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EPPLER 1214 AIRFOIL (e1214-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 1214 AIRFOIL (e1214-il)
Reynolds number: 500,000
Max Cl/Cd: 78.3 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e1214-il-500000.txt
Download as CSV file: xf-e1214-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.250  -0.9022   0.08941   0.08458  -0.0332   1.0000   0.0249
 -17.000  -0.9015   0.08622   0.08135  -0.0344   1.0000   0.0254
 -16.750  -0.8991   0.08337   0.07847  -0.0353   1.0000   0.0256
 -16.500  -0.8989   0.08015   0.07519  -0.0365   1.0000   0.0260
 -16.250  -0.8984   0.07709   0.07210  -0.0376   1.0000   0.0261
 -16.000  -0.8981   0.07393   0.06887  -0.0387   1.0000   0.0265
 -15.750  -0.9028   0.07035   0.06528  -0.0399   1.0000   0.0268
 -15.500  -0.9073   0.06679   0.06170  -0.0412   1.0000   0.0271
 -15.250  -0.9150   0.06287   0.05774  -0.0427   1.0000   0.0274
 -15.000  -0.9240   0.05896   0.05378  -0.0440   1.0000   0.0278
 -14.750  -0.9312   0.05528   0.05005  -0.0453   1.0000   0.0279
 -14.500  -0.9411   0.05132   0.04602  -0.0467   1.0000   0.0283
 -14.250  -0.9506   0.04737   0.04200  -0.0480   1.0000   0.0287
 -14.000  -0.9596   0.04348   0.03802  -0.0493   1.0000   0.0291
 -13.750  -0.9672   0.03971   0.03417  -0.0507   1.0000   0.0293
 -13.500  -0.9736   0.03604   0.03041  -0.0520   1.0000   0.0297
 -13.250  -0.9770   0.03278   0.02705  -0.0532   1.0000   0.0302
 -13.000  -0.9876   0.02904   0.02322  -0.0544   1.0000   0.0308
 -12.750  -0.9915   0.02651   0.02062  -0.0543   1.0000   0.0313
 -12.500  -0.9946   0.02455   0.01860  -0.0532   1.0000   0.0322
 -12.250  -0.9947   0.02317   0.01716  -0.0512   1.0000   0.0331
 -12.000  -0.9956   0.02204   0.01597  -0.0484   1.0000   0.0343
 -11.750  -1.0000   0.02102   0.01494  -0.0444   1.0000   0.0356
 -11.500  -1.0026   0.02031   0.01420  -0.0399   1.0000   0.0373
 -11.250  -1.0022   0.01958   0.01346  -0.0358   1.0000   0.0395
 -11.000  -0.9983   0.01881   0.01270  -0.0322   1.0000   0.0434
 -10.750  -0.9879   0.01787   0.01182  -0.0300   0.9983   0.0511
 -10.500  -0.9555   0.01648   0.01058  -0.0324   0.9803   0.0719
 -10.250  -0.9151   0.01521   0.00947  -0.0360   0.9419   0.0979
 -10.000  -0.8609   0.01410   0.00841  -0.0421   0.8897   0.1266
  -9.500  -0.8225   0.01329   0.00744  -0.0391   0.8038   0.1613
  -9.250  -0.8027   0.01299   0.00710  -0.0376   0.7771   0.1774
  -9.000  -0.7808   0.01277   0.00682  -0.0364   0.7542   0.1914
  -8.750  -0.7576   0.01260   0.00658  -0.0354   0.7338   0.2037
  -8.500  -0.7340   0.01242   0.00637  -0.0344   0.7152   0.2139
  -8.250  -0.7090   0.01231   0.00618  -0.0337   0.6977   0.2224
  -8.000  -0.6840   0.01219   0.00601  -0.0329   0.6820   0.2305
  -7.750  -0.6582   0.01213   0.00584  -0.0323   0.6672   0.2376
  -7.500  -0.6327   0.01204   0.00572  -0.0316   0.6528   0.2454
  -7.250  -0.6058   0.01202   0.00560  -0.0312   0.6393   0.2526
  -7.000  -0.5805   0.01194   0.00549  -0.0305   0.6263   0.2597
  -6.750  -0.5534   0.01193   0.00541  -0.0301   0.6139   0.2659
  -6.500  -0.5270   0.01188   0.00529  -0.0296   0.6022   0.2723
  -6.250  -0.5005   0.01188   0.00526  -0.0291   0.5902   0.2790
  -6.000  -0.4732   0.01190   0.00519  -0.0287   0.5792   0.2842
  -5.750  -0.4464   0.01182   0.00503  -0.0282   0.5685   0.2888
  -5.500  -0.4195   0.01172   0.00492  -0.0278   0.5587   0.2931
  -5.250  -0.3923   0.01169   0.00483  -0.0274   0.5482   0.2971
  -5.000  -0.3648   0.01167   0.00473  -0.0270   0.5385   0.3011
  -4.750  -0.3371   0.01169   0.00464  -0.0267   0.5285   0.3043
  -4.500  -0.3103   0.01151   0.00447  -0.0263   0.5198   0.3089
  -4.250  -0.2829   0.01145   0.00439  -0.0260   0.5108   0.3131
  -4.000  -0.2556   0.01146   0.00432  -0.0256   0.5021   0.3171
  -3.750  -0.2275   0.01144   0.00425  -0.0254   0.4934   0.3210
  -3.500  -0.2002   0.01141   0.00413  -0.0250   0.4846   0.3245
  -3.250  -0.1728   0.01128   0.00402  -0.0247   0.4768   0.3288
  -3.000  -0.1453   0.01124   0.00396  -0.0244   0.4689   0.3328
  -2.750  -0.1178   0.01126   0.00391  -0.0241   0.4614   0.3368
  -2.500  -0.0896   0.01124   0.00385  -0.0239   0.4538   0.3404
  -2.250  -0.0621   0.01122   0.00376  -0.0236   0.4461   0.3440
  -2.000  -0.0349   0.01113   0.00370  -0.0232   0.4393   0.3485
  -1.750  -0.0072   0.01110   0.00366  -0.0230   0.4323   0.3530
  -1.500   0.0202   0.01114   0.00364  -0.0227   0.4255   0.3575
  -1.250   0.0484   0.01117   0.00362  -0.0225   0.4194   0.3614
  -1.000   0.0758   0.01109   0.00356  -0.0222   0.4126   0.3662
  -0.750   0.1027   0.01110   0.00354  -0.0218   0.4062   0.3712
  -0.500   0.1305   0.01111   0.00355  -0.0216   0.4008   0.3762
  -0.250   0.1585   0.01114   0.00354  -0.0214   0.3950   0.3811
   0.000   0.1854   0.01113   0.00352  -0.0210   0.3892   0.3870
   0.250   0.2124   0.01116   0.00355  -0.0206   0.3837   0.3930
   0.500   0.2404   0.01116   0.00357  -0.0204   0.3786   0.3990
   0.750   0.2679   0.01119   0.00358  -0.0202   0.3735   0.4049
   1.000   0.2942   0.01123   0.00362  -0.0198   0.3684   0.4123
   1.250   0.3217   0.01127   0.00367  -0.0195   0.3639   0.4202
   1.500   0.3492   0.01126   0.00371  -0.0192   0.3593   0.4284
   1.750   0.3760   0.01129   0.00375  -0.0189   0.3546   0.4376
   2.000   0.4025   0.01139   0.00382  -0.0185   0.3499   0.4470
   2.250   0.4292   0.01141   0.00391  -0.0181   0.3462   0.4586
   2.500   0.4564   0.01142   0.00398  -0.0178   0.3424   0.4715
   2.750   0.4831   0.01145   0.00405  -0.0175   0.3382   0.4867
   3.000   0.5089   0.01150   0.00414  -0.0170   0.3341   0.5041
   3.250   0.5343   0.01160   0.00428  -0.0164   0.3298   0.5238
   3.500   0.5608   0.01158   0.00437  -0.0160   0.3267   0.5473
   3.750   0.5867   0.01158   0.00448  -0.0155   0.3233   0.5750
   4.000   0.6116   0.01158   0.00460  -0.0149   0.3198   0.6084
   4.250   0.6357   0.01161   0.00474  -0.0140   0.3163   0.6464
   4.500   0.6589   0.01170   0.00494  -0.0131   0.3124   0.6895
   4.750   0.6826   0.01161   0.00508  -0.0121   0.3097   0.7403
   5.000   0.7052   0.01152   0.00523  -0.0108   0.3065   0.8013
   5.250   0.7321   0.01147   0.00544  -0.0102   0.3033   0.8807
   5.500   0.7946   0.01178   0.00579  -0.0172   0.2987   0.9411
   5.750   0.8405   0.01214   0.00611  -0.0208   0.2947   0.9663
   6.000   0.8797   0.01232   0.00632  -0.0231   0.2918   0.9820
   6.250   0.9219   0.01253   0.00653  -0.0260   0.2881   0.9918
   6.750   0.9988   0.01302   0.00693  -0.0306   0.2810   1.0000
   7.000   1.0181   0.01330   0.00719  -0.0291   0.2782   1.0000
   7.250   1.0387   0.01345   0.00738  -0.0277   0.2761   1.0000
   7.500   1.0592   0.01363   0.00758  -0.0263   0.2736   1.0000
   7.750   1.0794   0.01382   0.00778  -0.0250   0.2711   1.0000
   8.000   1.0993   0.01404   0.00798  -0.0235   0.2685   1.0000
   8.250   1.1184   0.01431   0.00822  -0.0220   0.2657   1.0000
   8.500   1.1371   0.01472   0.00858  -0.0205   0.2625   1.0000
   8.750   1.1571   0.01490   0.00882  -0.0191   0.2608   1.0000
   9.000   1.1767   0.01512   0.00908  -0.0176   0.2587   1.0000
   9.250   1.1959   0.01535   0.00934  -0.0162   0.2564   1.0000
   9.500   1.2145   0.01560   0.00960  -0.0146   0.2540   1.0000
   9.750   1.2322   0.01588   0.00987  -0.0129   0.2517   1.0000
  10.000   1.2489   0.01624   0.01020  -0.0112   0.2491   1.0000
  10.250   1.2663   0.01669   0.01064  -0.0096   0.2465   1.0000
  10.500   1.2812   0.01693   0.01095  -0.0075   0.2449   1.0000
  10.750   1.2943   0.01721   0.01128  -0.0051   0.2429   1.0000
  11.000   1.3077   0.01752   0.01163  -0.0028   0.2408   1.0000
  11.250   1.3213   0.01785   0.01199  -0.0007   0.2386   1.0000
  11.500   1.3349   0.01824   0.01240   0.0012   0.2364   1.0000
  11.750   1.3484   0.01874   0.01287   0.0030   0.2340   1.0000
  12.000   1.3631   0.01933   0.01346   0.0046   0.2313   1.0000
  12.250   1.3757   0.01980   0.01402   0.0063   0.2297   1.0000
  12.500   1.3883   0.02035   0.01464   0.0078   0.2276   1.0000
  12.750   1.4006   0.02096   0.01530   0.0092   0.2252   1.0000
  13.000   1.4128   0.02164   0.01602   0.0105   0.2230   1.0000
  13.250   1.4244   0.02242   0.01681   0.0116   0.2208   1.0000
  13.500   1.4362   0.02329   0.01765   0.0127   0.2182   1.0000
  13.750   1.4480   0.02419   0.01861   0.0137   0.2161   1.0000
  14.000   1.4577   0.02521   0.01973   0.0145   0.2142   1.0000
  14.250   1.4675   0.02630   0.02090   0.0152   0.2121   1.0000
  14.500   1.4770   0.02746   0.02212   0.0158   0.2098   1.0000
  14.750   1.4858   0.02872   0.02341   0.0164   0.2076   1.0000
  15.000   1.4941   0.03004   0.02473   0.0169   0.2052   1.0000
  15.250   1.5034   0.03130   0.02599   0.0175   0.2025   1.0000
  15.500   1.5080   0.03305   0.02788   0.0177   0.2006   1.0000
  15.750   1.5124   0.03488   0.02979   0.0177   0.1982   1.0000
  16.000   1.5166   0.03676   0.03174   0.0178   0.1957   1.0000
  16.250   1.5206   0.03865   0.03367   0.0178   0.1934   1.0000
  16.500   1.5243   0.04052   0.03553   0.0179   0.1905   1.0000
  16.750   1.5265   0.04267   0.03775   0.0179   0.1881   1.0000
  17.000   1.5240   0.04545   0.04065   0.0174   0.1855   1.0000
  17.250   1.5230   0.04812   0.04342   0.0169   0.1829   1.0000
  17.500   1.5206   0.05097   0.04630   0.0163   0.1798   1.0000
  17.750   1.5218   0.05332   0.04862   0.0160   0.1769   1.0000
  18.000   1.5150   0.05681   0.05223   0.0151   0.1740   1.0000
  18.250   1.5077   0.06048   0.05602   0.0140   0.1710   1.0000
  18.500   1.5006   0.06409   0.05968   0.0130   0.1677   1.0000
  18.750   1.4969   0.06720   0.06277   0.0123   0.1643   1.0000
  19.000   1.4888   0.07103   0.06671   0.0111   0.1617   1.0000
  19.250   1.4761   0.07557   0.07136   0.0096   0.1583   1.0000
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