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EPPLER E1212MOD AIRFOIL (e1212mod-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER E1212MOD AIRFOIL (e1212mod-il)
Reynolds number: 100,000
Max Cl/Cd: 27.95 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e1212mod-il-100000.txt
Download as CSV file: xf-e1212mod-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3866   0.08046   0.07570  -0.0349   1.0000   0.2060
  -8.000  -0.3729   0.07768   0.07300  -0.0339   1.0000   0.2067
  -7.750  -0.3667   0.07607   0.07154  -0.0321   1.0000   0.2077
  -7.500  -0.3616   0.06561   0.06099  -0.0458   0.9513   0.2018
  -7.250  -0.4728   0.04036   0.03442  -0.0666   0.9087   0.2066
  -7.000  -0.4141   0.04239   0.03675  -0.0673   0.8805   0.2108
  -6.750  -0.3957   0.04088   0.03501  -0.0670   0.8521   0.2162
  -6.500  -0.4065   0.03615   0.02942  -0.0662   0.8295   0.2228
  -6.250  -0.3752   0.03656   0.03000  -0.0652   0.8070   0.2265
  -6.000  -0.3509   0.03658   0.02996  -0.0639   0.7870   0.2313
  -5.750  -0.3399   0.03468   0.02764  -0.0629   0.7707   0.2373
  -5.500  -0.3232   0.03337   0.02603  -0.0617   0.7565   0.2421
  -5.250  -0.2966   0.03350   0.02623  -0.0607   0.7415   0.2464
  -5.000  -0.2760   0.03275   0.02532  -0.0598   0.7281   0.2515
  -4.750  -0.2590   0.03132   0.02339  -0.0588   0.7179   0.2565
  -4.500  -0.2366   0.03045   0.02248  -0.0581   0.7053   0.2602
  -4.250  -0.2115   0.03004   0.02199  -0.0572   0.6957   0.2638
  -4.000  -0.1881   0.02939   0.02125  -0.0566   0.6837   0.2677
  -3.750  -0.1649   0.02857   0.02011  -0.0558   0.6754   0.2722
  -3.500  -0.1424   0.02778   0.01904  -0.0552   0.6640   0.2762
  -3.250  -0.1168   0.02707   0.01828  -0.0545   0.6555   0.2795
  -3.000  -0.0917   0.02668   0.01789  -0.0539   0.6446   0.2836
  -2.750  -0.0660   0.02616   0.01719  -0.0532   0.6359   0.2884
  -2.500  -0.0411   0.02569   0.01650  -0.0526   0.6259   0.2933
  -2.250  -0.0152   0.02507   0.01576  -0.0520   0.6167   0.2976
  -2.000   0.0108   0.02475   0.01542  -0.0514   0.6075   0.3027
  -1.750   0.0368   0.02442   0.01499  -0.0507   0.5974   0.3092
  -1.500   0.0634   0.02407   0.01438  -0.0501   0.5891   0.3160
  -1.250   0.0890   0.02374   0.01416  -0.0495   0.5785   0.3221
  -1.000   0.1166   0.02347   0.01369  -0.0489   0.5707   0.3309
  -0.750   0.1414   0.02327   0.01355  -0.0483   0.5597   0.3398
  -0.500   0.1685   0.02307   0.01327  -0.0477   0.5514   0.3511
  -0.250   0.1937   0.02297   0.01322  -0.0470   0.5417   0.3631
   0.000   0.2200   0.02288   0.01304  -0.0464   0.5327   0.3786
   0.250   0.2464   0.02281   0.01300  -0.0457   0.5251   0.3946
   0.500   0.2705   0.02281   0.01316  -0.0450   0.5152   0.4125
   0.750   0.2973   0.02273   0.01303  -0.0443   0.5079   0.4329
   1.000   0.3215   0.02284   0.01325  -0.0435   0.4992   0.4531
   1.250   0.3465   0.02282   0.01332  -0.0428   0.4906   0.4741
   1.500   0.3740   0.02281   0.01326  -0.0422   0.4844   0.4974
   1.750   0.3964   0.02301   0.01372  -0.0413   0.4757   0.5213
   2.000   0.4216   0.02307   0.01390  -0.0405   0.4685   0.5510
   2.250   0.4493   0.02304   0.01394  -0.0399   0.4631   0.5917
   2.500   0.4699   0.02319   0.01461  -0.0385   0.4557   0.6497
   2.750   0.4963   0.02295   0.01499  -0.0372   0.4487   0.7985
   3.000   0.6034   0.02311   0.01504  -0.0512   0.4394   1.0000
   3.250   0.6199   0.02376   0.01571  -0.0497   0.4324   1.0000
   3.500   0.6414   0.02419   0.01602  -0.0486   0.4271   1.0000
   3.750   0.6656   0.02451   0.01616  -0.0477   0.4231   1.0000
   4.000   0.6867   0.02520   0.01677  -0.0467   0.4188   1.0000
   4.250   0.7023   0.02616   0.01783  -0.0451   0.4132   1.0000
   4.500   0.7231   0.02681   0.01845  -0.0440   0.4087   1.0000
   4.750   0.7469   0.02726   0.01880  -0.0432   0.4052   1.0000
   5.000   0.7731   0.02766   0.01904  -0.0426   0.4022   1.0000
   5.250   0.7857   0.02903   0.02057  -0.0409   0.3976   1.0000
   5.500   0.7995   0.03028   0.02192  -0.0394   0.3928   1.0000
   5.750   0.8200   0.03104   0.02266  -0.0384   0.3892   1.0000
   6.000   0.8427   0.03170   0.02327  -0.0376   0.3864   1.0000
   6.250   0.8685   0.03225   0.02373  -0.0371   0.3841   1.0000
   6.500   0.8846   0.03366   0.02518  -0.0359   0.3814   1.0000
   6.750   0.8665   0.03759   0.02949  -0.0328   0.3770   1.0000
   7.000   0.8287   0.04317   0.03538  -0.0293   0.3725   1.0000
   7.250   0.5291   0.07865   0.07133  -0.0349   0.3804   1.0000
   7.500   0.5468   0.08122   0.07388  -0.0349   0.3816   1.0000
   7.750   0.5700   0.08346   0.07609  -0.0348   0.3824   1.0000
   8.000   0.4585   0.09827   0.09111  -0.0424   0.4237   1.0000
   8.250   0.4925   0.10109   0.09390  -0.0424   0.4219   1.0000
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