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=9


Details Polar file
Airfoil: EPPLER 1214 AIRFOIL (e1214-il)
Reynolds number: 1,000,000
Max Cl/Cd: 105.14 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e1214-il-1000000.txt
Download as CSV file: xf-e1214-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.750  -0.9670   0.08960   0.08554  -0.0308   1.0000   0.0178
 -17.500  -0.9711   0.08573   0.08163  -0.0324   1.0000   0.0180
 -17.250  -0.9795   0.08129   0.07713  -0.0342   1.0000   0.0181
 -17.000  -0.9852   0.07731   0.07310  -0.0359   1.0000   0.0184
 -16.750  -0.9945   0.07285   0.06858  -0.0377   1.0000   0.0183
 -16.500  -1.0022   0.06869   0.06436  -0.0394   1.0000   0.0186
 -16.250  -1.0118   0.06440   0.06000  -0.0411   1.0000   0.0185
 -16.000  -1.0224   0.06014   0.05567  -0.0428   1.0000   0.0188
 -15.750  -1.0367   0.05555   0.05100  -0.0445   1.0000   0.0188
 -15.500  -1.0479   0.05133   0.04670  -0.0461   1.0000   0.0190
 -15.250  -1.0620   0.04676   0.04203  -0.0478   1.0000   0.0190
 -15.000  -1.0727   0.04257   0.03776  -0.0494   1.0000   0.0192
 -14.750  -1.0798   0.03873   0.03383  -0.0509   1.0000   0.0193
 -14.500  -1.0858   0.03500   0.03001  -0.0525   1.0000   0.0195
 -14.250  -1.0881   0.03172   0.02663  -0.0538   1.0000   0.0197
 -14.000  -1.0883   0.02885   0.02367  -0.0548   1.0000   0.0199
 -13.750  -1.0871   0.02643   0.02117  -0.0553   1.0000   0.0200
 -13.500  -1.0864   0.02435   0.01901  -0.0551   1.0000   0.0202
 -13.250  -1.0900   0.02242   0.01701  -0.0537   1.0000   0.0206
 -13.000  -1.0902   0.02109   0.01563  -0.0515   1.0000   0.0210
 -12.750  -1.0871   0.02016   0.01466  -0.0489   1.0000   0.0213
 -12.500  -1.0844   0.01940   0.01386  -0.0456   1.0000   0.0217
 -12.250  -1.0822   0.01881   0.01324  -0.0418   1.0000   0.0221
 -12.000  -1.0809   0.01832   0.01272  -0.0375   1.0000   0.0225
 -11.750  -1.0717   0.01782   0.01218  -0.0345   1.0000   0.0230
 -11.500  -1.0393   0.01700   0.01136  -0.0362   0.9932   0.0243
 -11.250  -1.0058   0.01630   0.01065  -0.0379   0.9697   0.0257
 -11.000  -0.9299   0.01527   0.00951  -0.0482   0.8935   0.0300
 -10.500  -0.9045   0.01446   0.00839  -0.0430   0.7903   0.0420
 -10.250  -0.8897   0.01394   0.00784  -0.0409   0.7626   0.0526
 -10.000  -0.8735   0.01340   0.00729  -0.0390   0.7395   0.0653
  -9.750  -0.8557   0.01287   0.00679  -0.0373   0.7195   0.0796
  -9.500  -0.8366   0.01238   0.00633  -0.0359   0.7016   0.0953
  -9.250  -0.8165   0.01191   0.00589  -0.0345   0.6850   0.1111
  -9.000  -0.7948   0.01154   0.00552  -0.0334   0.6692   0.1259
  -8.750  -0.7730   0.01111   0.00515  -0.0323   0.6545   0.1424
  -8.500  -0.7500   0.01076   0.00484  -0.0314   0.6414   0.1597
  -8.250  -0.7261   0.01049   0.00458  -0.0306   0.6275   0.1755
  -8.000  -0.7009   0.01025   0.00437  -0.0299   0.6148   0.1894
  -7.750  -0.6755   0.01005   0.00418  -0.0293   0.6030   0.2018
  -7.500  -0.6494   0.00989   0.00401  -0.0288   0.5910   0.2115
  -7.250  -0.6223   0.00981   0.00388  -0.0284   0.5798   0.2189
  -7.000  -0.5958   0.00968   0.00374  -0.0279   0.5682   0.2268
  -6.750  -0.5682   0.00961   0.00364  -0.0276   0.5584   0.2340
  -6.500  -0.5412   0.00951   0.00352  -0.0272   0.5480   0.2410
  -6.250  -0.5136   0.00944   0.00344  -0.0269   0.5385   0.2480
  -6.000  -0.4855   0.00942   0.00335  -0.0267   0.5282   0.2527
  -5.750  -0.4583   0.00933   0.00326  -0.0263   0.5187   0.2603
  -5.500  -0.4302   0.00930   0.00320  -0.0261   0.5095   0.2657
  -5.250  -0.4017   0.00931   0.00314  -0.0259   0.5007   0.2690
  -5.000  -0.3744   0.00920   0.00304  -0.0255   0.4925   0.2753
  -4.750  -0.3467   0.00918   0.00298  -0.0252   0.4830   0.2797
  -4.500  -0.3181   0.00916   0.00292  -0.0251   0.4754   0.2832
  -4.250  -0.2897   0.00917   0.00286  -0.0249   0.4665   0.2857
  -4.000  -0.2620   0.00910   0.00277  -0.0246   0.4592   0.2904
  -3.750  -0.2341   0.00904   0.00271  -0.0244   0.4518   0.2946
  -3.500  -0.2061   0.00905   0.00267  -0.0241   0.4432   0.2986
  -3.250  -0.1773   0.00904   0.00264  -0.0240   0.4369   0.3020
  -3.000  -0.1487   0.00907   0.00260  -0.0238   0.4291   0.3042
  -2.750  -0.1213   0.00901   0.00253  -0.0235   0.4219   0.3093
  -2.500  -0.0931   0.00897   0.00249  -0.0233   0.4159   0.3134
  -2.250  -0.0649   0.00897   0.00247  -0.0231   0.4090   0.3172
  -2.000  -0.0366   0.00900   0.00245  -0.0230   0.4023   0.3204
  -1.750  -0.0078   0.00901   0.00243  -0.0229   0.3962   0.3227
  -1.500   0.0198   0.00899   0.00239  -0.0226   0.3897   0.3275
  -1.250   0.0477   0.00898   0.00238  -0.0224   0.3838   0.3320
  -1.000   0.0762   0.00897   0.00237  -0.0222   0.3786   0.3363
  -0.750   0.1045   0.00901   0.00237  -0.0221   0.3725   0.3400
  -0.500   0.1326   0.00908   0.00238  -0.0219   0.3661   0.3427
  -0.250   0.1607   0.00902   0.00236  -0.0217   0.3622   0.3486
   0.000   0.1888   0.00903   0.00237  -0.0215   0.3573   0.3535
   0.250   0.2167   0.00908   0.00239  -0.0213   0.3517   0.3581
   0.500   0.2450   0.00914   0.00242  -0.0212   0.3469   0.3619
   0.750   0.2730   0.00911   0.00243  -0.0210   0.3428   0.3687
   1.000   0.3009   0.00913   0.00245  -0.0208   0.3383   0.3746
   1.250   0.3286   0.00920   0.00250  -0.0206   0.3334   0.3799
   1.500   0.3564   0.00925   0.00254  -0.0204   0.3293   0.3858
   1.750   0.3845   0.00924   0.00258  -0.0202   0.3262   0.3936
   2.000   0.4125   0.00928   0.00262  -0.0200   0.3222   0.4009
   2.250   0.4398   0.00932   0.00267  -0.0198   0.3178   0.4098
   2.500   0.4666   0.00941   0.00276  -0.0194   0.3128   0.4191
   2.750   0.4948   0.00942   0.00281  -0.0193   0.3106   0.4289
   3.000   0.5225   0.00943   0.00287  -0.0191   0.3077   0.4405
   3.250   0.5498   0.00946   0.00294  -0.0189   0.3043   0.4540
   3.500   0.5768   0.00952   0.00302  -0.0186   0.3005   0.4688
   3.750   0.6027   0.00962   0.00314  -0.0181   0.2958   0.4858
   4.000   0.6303   0.00961   0.00321  -0.0179   0.2937   0.5048
   4.250   0.6574   0.00962   0.00330  -0.0176   0.2911   0.5263
   4.500   0.6840   0.00964   0.00339  -0.0173   0.2882   0.5509
   4.750   0.7099   0.00966   0.00350  -0.0168   0.2850   0.5804
   5.000   0.7350   0.00973   0.00364  -0.0162   0.2814   0.6139
   5.250   0.7598   0.00976   0.00379  -0.0156   0.2783   0.6504
   5.500   0.7854   0.00972   0.00389  -0.0150   0.2763   0.6921
   5.750   0.8100   0.00968   0.00401  -0.0142   0.2736   0.7405
   6.000   0.8326   0.00962   0.00415  -0.0130   0.2708   0.8005
   6.250   0.8540   0.00955   0.00432  -0.0115   0.2679   0.8805
   6.500   0.9101   0.00982   0.00469  -0.0173   0.2628   0.9534
   6.750   0.9549   0.00998   0.00488  -0.0207   0.2609   0.9732
   7.000   0.9918   0.01014   0.00504  -0.0225   0.2585   0.9838
   7.250   1.0289   0.01034   0.00522  -0.0244   0.2555   0.9911
   7.500   1.0704   0.01055   0.00541  -0.0273   0.2519   0.9953
   7.750   1.1100   0.01085   0.00566  -0.0299   0.2478   0.9987
   8.000   1.1424   0.01101   0.00584  -0.0309   0.2457   1.0000
   8.250   1.1640   0.01115   0.00599  -0.0297   0.2440   1.0000
   8.500   1.1853   0.01130   0.00616  -0.0285   0.2420   1.0000
   8.750   1.2060   0.01147   0.00634  -0.0271   0.2397   1.0000
   9.000   1.2258   0.01168   0.00653  -0.0257   0.2371   1.0000
   9.250   1.2441   0.01195   0.00678  -0.0240   0.2341   1.0000
   9.500   1.2618   0.01223   0.00706  -0.0222   0.2314   1.0000
   9.750   1.2830   0.01238   0.00724  -0.0210   0.2300   1.0000
  10.000   1.3034   0.01255   0.00744  -0.0197   0.2282   1.0000
  10.250   1.3230   0.01275   0.00765  -0.0182   0.2261   1.0000
  10.500   1.3414   0.01298   0.00789  -0.0166   0.2237   1.0000
  10.750   1.3580   0.01327   0.00817  -0.0147   0.2211   1.0000
  11.000   1.3695   0.01364   0.00853  -0.0120   0.2181   1.0000
  11.250   1.3822   0.01389   0.00881  -0.0094   0.2162   1.0000
  11.500   1.3983   0.01410   0.00905  -0.0074   0.2147   1.0000
  11.750   1.4143   0.01435   0.00933  -0.0056   0.2128   1.0000
  12.000   1.4293   0.01466   0.00967  -0.0037   0.2106   1.0000
  12.250   1.4433   0.01504   0.01006  -0.0017   0.2084   1.0000
  12.500   1.4553   0.01553   0.01056   0.0003   0.2059   1.0000
  12.750   1.4638   0.01622   0.01125   0.0026   0.2029   1.0000
  13.000   1.4813   0.01660   0.01169   0.0037   0.2016   1.0000
  13.250   1.4976   0.01707   0.01220   0.0048   0.2000   1.0000
  13.500   1.5128   0.01763   0.01280   0.0058   0.1980   1.0000
  13.750   1.5263   0.01832   0.01353   0.0069   0.1959   1.0000
  14.000   1.5377   0.01921   0.01443   0.0080   0.1935   1.0000
  14.250   1.5457   0.02038   0.01562   0.0091   0.1907   1.0000
  14.500   1.5568   0.02144   0.01672   0.0098   0.1885   1.0000
  14.750   1.5725   0.02223   0.01758   0.0102   0.1865   1.0000
  15.000   1.5855   0.02326   0.01864   0.0106   0.1840   1.0000
  15.250   1.5944   0.02462   0.02004   0.0110   0.1810   1.0000
  15.500   1.5995   0.02636   0.02180   0.0114   0.1783   1.0000
  15.750   1.6046   0.02814   0.02362   0.0117   0.1754   1.0000
  16.000   1.6158   0.02944   0.02498   0.0119   0.1733   1.0000
  16.250   1.6230   0.03110   0.02670   0.0120   0.1709   1.0000
  16.500   1.6246   0.03328   0.02891   0.0121   0.1676   1.0000
  16.750   1.6218   0.03589   0.03156   0.0121   0.1651   1.0000
  17.000   1.6207   0.03837   0.03410   0.0121   0.1629   1.0000
  17.250   1.6250   0.04039   0.03619   0.0120   0.1606   1.0000
  17.500   1.6239   0.04297   0.03883   0.0118   0.1577   1.0000
  17.750   1.6165   0.04626   0.04216   0.0114   0.1547   1.0000
  18.000   1.6027   0.05027   0.04620   0.0108   0.1512   1.0000
  18.250   1.6022   0.05296   0.04896   0.0104   0.1483   1.0000
  18.500   1.5949   0.05640   0.05245   0.0098   0.1450   1.0000
  18.750   1.5789   0.06086   0.05696   0.0089   0.1417   1.0000
  19.000   1.5670   0.06494   0.06110   0.0079   0.1386   1.0000
  19.250   1.5577   0.06879   0.06501   0.0070   0.1355   1.0000
<< Back to EPPLER 1214 AIRFOIL (e1214-il)

Polar data table (+)

Polar graphs


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