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EPPLER 1214 AIRFOIL (e1214-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 1214 AIRFOIL (e1214-il)
Reynolds number: 100,000
Max Cl/Cd: 25.27 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e1214-il-100000.txt
Download as CSV file: xf-e1214-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.500  -0.7651   0.10246   0.09629  -0.0377   1.0000   0.0715
 -16.250  -0.8063   0.09203   0.08562  -0.0440   1.0000   0.0709
 -16.000  -0.8434   0.08317   0.07648  -0.0494   1.0000   0.0708
 -15.750  -0.8699   0.07638   0.06943  -0.0533   1.0000   0.0711
 -15.500  -0.8909   0.07070   0.06349  -0.0563   1.0000   0.0715
 -15.250  -0.8649   0.07047   0.06347  -0.0546   1.0000   0.0741
 -15.000  -0.8677   0.06705   0.05997  -0.0557   1.0000   0.0759
 -14.750  -0.8742   0.06321   0.05598  -0.0571   1.0000   0.0773
 -14.500  -0.8858   0.05897   0.05149  -0.0588   1.0000   0.0788
 -14.250  -0.8597   0.05881   0.05161  -0.0569   1.0000   0.0825
 -14.000  -0.8608   0.05580   0.04849  -0.0574   1.0000   0.0854
 -13.750  -0.8519   0.05397   0.04673  -0.0569   1.0000   0.0891
 -13.500  -0.8504   0.05147   0.04425  -0.0570   1.0000   0.0936
 -13.250  -0.8478   0.04919   0.04206  -0.0568   1.0000   0.0989
 -13.000  -0.8565   0.04576   0.03854  -0.0576   1.0000   0.1047
 -12.750  -0.8562   0.04352   0.03650  -0.0573   1.0000   0.1117
 -12.500  -0.8645   0.04057   0.03365  -0.0573   1.0000   0.1197
 -12.250  -0.8756   0.03766   0.03078  -0.0570   1.0000   0.1283
 -12.000  -0.8898   0.03497   0.02813  -0.0559   1.0000   0.1383
 -11.750  -0.9041   0.03288   0.02609  -0.0536   1.0000   0.1490
 -11.500  -0.9160   0.03147   0.02482  -0.0500   1.0000   0.1600
 -11.250  -0.9265   0.03050   0.02396  -0.0456   1.0000   0.1716
 -11.000  -0.9303   0.02980   0.02333  -0.0418   1.0000   0.1853
 -10.750  -0.9280   0.02944   0.02303  -0.0384   1.0000   0.1986
 -10.500  -0.9218   0.02934   0.02297  -0.0352   1.0000   0.2112
 -10.250  -0.9154   0.02918   0.02279  -0.0321   1.0000   0.2228
 -10.000  -0.9090   0.02914   0.02270  -0.0290   1.0000   0.2340
  -9.750  -0.8903   0.02993   0.02371  -0.0269   1.0000   0.2434
  -9.500  -0.9013   0.02940   0.02299  -0.0219   1.0000   0.2520
  -9.250  -0.8956   0.03056   0.02446  -0.0183   1.0000   0.2577
  -9.000  -0.8460   0.03187   0.02584  -0.0223   0.9874   0.2730
  -8.750  -0.7864   0.03292   0.02690  -0.0275   0.9703   0.2886
  -8.500  -0.7246   0.03391   0.02795  -0.0324   0.9541   0.3013
  -8.250  -0.6607   0.03472   0.02889  -0.0371   0.9386   0.3116
  -8.000  -0.6231   0.03335   0.02718  -0.0404   0.9179   0.3243
  -7.750  -0.5587   0.03441   0.02841  -0.0441   0.8978   0.3317
  -7.500  -0.5501   0.03254   0.02601  -0.0433   0.8710   0.3424
  -7.250  -0.5092   0.03289   0.02648  -0.0437   0.8471   0.3476
  -7.000  -0.4814   0.03286   0.02635  -0.0429   0.8245   0.3542
  -6.750  -0.4775   0.03131   0.02434  -0.0407   0.8049   0.3627
  -6.500  -0.4470   0.03136   0.02443  -0.0400   0.7858   0.3674
  -6.250  -0.4225   0.03122   0.02421  -0.0389   0.7682   0.3732
  -6.000  -0.4107   0.03019   0.02279  -0.0371   0.7536   0.3809
  -5.750  -0.3884   0.02965   0.02218  -0.0360   0.7374   0.3860
  -5.500  -0.3629   0.02952   0.02203  -0.0351   0.7219   0.3911
  -5.250  -0.3427   0.02899   0.02129  -0.0339   0.7089   0.3975
  -5.000  -0.3261   0.02817   0.02017  -0.0325   0.6957   0.4040
  -4.750  -0.3002   0.02790   0.01992  -0.0318   0.6822   0.4086
  -4.500  -0.2753   0.02763   0.01950  -0.0309   0.6711   0.4142
  -4.250  -0.2551   0.02712   0.01884  -0.0300   0.6580   0.4205
  -4.000  -0.2325   0.02657   0.01804  -0.0291   0.6482   0.4258
  -3.750  -0.2076   0.02631   0.01783  -0.0284   0.6353   0.4306
  -3.500  -0.1825   0.02606   0.01743  -0.0277   0.6258   0.4366
  -3.250  -0.1606   0.02569   0.01690  -0.0269   0.6144   0.4428
  -3.000  -0.1350   0.02530   0.01634  -0.0263   0.6060   0.4478
  -2.750  -0.1105   0.02514   0.01624  -0.0257   0.5943   0.4532
  -2.500  -0.0846   0.02491   0.01582  -0.0251   0.5863   0.4598
  -2.250  -0.0621   0.02474   0.01553  -0.0245   0.5759   0.4662
  -2.000  -0.0352   0.02446   0.01524  -0.0240   0.5677   0.4713
  -1.750  -0.0102   0.02442   0.01519  -0.0234   0.5588   0.4779
  -1.500   0.0144   0.02429   0.01492  -0.0228   0.5500   0.4856
  -1.250   0.0418   0.02411   0.01464  -0.0224   0.5433   0.4920
  -1.000   0.0655   0.02414   0.01478  -0.0218   0.5339   0.4986
  -0.750   0.0914   0.02404   0.01452  -0.0214   0.5269   0.5071
  -0.500   0.1172   0.02403   0.01452  -0.0209   0.5198   0.5144
  -0.250   0.1415   0.02408   0.01463  -0.0203   0.5114   0.5230
   0.000   0.1684   0.02398   0.01440  -0.0199   0.5053   0.5324
   0.250   0.1931   0.02413   0.01464  -0.0193   0.4986   0.5410
   0.500   0.2169   0.02426   0.01476  -0.0187   0.4912   0.5522
   0.750   0.2441   0.02418   0.01471  -0.0183   0.4855   0.5627
   1.000   0.2685   0.02439   0.01491  -0.0177   0.4794   0.5754
   1.250   0.2914   0.02459   0.01528  -0.0169   0.4722   0.5876
   1.500   0.3176   0.02461   0.01532  -0.0164   0.4669   0.6022
   1.750   0.3453   0.02470   0.01533  -0.0161   0.4625   0.6200
   2.000   0.3635   0.02516   0.01606  -0.0148   0.4552   0.6385
   2.250   0.3876   0.02527   0.01628  -0.0140   0.4494   0.6604
   2.500   0.4148   0.02524   0.01633  -0.0134   0.4451   0.6862
   2.750   0.4363   0.02567   0.01698  -0.0123   0.4401   0.7171
   3.000   0.4554   0.02615   0.01778  -0.0110   0.4339   0.7559
   3.250   0.4823   0.02622   0.01804  -0.0101   0.4288   0.8099
   3.500   0.5299   0.02630   0.01817  -0.0126   0.4243   0.8743
   3.750   0.5826   0.02768   0.01983  -0.0180   0.4164   0.9263
   4.000   0.6470   0.02836   0.02046  -0.0248   0.4100   0.9648
   4.250   0.7207   0.02852   0.02036  -0.0329   0.4050   0.9894
   4.500   0.7402   0.02988   0.02191  -0.0341   0.3989   1.0000
   4.750   0.7422   0.03082   0.02287  -0.0310   0.3945   1.0000
   5.000   0.7563   0.03140   0.02337  -0.0292   0.3910   1.0000
   5.250   0.7767   0.03178   0.02364  -0.0280   0.3880   1.0000
   5.500   0.8021   0.03220   0.02387  -0.0274   0.3852   1.0000
   5.750   0.7772   0.03519   0.02724  -0.0221   0.3794   1.0000
   6.000   0.7763   0.03691   0.02903  -0.0191   0.3747   1.0000
   6.250   0.7982   0.03731   0.02937  -0.0181   0.3714   1.0000
   6.500   0.8271   0.03745   0.02938  -0.0178   0.3689   1.0000
   6.750   0.8574   0.03784   0.02962  -0.0177   0.3666   1.0000
   7.000   0.3970   0.08221   0.07494  -0.0126   0.3626   1.0000
   7.250   0.5444   0.06850   0.06102  -0.0064   0.3488   1.0000
   7.750   0.7157   0.05527   0.04758  -0.0012   0.3484   1.0000
   8.750   0.3676   0.10811   0.10085  -0.0182   0.3760   1.0000
   9.000   0.3844   0.11018   0.10289  -0.0182   0.3717   1.0000
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