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EPPLER 1214 AIRFOIL (e1214-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 1214 AIRFOIL (e1214-il)
Reynolds number: 100,000
Max Cl/Cd: 36.34 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e1214-il-100000-n5.txt
Download as CSV file: xf-e1214-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 1214 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.750  -0.7145   0.09799   0.09093  -0.0300   1.0000   0.0526
 -15.500  -0.7118   0.09504   0.08802  -0.0310   1.0000   0.0543
 -15.250  -0.7122   0.09156   0.08455  -0.0324   1.0000   0.0568
 -15.000  -0.7129   0.08812   0.08109  -0.0337   1.0000   0.0595
 -14.750  -0.7136   0.08478   0.07778  -0.0350   1.0000   0.0619
 -14.500  -0.7166   0.08110   0.07409  -0.0364   1.0000   0.0654
 -14.250  -0.7211   0.07736   0.07038  -0.0378   1.0000   0.0687
 -14.000  -0.7268   0.07351   0.06653  -0.0393   1.0000   0.0727
 -13.750  -0.7349   0.06956   0.06260  -0.0408   1.0000   0.0764
 -13.500  -0.7442   0.06553   0.05858  -0.0423   1.0000   0.0807
 -13.250  -0.7552   0.06136   0.05440  -0.0438   1.0000   0.0853
 -13.000  -0.7687   0.05696   0.05001  -0.0455   1.0000   0.0902
 -12.750  -0.7812   0.05271   0.04572  -0.0470   1.0000   0.0950
 -12.500  -0.7981   0.04805   0.04105  -0.0488   1.0000   0.0999
 -12.250  -0.8128   0.04372   0.03666  -0.0504   1.0000   0.1052
 -12.000  -0.8313   0.03931   0.03222  -0.0519   1.0000   0.1102
 -11.750  -0.8465   0.03579   0.02864  -0.0524   1.0000   0.1164
 -11.500  -0.8606   0.03307   0.02590  -0.0515   1.0000   0.1228
 -11.250  -0.8719   0.03113   0.02396  -0.0493   1.0000   0.1299
 -11.000  -0.8810   0.02971   0.02255  -0.0459   1.0000   0.1386
 -10.750  -0.8881   0.02860   0.02147  -0.0420   1.0000   0.1476
 -10.500  -0.8890   0.02764   0.02057  -0.0387   1.0000   0.1586
 -10.250  -0.8862   0.02686   0.01985  -0.0356   1.0000   0.1698
 -10.000  -0.8812   0.02623   0.01925  -0.0326   1.0000   0.1816
  -9.750  -0.8676   0.02567   0.01873  -0.0312   0.9928   0.1954
  -9.500  -0.8320   0.02517   0.01820  -0.0336   0.9585   0.2138
  -9.250  -0.7927   0.02488   0.01780  -0.0364   0.9218   0.2310
  -9.000  -0.7508   0.02473   0.01753  -0.0392   0.8894   0.2445
  -8.500  -0.6872   0.02441   0.01681  -0.0407   0.8284   0.2635
  -8.250  -0.6637   0.02421   0.01637  -0.0399   0.8026   0.2711
  -8.000  -0.6388   0.02421   0.01627  -0.0390   0.7800   0.2774
  -7.750  -0.6179   0.02392   0.01570  -0.0378   0.7598   0.2845
  -7.500  -0.5937   0.02377   0.01545  -0.0369   0.7410   0.2897
  -7.250  -0.5692   0.02367   0.01524  -0.0360   0.7238   0.2950
  -7.000  -0.5467   0.02341   0.01474  -0.0350   0.7083   0.3012
  -6.750  -0.5228   0.02314   0.01431  -0.0342   0.6932   0.3064
  -6.500  -0.4970   0.02301   0.01413  -0.0336   0.6782   0.3109
  -6.250  -0.4724   0.02281   0.01379  -0.0328   0.6650   0.3162
  -6.000  -0.4493   0.02253   0.01324  -0.0319   0.6519   0.3221
  -5.750  -0.4236   0.02232   0.01299  -0.0313   0.6390   0.3263
  -5.250  -0.3729   0.02197   0.01244  -0.0301   0.6152   0.3359
  -5.000  -0.3486   0.02174   0.01196  -0.0293   0.6049   0.3412
  -4.750  -0.3226   0.02151   0.01170  -0.0288   0.5932   0.3452
  -4.500  -0.2965   0.02136   0.01147  -0.0282   0.5835   0.3493
  -4.250  -0.2708   0.02119   0.01122  -0.0277   0.5725   0.3541
  -4.000  -0.2453   0.02101   0.01085  -0.0271   0.5635   0.3591
  -3.750  -0.2195   0.02081   0.01057  -0.0266   0.5531   0.3635
  -3.500  -0.1932   0.02068   0.01038  -0.0261   0.5446   0.3676
  -3.250  -0.1670   0.02055   0.01023  -0.0257   0.5347   0.3724
  -3.000  -0.1410   0.02042   0.00998  -0.0252   0.5263   0.3776
  -2.750  -0.1148   0.02031   0.00972  -0.0247   0.5180   0.3826
  -2.500  -0.0884   0.02018   0.00962  -0.0243   0.5093   0.3869
  -2.250  -0.0621   0.02011   0.00946  -0.0238   0.5021   0.3921
  -2.000  -0.0359   0.02003   0.00936  -0.0234   0.4933   0.3978
  -1.750  -0.0096   0.01997   0.00917  -0.0229   0.4860   0.4034
  -1.500   0.0169   0.01989   0.00910  -0.0225   0.4792   0.4082
  -1.250   0.0431   0.01985   0.00907  -0.0221   0.4713   0.4141
  -1.000   0.0694   0.01983   0.00893  -0.0216   0.4648   0.4210
  -0.750   0.0957   0.01980   0.00891  -0.0212   0.4580   0.4270
  -0.500   0.1218   0.01978   0.00892  -0.0207   0.4509   0.4332
  -0.250   0.1482   0.01979   0.00885  -0.0203   0.4452   0.4406
   0.000   0.1744   0.01980   0.00887  -0.0199   0.4391   0.4479
   0.250   0.2001   0.01982   0.00894  -0.0194   0.4324   0.4558
   0.500   0.2264   0.01986   0.00890  -0.0190   0.4267   0.4649
   0.750   0.2524   0.01988   0.00895  -0.0185   0.4216   0.4730
   1.000   0.2781   0.01996   0.00909  -0.0180   0.4154   0.4830
   1.250   0.3038   0.02000   0.00917  -0.0175   0.4099   0.4933
   1.500   0.3299   0.02006   0.00918  -0.0170   0.4053   0.5055
   1.750   0.3552   0.02015   0.00938  -0.0165   0.3998   0.5179
   2.000   0.3806   0.02026   0.00955  -0.0160   0.3943   0.5322
   2.250   0.4062   0.02033   0.00967  -0.0155   0.3897   0.5482
   2.500   0.4323   0.02041   0.00976  -0.0150   0.3857   0.5667
   2.750   0.4569   0.02056   0.01006  -0.0144   0.3805   0.5876
   3.000   0.4819   0.02068   0.01031  -0.0139   0.3754   0.6120
   3.250   0.5068   0.02077   0.01049  -0.0132   0.3711   0.6401
   3.500   0.5321   0.02085   0.01064  -0.0125   0.3676   0.6730
   3.750   0.5557   0.02102   0.01101  -0.0116   0.3633   0.7123
   4.000   0.5804   0.02118   0.01141  -0.0108   0.3586   0.7593
   4.250   0.6114   0.02133   0.01173  -0.0111   0.3541   0.8146
   4.500   0.6564   0.02156   0.01201  -0.0141   0.3499   0.8736
   4.750   0.7064   0.02201   0.01254  -0.0184   0.3451   0.9221
   5.000   0.7487   0.02248   0.01307  -0.0215   0.3402   0.9612
   5.250   0.7901   0.02287   0.01343  -0.0244   0.3357   0.9891
   5.500   0.8234   0.02318   0.01364  -0.0258   0.3322   1.0000
   5.750   0.8422   0.02357   0.01396  -0.0244   0.3292   1.0000
   6.000   0.8576   0.02408   0.01455  -0.0226   0.3255   1.0000
   6.250   0.8747   0.02457   0.01506  -0.0210   0.3221   1.0000
   6.500   0.8930   0.02500   0.01548  -0.0196   0.3189   1.0000
   6.750   0.9130   0.02537   0.01579  -0.0184   0.3160   1.0000
   7.000   0.9347   0.02572   0.01604  -0.0174   0.3135   1.0000
   7.250   0.9493   0.02635   0.01675  -0.0157   0.3102   1.0000
   7.500   0.9630   0.02701   0.01751  -0.0138   0.3067   1.0000
   7.750   0.9789   0.02760   0.01814  -0.0122   0.3035   1.0000
   8.000   0.9968   0.02813   0.01867  -0.0109   0.3008   1.0000
   8.250   1.0170   0.02858   0.01908  -0.0098   0.2984   1.0000
   8.500   1.0399   0.02898   0.01940  -0.0091   0.2961   1.0000
   8.750   1.0485   0.02988   0.02044  -0.0069   0.2931   1.0000
   9.000   1.0550   0.03085   0.02155  -0.0044   0.2898   1.0000
   9.250   1.0647   0.03167   0.02245  -0.0024   0.2868   1.0000
   9.500   1.0781   0.03238   0.02318  -0.0008   0.2842   1.0000
   9.750   1.0948   0.03298   0.02378   0.0005   0.2820   1.0000
  10.000   1.1165   0.03342   0.02417   0.0012   0.2800   1.0000
  10.250   1.1225   0.03439   0.02520   0.0036   0.2777   1.0000
  10.500   1.1016   0.03635   0.02737   0.0081   0.2747   1.0000
  10.750   1.0845   0.03860   0.02978   0.0111   0.2717   1.0000
  11.000   1.0759   0.04073   0.03201   0.0128   0.2688   1.0000
  11.250   1.0827   0.04209   0.03341   0.0137   0.2664   1.0000
  11.500   1.1029   0.04263   0.03393   0.0142   0.2645   1.0000
  11.750   1.1355   0.04244   0.03366   0.0145   0.2629   1.0000
  12.250   0.9132   0.06938   0.06123   0.0098   0.2468   1.0000
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