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EPPLER E1212MOD AIRFOIL (e1212mod-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER E1212MOD AIRFOIL (e1212mod-il)
Reynolds number: 50,000
Max Cl/Cd: 20.81 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e1212mod-il-50000-n5.txt
Download as CSV file: xf-e1212mod-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E1212MOD AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3686   0.11498   0.10714  -0.0220   1.0000   0.1420
 -10.750  -0.3737   0.11050   0.10268  -0.0243   1.0000   0.1440
 -10.500  -0.3887   0.10478   0.09700  -0.0278   1.0000   0.1464
 -10.250  -0.3708   0.10328   0.09552  -0.0272   1.0000   0.1486
 -10.000  -0.3640   0.10039   0.09266  -0.0279   1.0000   0.1507
  -9.750  -0.3631   0.09687   0.08918  -0.0292   1.0000   0.1534
  -9.500  -0.3730   0.09207   0.08443  -0.0317   1.0000   0.1565
  -9.250  -0.4028   0.08466   0.07711  -0.0363   1.0000   0.1600
  -9.000  -0.3843   0.08376   0.07625  -0.0353   1.0000   0.1623
  -8.750  -0.3783   0.08136   0.07392  -0.0356   1.0000   0.1654
  -8.500  -0.3930   0.07657   0.06922  -0.0379   1.0000   0.1694
  -8.250  -0.5272   0.05977   0.05252  -0.0471   1.0000   0.1747
  -8.000  -0.5025   0.06075   0.05366  -0.0446   1.0000   0.1768
  -7.750  -0.4783   0.05942   0.05236  -0.0464   0.9722   0.1809
  -7.500  -0.5128   0.04844   0.04066  -0.0560   0.9233   0.1899
  -7.250  -0.4609   0.04895   0.04126  -0.0580   0.8995   0.1939
  -7.000  -0.4319   0.04711   0.03923  -0.0605   0.8742   0.1997
  -6.750  -0.4296   0.04284   0.03435  -0.0623   0.8506   0.2066
  -6.500  -0.3971   0.04275   0.03425  -0.0623   0.8293   0.2105
  -6.250  -0.3758   0.04176   0.03306  -0.0619   0.8091   0.2152
  -6.000  -0.3656   0.03953   0.03036  -0.0615   0.7907   0.2211
  -5.750  -0.3456   0.03855   0.02920  -0.0607   0.7737   0.2250
  -5.500  -0.3226   0.03803   0.02856  -0.0597   0.7579   0.2287
  -5.250  -0.3031   0.03714   0.02747  -0.0589   0.7419   0.2333
  -5.000  -0.2861   0.03575   0.02571  -0.0582   0.7273   0.2383
  -4.750  -0.2641   0.03496   0.02474  -0.0574   0.7144   0.2420
  -4.500  -0.2410   0.03451   0.02423  -0.0565   0.7006   0.2456
  -4.250  -0.2187   0.03386   0.02342  -0.0558   0.6878   0.2501
  -4.000  -0.1967   0.03296   0.02221  -0.0550   0.6767   0.2549
  -3.750  -0.1741   0.03227   0.02137  -0.0544   0.6642   0.2591
  -3.500  -0.1491   0.03186   0.02088  -0.0536   0.6545   0.2632
  -3.250  -0.1257   0.03141   0.02034  -0.0529   0.6423   0.2681
  -3.000  -0.1010   0.03075   0.01938  -0.0523   0.6336   0.2739
  -2.750  -0.0766   0.03033   0.01891  -0.0518   0.6222   0.2784
  -2.500  -0.0505   0.02994   0.01844  -0.0511   0.6135   0.2838
  -2.250  -0.0258   0.02962   0.01799  -0.0506   0.6028   0.2908
  -2.000   0.0003   0.02921   0.01742  -0.0500   0.5942   0.2975
  -1.750   0.0258   0.02897   0.01718  -0.0494   0.5845   0.3039
  -1.500   0.0519   0.02866   0.01671  -0.0489   0.5753   0.3126
  -1.250   0.0782   0.02841   0.01643  -0.0483   0.5670   0.3208
  -1.000   0.1037   0.02829   0.01626  -0.0478   0.5571   0.3310
  -0.750   0.1312   0.02802   0.01589  -0.0472   0.5496   0.3414
  -0.500   0.1564   0.02802   0.01590  -0.0468   0.5395   0.3533
  -0.250   0.1829   0.02790   0.01576  -0.0462   0.5313   0.3656
   0.000   0.2089   0.02789   0.01567  -0.0456   0.5232   0.3805
   0.250   0.2335   0.02794   0.01577  -0.0450   0.5138   0.3955
   0.500   0.2605   0.02784   0.01561  -0.0443   0.5068   0.4117
   0.750   0.2840   0.02803   0.01589  -0.0437   0.4978   0.4290
   1.000   0.3089   0.02808   0.01596  -0.0430   0.4897   0.4483
   1.250   0.3360   0.02798   0.01582  -0.0423   0.4837   0.4702
   1.500   0.3567   0.02829   0.01637  -0.0414   0.4743   0.4928
   1.750   0.3805   0.02832   0.01654  -0.0404   0.4672   0.5217
   2.000   0.4062   0.02819   0.01651  -0.0394   0.4620   0.5616
   2.250   0.4234   0.02855   0.01729  -0.0378   0.4532   0.6115
   2.500   0.4449   0.02847   0.01765  -0.0360   0.4467   0.7025
   2.750   0.5074   0.02822   0.01772  -0.0406   0.4402   0.8898
   3.000   0.5538   0.02911   0.01864  -0.0451   0.4305   1.0000
   3.250   0.5747   0.02954   0.01887  -0.0441   0.4251   1.0000
   3.500   0.5991   0.02979   0.01887  -0.0432   0.4210   1.0000
   3.750   0.6112   0.03094   0.02007  -0.0417   0.4137   1.0000
   4.000   0.6297   0.03166   0.02071  -0.0405   0.4083   1.0000
   4.250   0.6525   0.03212   0.02103  -0.0396   0.4043   1.0000
   4.500   0.6769   0.03253   0.02126  -0.0388   0.4010   1.0000
   4.750   0.6834   0.03422   0.02310  -0.0371   0.3945   1.0000
   5.000   0.6994   0.03520   0.02406  -0.0359   0.3897   1.0000
   5.250   0.7213   0.03575   0.02450  -0.0350   0.3860   1.0000
   5.500   0.7479   0.03602   0.02464  -0.0343   0.3831   1.0000
   5.750   0.7459   0.03834   0.02711  -0.0322   0.3772   1.0000
   6.000   0.7505   0.04018   0.02901  -0.0306   0.3723   1.0000
   6.250   0.7648   0.04136   0.03016  -0.0294   0.3688   1.0000
   6.500   0.7855   0.04213   0.03087  -0.0285   0.3663   1.0000
   6.750   0.8110   0.04263   0.03128  -0.0279   0.3642   1.0000
   7.000   0.7039   0.05269   0.04172  -0.0233   0.3534   1.0000
   7.250   0.7052   0.05520   0.04421  -0.0227   0.3495   1.0000
   7.500   0.7254   0.05596   0.04492  -0.0218   0.3472   1.0000
   7.750   0.7518   0.05621   0.04510  -0.0209   0.3456   1.0000
   8.250   0.6415   0.07561   0.06470  -0.0263   0.3299   1.0000
   8.500   0.6612   0.07670   0.06576  -0.0257   0.3280   1.0000
   9.000   0.6211   0.08826   0.07740  -0.0290   0.3190   1.0000
   9.250   0.6238   0.09140   0.08054  -0.0295   0.3157   1.0000
   9.500   0.6357   0.09348   0.08261  -0.0295   0.3128   1.0000
   9.750   0.6547   0.09481   0.08393  -0.0290   0.3105   1.0000
  10.000   0.6776   0.09578   0.08489  -0.0283   0.3087   1.0000
  10.250   0.6416   0.10319   0.09237  -0.0313   0.3021   1.0000
  10.500   0.6467   0.10595   0.09516  -0.0317   0.2976   1.0000
  10.750   0.6640   0.10739   0.09660  -0.0313   0.2941   1.0000
  11.000   0.6911   0.10774   0.09692  -0.0302   0.2914   1.0000
  11.250   0.6669   0.11356   0.10281  -0.0326   0.2829   1.0000
  11.500   0.6802   0.11529   0.10455  -0.0325   0.2780   1.0000
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