0.8882   0.2289
  -6.750  -0.3813   0.04099   0.03245  -0.0651   0.8687   0.2348
  -6.500  -0.3479   0.04023   0.03161  -0.0661   0.8497   0.2399
  -6.250  -0.3258   0.03838   0.02939  -0.0671   0.8307   0.2465
  -6.000  -0.3032   0.03691   0.02761  -0.0675   0.8127   0.2522
  -5.750  -0.2758   0.03637   0.02698  -0.0672   0.7957   0.2567
  -5.500  -0.2526   0.03545   0.02584  -0.0668   0.7791   0.2622
  -5.250  -0.2343   0.03406   0.02398  -0.0666   0.7626   0.2690
  -5.000  -0.2090   0.03364   0.02358  -0.0658   0.7471   0.2728
  -4.750  -0.1841   0.03312   0.02291  -0.0651   0.7332   0.2777
  -4.500  -0.1614   0.03241   0.02198  -0.0645   0.7187   0.2838
  -4.250  -0.1388   0.03164   0.02093  -0.0641   0.7049   0.2896
  -4.000  -0.1128   0.03124   0.02047  -0.0633   0.6930   0.2940
  -3.750  -0.0893   0.03085   0.02000  -0.0626   0.6790   0.2996
  -3.500  -0.0648   0.03031   0.01919  -0.0622   0.6673   0.3061
  -3.250  -0.0398   0.02987   0.01863  -0.0616   0.6553   0.3113
  -3.000  -0.0146   0.02960   0.01835  -0.0610   0.6433   0.3166
  -2.750   0.0118   0.02925   0.01781  -0.0605   0.6328   0.3233
  -2.500   0.0368   0.02893   0.01733  -0.0602   0.6210   0.3299
  -2.250   0.0636   0.02866   0.01702  -0.0596   0.6112   0.3354
  -2.000   0.0885   0.02851   0.01683  -0.0591   0.5998   0.3422
  -1.750   0.1159   0.02824   0.01633  -0.0588   0.5907   0.3502
  -1.500   0.1406   0.02814   0.01631  -0.0582   0.5797   0.3563
  -1.250   0.1678   0.02796   0.01601  -0.0578   0.5707   0.3642
  -1.000   0.1934   0.02792   0.01591  -0.0574   0.5606   0.3726
  -0.750   0.2196   0.02781   0.01579  -0.0568   0.5517   0.3809
  -0.500   0.2454   0.02781   0.01569  -0.0564   0.5425   0.3911
  -0.250   0.2711   0.02777   0.01570  -0.0558   0.5333   0.4002
   0.000   0.2983   0.02775   0.01555  -0.0554   0.5258   0.4126
   0.250   0.3221   0.02785   0.01578  -0.0548   0.5161   0.4241
   0.500   0.3496   0.02776   0.01562  -0.0543   0.5091   0.4388
   0.750   0.3728   0.02797   0.01592  -0.0537   0.5000   0.4547
   1.000   0.3981   0.02798   0.01600  -0.0530   0.4924   0.4733
   1.250   0.4233   0.02802   0.01610  -0.0523   0.4855   0.4958
   1.500   0.4451   0.02824   0.01650  -0.0514   0.4768   0.5217
   1.750   0.4701   0.02816   0.01654  -0.0504   0.4705   0.5555
   2.000   0.4906   0.02837   0.01700  -0.0490   0.4631   0.5979
   2.250   0.5105   0.02847   0.01739  -0.0473   0.4558   0.6544
   2.500   0.5342   0.02827   0.01743  -0.0455   0.4503   0.7375
   2.750   0.5669   0.02859   0.01812  -0.0460   0.4416   0.8690
   3.000   0.6134   0.02890   0.01832  -0.0496   0.4339   1.0000
   3.250   0.6390   0.02921   0.01838  -0.0491   0.4288   1.0000
   3.500   0.6540   0.03018   0.01937  -0.0479   0.4208   1.0000
   3.750   0.6772   0.03064   0.01969  -0.0472   0.4150   1.0000
   4.000   0.7051   0.03087   0.01969  -0.0469   0.4106   1.0000
   4.250   0.7161   0.03216   0.02109  -0.0454   0.4028   1.0000
   4.500   0.7377   0.03275   0.02160  -0.0445   0.3970   1.0000
   4.750   0.7653   0.03301   0.02167  -0.0442   0.3927   1.0000
   5.000   0.7754   0.03441   0.02317  -0.0426   0.3859   1.0000
   5.250   0.7921   0.03536   0.02412  -0.0415   0.3800   1.0000
   5.500   0.8179   0.03573   0.02437  -0.0410   0.3756   1.0000
   5.750   0.8347   0.03673   0.02535  -0.0400   0.3706   1.0000
   6.000   0.8380   0.03858   0.02734  -0.0381   0.3641   1.0000
   6.250   0.8575   0.03936   0.02807  -0.0372   0.3594   1.0000
   6.500   0.8877   0.03949   0.02807  -0.0370   0.3559   1.0000
   6.750   0.8749   0.04239   0.03117  -0.0343   0.3494   1.0000
   7.000   0.8726   0.04458   0.03344  -0.0324   0.3438   1.0000
   7.250   0.8947   0.04519   0.03399  -0.0317   0.3401   1.0000
   7.500   0.9302   0.04503   0.03372  -0.0317   0.3374   1.0000
   7.750   0.8008   0.05715   0.04624  -0.0276   0.3249   1.0000
   8.000   0.8244   0.05753   0.04657  -0.0268   0.3220   1.0000
   8.250   0.8606   0.05671   0.04568  -0.0258   0.3201   1.0000
   8.750   0.7746   0.07341   0.06257  -0.0299   0.3027   1.0000
   9.250   0.7242   0.08745   0.07671  -0.0344   0.2877   1.0000
   9.500   0.7450   0.08834   0.07758  -0.0338   0.2858   1.0000
   9.750   0.7004   0.09817   0.08750  -0.0377   0.2775   1.0000
  10.000   0.7066   0.10104   0.09037  -0.0382   0.2735   1.0000
  10.250   0.7223   0.10271   0.09205  -0.0380   0.2709   1.0000
  10.500   0.7408   0.10409   0.09342  -0.0377   0.2691   1.0000
  10.750   0.7087   0.11240   0.10181  -0.0413   0.2629   1.0000
  11.000   0.7099   0.11608   0.10551  -0.0424   0.2588   1.0000
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