Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

EPPLER 1214 AIRFOIL (e1214-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 1214 AIRFOIL (e1214-il)
Reynolds number: 1,000,000
Max Cl/Cd: 103.93 at α=9.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e1214-il-1000000-n5.txt
Download as CSV file: xf-e1214-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -18.000  -0.9924   0.08945   0.08528  -0.0311   1.0000   0.0138
 -17.750  -0.9974   0.08544   0.08122  -0.0328   1.0000   0.0139
 -17.500  -1.0059   0.08099   0.07670  -0.0346   1.0000   0.0140
 -17.250  -1.0132   0.07680   0.07244  -0.0364   1.0000   0.0140
 -17.000  -1.0184   0.07289   0.06847  -0.0379   1.0000   0.0142
 -16.750  -1.0292   0.06833   0.06384  -0.0398   1.0000   0.0142
 -16.500  -1.0370   0.06427   0.05971  -0.0415   1.0000   0.0143
 -16.250  -1.0492   0.05982   0.05517  -0.0432   1.0000   0.0143
 -16.000  -1.0593   0.05572   0.05100  -0.0448   1.0000   0.0144
 -15.750  -1.0726   0.05126   0.04644  -0.0464   1.0000   0.0144
 -15.500  -1.0817   0.04727   0.04237  -0.0479   1.0000   0.0145
 -15.250  -1.0935   0.04296   0.03797  -0.0496   1.0000   0.0145
 -15.000  -1.1047   0.03865   0.03357  -0.0513   1.0000   0.0147
 -14.750  -1.1092   0.03512   0.02995  -0.0527   1.0000   0.0148
 -14.500  -1.1132   0.03167   0.02641  -0.0542   1.0000   0.0150
 -14.250  -1.1143   0.02873   0.02340  -0.0552   1.0000   0.0152
 -14.000  -1.1132   0.02632   0.02092  -0.0556   1.0000   0.0154
 -13.750  -1.1105   0.02442   0.01895  -0.0554   1.0000   0.0155
 -13.500  -1.1071   0.02288   0.01735  -0.0544   1.0000   0.0157
 -13.250  -1.1026   0.02168   0.01611  -0.0528   1.0000   0.0159
 -13.000  -1.0980   0.02069   0.01508  -0.0507   1.0000   0.0162
 -12.750  -1.0669   0.01975   0.01410  -0.0529   0.9607   0.0166
 -12.500  -0.9951   0.01898   0.01295  -0.0625   0.8331   0.0172
 -12.250  -0.9913   0.01849   0.01227  -0.0591   0.7852   0.0175
 -12.000  -0.9851   0.01799   0.01163  -0.0559   0.7532   0.0180
 -11.750  -0.9766   0.01753   0.01107  -0.0529   0.7304   0.0184
 -11.500  -0.9667   0.01717   0.01061  -0.0500   0.7092   0.0190
 -11.250  -0.9527   0.01682   0.01018  -0.0478   0.6902   0.0195
 -11.000  -0.9359   0.01646   0.00974  -0.0460   0.6726   0.0203
 -10.750  -0.9185   0.01606   0.00929  -0.0443   0.6580   0.0214
 -10.500  -0.8998   0.01570   0.00887  -0.0428   0.6433   0.0230
 -10.000  -0.8609   0.01494   0.00803  -0.0400   0.6159   0.0282
  -9.750  -0.8407   0.01456   0.00762  -0.0387   0.6038   0.0325
  -9.500  -0.8199   0.01416   0.00721  -0.0375   0.5917   0.0384
  -9.250  -0.7990   0.01376   0.00680  -0.0363   0.5805   0.0457
  -9.000  -0.7770   0.01340   0.00644  -0.0353   0.5694   0.0529
  -8.750  -0.7553   0.01300   0.00605  -0.0342   0.5595   0.0623
  -8.500  -0.7329   0.01261   0.00569  -0.0332   0.5494   0.0732
  -8.250  -0.7104   0.01223   0.00534  -0.0322   0.5398   0.0863
  -8.000  -0.6876   0.01184   0.00499  -0.0313   0.5293   0.1005
  -7.750  -0.6642   0.01149   0.00468  -0.0305   0.5206   0.1156
  -7.500  -0.6404   0.01113   0.00437  -0.0297   0.5116   0.1309
  -7.250  -0.6160   0.01084   0.00411  -0.0289   0.5020   0.1457
  -7.000  -0.5911   0.01055   0.00387  -0.0283   0.4935   0.1621
  -6.750  -0.5663   0.01027   0.00365  -0.0276   0.4848   0.1803
  -6.500  -0.5403   0.01006   0.00348  -0.0271   0.4780   0.1948
  -6.250  -0.5137   0.00991   0.00333  -0.0267   0.4696   0.2071
  -6.000  -0.4868   0.00979   0.00322  -0.0263   0.4613   0.2171
  -5.750  -0.4597   0.00966   0.00311  -0.0259   0.4533   0.2277
  -5.500  -0.4321   0.00961   0.00302  -0.0257   0.4453   0.2348
  -5.250  -0.4045   0.00952   0.00292  -0.0253   0.4392   0.2413
  -5.000  -0.3767   0.00945   0.00285  -0.0251   0.4324   0.2478
  -4.750  -0.3486   0.00944   0.00278  -0.0249   0.4247   0.2516
  -4.500  -0.3207   0.00937   0.00270  -0.0246   0.4182   0.2562
  -4.250  -0.2928   0.00932   0.00263  -0.0244   0.4107   0.2605
  -4.000  -0.2647   0.00931   0.00258  -0.0241   0.4040   0.2645
  -3.750  -0.2362   0.00928   0.00253  -0.0240   0.3991   0.2676
  -3.500  -0.2081   0.00925   0.00247  -0.0238   0.3928   0.2718
  -3.000  -0.1519   0.00921   0.00239  -0.0233   0.3804   0.2801
  -2.750  -0.1235   0.00920   0.00235  -0.0232   0.3744   0.2831
  -2.500  -0.0952   0.00922   0.00232  -0.0230   0.3685   0.2857
  -2.250  -0.0669   0.00920   0.00229  -0.0228   0.3640   0.2893
  -2.000  -0.0387   0.00918   0.00226  -0.0226   0.3587   0.2930
  -1.750  -0.0106   0.00919   0.00225  -0.0224   0.3525   0.2964
  -1.500   0.0177   0.00921   0.00224  -0.0223   0.3475   0.2996
  -1.250   0.0463   0.00921   0.00223  -0.0221   0.3436   0.3026
  -1.000   0.0746   0.00922   0.00222  -0.0220   0.3388   0.3057
  -0.750   0.1025   0.00924   0.00222  -0.0218   0.3334   0.3101
  -0.500   0.1307   0.00925   0.00223  -0.0216   0.3289   0.3138
  -0.250   0.1591   0.00926   0.00224  -0.0215   0.3253   0.3174
   0.000   0.1875   0.00929   0.00225  -0.0213   0.3214   0.3206
   0.250   0.2157   0.00934   0.00227  -0.0212   0.3170   0.3236
   0.500   0.2435   0.00937   0.00229  -0.0210   0.3124   0.3288
   0.750   0.2718   0.00937   0.00232  -0.0208   0.3093   0.3335
   1.000   0.3000   0.00940   0.00235  -0.0207   0.3057   0.3376
   1.250   0.3281   0.00945   0.00238  -0.0205   0.3020   0.3410
   1.500   0.3559   0.00951   0.00242  -0.0203   0.2983   0.3451
   1.750   0.3837   0.00954   0.00247  -0.0201   0.2950   0.3506
   2.000   0.4118   0.00957   0.00252  -0.0200   0.2921   0.3564
   2.250   0.4398   0.00962   0.00257  -0.0198   0.2887   0.3612
   2.500   0.4675   0.00967   0.00262  -0.0196   0.2852   0.3668
   2.750   0.4950   0.00973   0.00269  -0.0194   0.2818   0.3730
   3.000   0.5225   0.00980   0.00277  -0.0192   0.2786   0.3789
   3.250   0.5504   0.00984   0.00283  -0.0190   0.2766   0.3859
   3.500   0.5779   0.00988   0.00290  -0.0188   0.2738   0.3947
   3.750   0.6054   0.00995   0.00298  -0.0186   0.2706   0.4021
   4.000   0.6323   0.01002   0.00307  -0.0183   0.2671   0.4108
   4.250   0.6592   0.01011   0.00317  -0.0180   0.2638   0.4201
   4.500   0.6863   0.01016   0.00327  -0.0177   0.2616   0.4307
   4.750   0.7135   0.01021   0.00337  -0.0175   0.2596   0.4436
   5.000   0.7403   0.01026   0.00347  -0.0172   0.2572   0.4580
   5.250   0.7670   0.01033   0.00358  -0.0169   0.2544   0.4717
   5.500   0.7932   0.01042   0.00370  -0.0165   0.2514   0.4869
   5.750   0.8189   0.01052   0.00384  -0.0161   0.2479   0.5048
   6.000   0.8450   0.01057   0.00397  -0.0157   0.2457   0.5267
   6.250   0.8710   0.01062   0.00410  -0.0153   0.2437   0.5516
   6.500   0.8966   0.01066   0.00424  -0.0148   0.2414   0.5785
   6.750   0.9217   0.01073   0.00439  -0.0143   0.2389   0.6066
   7.000   0.9463   0.01080   0.00455  -0.0137   0.2363   0.6380
   7.250   0.9699   0.01088   0.00473  -0.0129   0.2336   0.6757
   7.500   0.9929   0.01092   0.00491  -0.0119   0.2312   0.7227
   7.750   1.0151   0.01089   0.00508  -0.0108   0.2295   0.7787
   8.000   1.0357   0.01085   0.00526  -0.0093   0.2272   0.8446
   8.500   1.1333   0.01123   0.00588  -0.0181   0.2211   0.9758
   8.750   1.1678   0.01150   0.00613  -0.0196   0.2183   0.9861
   9.000   1.1969   0.01172   0.00637  -0.0200   0.2162   0.9927
   9.250   1.2297   0.01193   0.00659  -0.0212   0.2142   0.9974
   9.500   1.2638   0.01216   0.00683  -0.0227   0.2118   1.0000
   9.750   1.2832   0.01238   0.00705  -0.0212   0.2097   1.0000
  10.000   1.3018   0.01262   0.00728  -0.0196   0.2074   1.0000
  10.250   1.3194   0.01288   0.00755  -0.0179   0.2049   1.0000
  10.500   1.3366   0.01315   0.00783  -0.0161   0.2025   1.0000
  10.750   1.3552   0.01337   0.00807  -0.0145   0.2009   1.0000
  11.000   1.3715   0.01361   0.00833  -0.0125   0.1988   1.0000
  11.250   1.3841   0.01386   0.00860  -0.0099   0.1965   1.0000
  11.500   1.3963   0.01417   0.00891  -0.0074   0.1942   1.0000
  11.750   1.4082   0.01454   0.00929  -0.0049   0.1917   1.0000
  12.000   1.4203   0.01497   0.00972  -0.0027   0.1891   1.0000
  12.250   1.4363   0.01530   0.01009  -0.0011   0.1876   1.0000
  12.500   1.4514   0.01570   0.01052   0.0006   0.1856   1.0000
  12.750   1.4655   0.01617   0.01103   0.0021   0.1834   1.0000
  13.000   1.4784   0.01675   0.01163   0.0037   0.1811   1.0000
  13.250   1.4901   0.01746   0.01235   0.0052   0.1786   1.0000
  13.500   1.5002   0.01832   0.01323   0.0066   0.1761   1.0000
  13.750   1.5148   0.01901   0.01397   0.0075   0.1745   1.0000
  14.000   1.5281   0.01983   0.01484   0.0083   0.1724   1.0000
  14.250   1.5399   0.02082   0.01586   0.0091   0.1699   1.0000
  14.500   1.5493   0.02204   0.01711   0.0098   0.1671   1.0000
  14.750   1.5548   0.02364   0.01872   0.0104   0.1635   1.0000
  15.000   1.5659   0.02486   0.01999   0.0107   0.1612   1.0000
  15.250   1.5734   0.02643   0.02160   0.0111   0.1574   1.0000
  15.500   1.5773   0.02834   0.02354   0.0113   0.1543   1.0000
  15.750   1.5779   0.03059   0.02583   0.0115   0.1506   1.0000
  16.000   1.5816   0.03260   0.02789   0.0116   0.1474   1.0000
  16.250   1.5818   0.03496   0.03029   0.0116   0.1443   1.0000
  16.500   1.5720   0.03830   0.03367   0.0115   0.1399   1.0000
  16.750   1.5713   0.04082   0.03624   0.0114   0.1372   1.0000
  17.000   1.5670   0.04375   0.03923   0.0112   0.1344   1.0000
  17.250   1.5546   0.04760   0.04312   0.0107   0.1306   1.0000
  17.500   1.5439   0.05136   0.04694   0.0101   0.1275   1.0000
  17.750   1.5349   0.05501   0.05065   0.0095   0.1244   1.0000
  18.000   1.5182   0.05959   0.05528   0.0086   0.1206   1.0000
  18.250   1.4981   0.06465   0.06040   0.0075   0.1163   1.0000
  18.500   1.4828   0.06923   0.06503   0.0064   0.1127   1.0000
  18.750   1.4601   0.07477   0.07062   0.0049   0.1092   1.0000
  19.000   1.4447   0.07954   0.07546   0.0036   0.1058   1.0000
  19.250   1.4230   0.08514   0.08111   0.0020   0.1019   1.0000
<< Back to EPPLER 1214 AIRFOIL (e1214-il)

Polar data table (+)

Polar graphs


<< Back to EPPLER 1214 AIRFOIL (e1214-il)