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=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 1214 AIRFOIL (e1214-il)
Reynolds number: 200,000
Max Cl/Cd: 48.36 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e1214-il-200000.txt
Download as CSV file: xf-e1214-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.250  -0.9016   0.11418   0.10874  -0.0317   1.0000   0.0381
 -19.000  -0.9157   0.10810   0.10249  -0.0352   1.0000   0.0381
 -18.750  -0.9338   0.10155   0.09571  -0.0392   1.0000   0.0382
 -18.500  -0.9420   0.09672   0.09072  -0.0418   1.0000   0.0382
 -18.250  -0.9262   0.09582   0.08990  -0.0409   1.0000   0.0388
 -18.000  -0.9215   0.09314   0.08719  -0.0418   1.0000   0.0392
 -17.750  -0.9183   0.09025   0.08424  -0.0427   1.0000   0.0396
 -17.500  -0.9157   0.08729   0.08122  -0.0438   1.0000   0.0400
 -17.250  -0.9128   0.08438   0.07824  -0.0448   1.0000   0.0404
 -17.000  -0.9122   0.08116   0.07493  -0.0460   1.0000   0.0412
 -16.750  -0.9077   0.07859   0.07228  -0.0467   1.0000   0.0416
 -16.500  -0.9094   0.07510   0.06864  -0.0481   1.0000   0.0424
 -16.250  -0.9028   0.07290   0.06640  -0.0484   1.0000   0.0430
 -16.000  -0.8885   0.07200   0.06563  -0.0477   1.0000   0.0441
 -15.750  -0.8803   0.07014   0.06378  -0.0478   1.0000   0.0451
 -15.500  -0.8750   0.06786   0.06146  -0.0482   1.0000   0.0460
 -15.250  -0.8709   0.06542   0.05895  -0.0487   1.0000   0.0471
 -15.000  -0.8639   0.06360   0.05715  -0.0485   1.0000   0.0483
 -14.750  -0.8567   0.06184   0.05545  -0.0484   1.0000   0.0493
 -14.500  -0.8539   0.05953   0.05316  -0.0487   1.0000   0.0507
 -14.250  -0.8525   0.05701   0.05059  -0.0492   1.0000   0.0522
 -14.000  -0.8524   0.05454   0.04815  -0.0494   1.0000   0.0538
 -13.750  -0.8544   0.05177   0.04541  -0.0499   1.0000   0.0553
 -13.500  -0.8581   0.04874   0.04236  -0.0505   1.0000   0.0573
 -13.250  -0.8639   0.04551   0.03911  -0.0513   1.0000   0.0594
 -13.000  -0.8738   0.04186   0.03546  -0.0523   1.0000   0.0618
 -12.750  -0.8801   0.03857   0.03211  -0.0531   1.0000   0.0645
 -12.500  -0.8935   0.03473   0.02828  -0.0541   1.0000   0.0673
 -12.250  -0.9026   0.03162   0.02511  -0.0544   1.0000   0.0714
 -12.000  -0.9176   0.02864   0.02214  -0.0537   1.0000   0.0757
 -11.750  -0.9316   0.02640   0.01990  -0.0513   1.0000   0.0822
 -11.500  -0.9451   0.02471   0.01825  -0.0475   1.0000   0.0906
 -11.250  -0.9587   0.02343   0.01703  -0.0424   1.0000   0.1007
 -11.000  -0.9667   0.02224   0.01592  -0.0377   1.0000   0.1158
 -10.750  -0.9694   0.02115   0.01496  -0.0336   1.0000   0.1326
 -10.500  -0.9660   0.02032   0.01422  -0.0302   1.0000   0.1504
 -10.250  -0.9605   0.01969   0.01370  -0.0270   1.0000   0.1664
 -10.000  -0.9551   0.01928   0.01336  -0.0237   1.0000   0.1806
  -9.750  -0.9167   0.01886   0.01297  -0.0265   0.9894   0.2006
  -9.500  -0.8708   0.01853   0.01257  -0.0303   0.9686   0.2182
  -9.250  -0.8254   0.01830   0.01231  -0.0337   0.9435   0.2323
  -9.000  -0.7758   0.01814   0.01209  -0.0378   0.9174   0.2444
  -8.750  -0.7326   0.01803   0.01182  -0.0406   0.8844   0.2554
  -8.500  -0.7025   0.01825   0.01186  -0.0406   0.8511   0.2657
  -8.250  -0.6783   0.01847   0.01199  -0.0395   0.8224   0.2742
  -8.000  -0.6559   0.01877   0.01212  -0.0381   0.7983   0.2829
  -7.750  -0.6329   0.01883   0.01205  -0.0368   0.7772   0.2899
  -7.500  -0.6081   0.01902   0.01219  -0.0358   0.7575   0.2964
  -7.250  -0.5862   0.01908   0.01200  -0.0345   0.7394   0.3032
  -7.000  -0.5606   0.01890   0.01180  -0.0338   0.7228   0.3084
  -6.750  -0.5347   0.01892   0.01175  -0.0330   0.7074   0.3136
  -6.500  -0.5105   0.01886   0.01150  -0.0321   0.6930   0.3192
  -6.250  -0.4865   0.01865   0.01112  -0.0312   0.6784   0.3243
  -6.000  -0.4595   0.01848   0.01095  -0.0308   0.6652   0.3287
  -5.750  -0.4333   0.01841   0.01079  -0.0301   0.6521   0.3335
  -5.500  -0.4081   0.01830   0.01054  -0.0294   0.6395   0.3388
  -5.250  -0.3831   0.01814   0.01015  -0.0287   0.6284   0.3435
  -5.000  -0.3559   0.01788   0.00995  -0.0284   0.6159   0.3478
  -4.750  -0.3292   0.01781   0.00978  -0.0279   0.6054   0.3524
  -4.500  -0.3031   0.01768   0.00957  -0.0273   0.5938   0.3575
  -4.250  -0.2774   0.01766   0.00931  -0.0267   0.5844   0.3621
  -4.000  -0.2502   0.01730   0.00901  -0.0264   0.5734   0.3665
  -3.750  -0.2231   0.01722   0.00883  -0.0260   0.5642   0.3708
  -3.500  -0.1964   0.01708   0.00867  -0.0256   0.5536   0.3757
  -3.250  -0.1699   0.01705   0.00844  -0.0251   0.5450   0.3807
  -3.000  -0.1429   0.01681   0.00820  -0.0248   0.5357   0.3851
  -2.750  -0.1156   0.01667   0.00803  -0.0245   0.5270   0.3893
  -2.500  -0.0885   0.01662   0.00793  -0.0241   0.5185   0.3944
  -2.250  -0.0617   0.01655   0.00778  -0.0237   0.5096   0.4000
  -2.000  -0.0345   0.01649   0.00758  -0.0234   0.5023   0.4049
  -1.750  -0.0074   0.01634   0.00751  -0.0231   0.4940   0.4098
  -1.500   0.0199   0.01628   0.00740  -0.0228   0.4866   0.4152
  -1.250   0.0469   0.01632   0.00734  -0.0224   0.4794   0.4213
  -1.000   0.0739   0.01619   0.00723  -0.0221   0.4716   0.4272
  -0.750   0.1011   0.01616   0.00716  -0.0218   0.4651   0.4332
  -0.500   0.1282   0.01620   0.00718  -0.0215   0.4585   0.4399
  -0.250   0.1552   0.01615   0.00711  -0.0212   0.4516   0.4464
   0.000   0.1823   0.01611   0.00707  -0.0208   0.4456   0.4534
   0.250   0.2092   0.01618   0.00712  -0.0205   0.4394   0.4617
   0.500   0.2359   0.01614   0.00713  -0.0201   0.4330   0.4698
   0.750   0.2628   0.01614   0.00713  -0.0198   0.4276   0.4785
   1.000   0.2901   0.01629   0.00719  -0.0196   0.4223   0.4882
   1.250   0.3159   0.01623   0.00729  -0.0190   0.4164   0.4983
   1.500   0.3425   0.01625   0.00731  -0.0187   0.4108   0.5105
   1.750   0.3692   0.01630   0.00737  -0.0183   0.4062   0.5235
   2.000   0.3952   0.01639   0.00755  -0.0179   0.4014   0.5378
   2.250   0.4207   0.01642   0.00769  -0.0173   0.3962   0.5547
   2.500   0.4464   0.01643   0.00777  -0.0168   0.3914   0.5749
   2.750   0.4722   0.01647   0.00787  -0.0162   0.3870   0.5988
   3.000   0.4965   0.01656   0.00812  -0.0154   0.3827   0.6276
   3.250   0.5199   0.01656   0.00835  -0.0144   0.3781   0.6634
   3.500   0.5434   0.01654   0.00853  -0.0133   0.3739   0.7083
   3.750   0.5676   0.01651   0.00870  -0.0122   0.3700   0.7663
   4.000   0.5977   0.01670   0.00905  -0.0122   0.3659   0.8364
   4.250   0.6478   0.01691   0.00951  -0.0162   0.3603   0.9027
   4.500   0.7026   0.01722   0.00983  -0.0212   0.3550   0.9414
   4.750   0.7504   0.01758   0.01007  -0.0250   0.3508   0.9676
   5.000   0.7995   0.01808   0.01054  -0.0293   0.3464   0.9854
   5.250   0.8514   0.01836   0.01089  -0.0343   0.3411   0.9984
   5.500   0.8748   0.01859   0.01107  -0.0337   0.3373   1.0000
   5.750   0.8945   0.01883   0.01123  -0.0324   0.3342   1.0000
   6.000   0.9162   0.01924   0.01152  -0.0314   0.3313   1.0000
   6.250   0.9341   0.01967   0.01201  -0.0298   0.3283   1.0000
   6.500   0.9517   0.02004   0.01246  -0.0282   0.3250   1.0000
   6.750   0.9709   0.02038   0.01282  -0.0268   0.3216   1.0000
   7.000   0.9920   0.02068   0.01309  -0.0256   0.3184   1.0000
   7.250   1.0150   0.02099   0.01332  -0.0248   0.3156   1.0000
   7.500   1.0388   0.02160   0.01383  -0.0242   0.3126   1.0000
   7.750   1.0542   0.02204   0.01442  -0.0223   0.3098   1.0000
   8.000   1.0712   0.02252   0.01499  -0.0206   0.3068   1.0000
   8.250   1.0902   0.02296   0.01547  -0.0193   0.3038   1.0000
   8.500   1.1113   0.02333   0.01584  -0.0182   0.3011   1.0000
   8.750   1.1351   0.02369   0.01612  -0.0176   0.2985   1.0000
   9.000   1.1612   0.02438   0.01671  -0.0175   0.2956   1.0000
   9.250   1.1732   0.02494   0.01744  -0.0152   0.2932   1.0000
   9.500   1.1864   0.02557   0.01821  -0.0132   0.2904   1.0000
   9.750   1.2021   0.02617   0.01888  -0.0115   0.2877   1.0000
  10.000   1.2211   0.02664   0.01938  -0.0104   0.2850   1.0000
  10.250   1.2440   0.02700   0.01971  -0.0097   0.2826   1.0000
  10.500   1.2709   0.02748   0.02009  -0.0097   0.2802   1.0000
  10.750   1.2864   0.02839   0.02108  -0.0083   0.2778   1.0000
  11.000   1.2921   0.02924   0.02212  -0.0055   0.2754   1.0000
  11.250   1.2984   0.03007   0.02308  -0.0030   0.2726   1.0000
  11.500   1.3086   0.03076   0.02384  -0.0009   0.2700   1.0000
  11.750   1.3252   0.03125   0.02435   0.0004   0.2676   1.0000
  12.000   1.3498   0.03162   0.02468   0.0007   0.2654   1.0000
  12.250   1.3844   0.03222   0.02516  -0.0004   0.2628   1.0000
  12.500   1.3714   0.03339   0.02654   0.0044   0.2608   1.0000
  12.750   1.3546   0.03478   0.02812   0.0092   0.2586   1.0000
  13.000   1.3412   0.03640   0.02990   0.0127   0.2561   1.0000
  13.250   1.3373   0.03783   0.03142   0.0148   0.2536   1.0000
  13.500   1.3497   0.03857   0.03217   0.0157   0.2513   1.0000
  13.750   1.3869   0.03822   0.03173   0.0153   0.2490   1.0000
  14.000   1.4146   0.03881   0.03227   0.0152   0.2465   1.0000
  14.250   1.3537   0.04352   0.03732   0.0189   0.2442   1.0000
  15.000   1.1658   0.06805   0.06245   0.0155   0.2325   1.0000
  15.250   1.2970   0.05621   0.05040   0.0197   0.2332   1.0000
  15.500   0.7030   0.14960   0.14442  -0.0200   0.1819   1.0000
  15.750   0.7208   0.15034   0.14516  -0.0200   0.1794   1.0000
<< Back to EPPLER 1214 AIRFOIL (e1214-il)

Polar data table (+)

Polar graphs


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