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EPPLER 1210 AIRFOIL (e1210-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 1210 AIRFOIL (e1210-il)
Reynolds number: 200,000
Max Cl/Cd: 65.09 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e1210-il-200000-n5.txt
Download as CSV file: xf-e1210-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 1210 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.7004   0.04014   0.03568  -0.0791   1.0000   0.0326
 -11.250  -0.7034   0.03547   0.03078  -0.0835   0.9945   0.0332
 -11.000  -0.6828   0.03228   0.02737  -0.0877   0.9749   0.0344
 -10.750  -0.6594   0.02963   0.02442  -0.0908   0.9492   0.0358
 -10.500  -0.6218   0.02806   0.02274  -0.0948   0.9268   0.0373
 -10.250  -0.5810   0.02615   0.02051  -0.0993   0.9031   0.0398
 -10.000  -0.5408   0.02506   0.01930  -0.1028   0.8749   0.0417
  -9.500  -0.4823   0.02324   0.01702  -0.1048   0.8200   0.0459
  -9.250  -0.4583   0.02256   0.01613  -0.1045   0.7967   0.0481
  -9.000  -0.4350   0.02194   0.01530  -0.1040   0.7762   0.0501
  -8.750  -0.4110   0.02152   0.01473  -0.1034   0.7575   0.0523
  -8.500  -0.3875   0.02094   0.01391  -0.1027   0.7405   0.0548
  -8.250  -0.3630   0.02065   0.01354  -0.1021   0.7241   0.0570
  -8.000  -0.3386   0.02015   0.01280  -0.1015   0.7091   0.0599
  -7.750  -0.3136   0.01990   0.01249  -0.1009   0.6949   0.0621
  -7.500  -0.2885   0.01955   0.01197  -0.1003   0.6811   0.0650
  -7.250  -0.2631   0.01920   0.01149  -0.0997   0.6680   0.0675
  -7.000  -0.2375   0.01896   0.01114  -0.0992   0.6558   0.0700
  -6.750  -0.2117   0.01855   0.01053  -0.0986   0.6434   0.0730
  -6.500  -0.1858   0.01835   0.01028  -0.0981   0.6320   0.0752
  -6.250  -0.1596   0.01809   0.00989  -0.0976   0.6204   0.0782
  -6.000  -0.1333   0.01777   0.00943  -0.0971   0.6098   0.0810
  -5.750  -0.1069   0.01759   0.00918  -0.0966   0.5989   0.0835
  -5.500  -0.0802   0.01734   0.00880  -0.0961   0.5889   0.0868
  -5.250  -0.0537   0.01709   0.00845  -0.0957   0.5787   0.0896
  -5.000  -0.0268   0.01692   0.00823  -0.0952   0.5691   0.0925
  -4.750   0.0001   0.01672   0.00789  -0.0948   0.5595   0.0960
  -4.500   0.0269   0.01650   0.00761  -0.0943   0.5508   0.0989
  -4.250   0.0539   0.01635   0.00741  -0.0939   0.5413   0.1020
  -4.000   0.0810   0.01620   0.00712  -0.0934   0.5329   0.1057
  -3.750   0.1081   0.01600   0.00689  -0.0930   0.5241   0.1089
  -3.500   0.1349   0.01589   0.00671  -0.0926   0.5161   0.1124
  -3.250   0.1624   0.01575   0.00650  -0.0922   0.5078   0.1164
  -3.000   0.1893   0.01560   0.00630  -0.0918   0.4995   0.1201
  -2.750   0.2164   0.01549   0.00616  -0.0914   0.4921   0.1240
  -2.500   0.2439   0.01539   0.00599  -0.0910   0.4844   0.1285
  -2.250   0.2706   0.01529   0.00583  -0.0906   0.4773   0.1326
  -2.000   0.2980   0.01519   0.00573  -0.0902   0.4698   0.1372
  -1.750   0.3252   0.01513   0.00560  -0.0898   0.4623   0.1422
  -1.500   0.3520   0.01506   0.00549  -0.0894   0.4559   0.1472
  -1.250   0.3794   0.01499   0.00543  -0.0890   0.4491   0.1529
  -1.000   0.4065   0.01497   0.00535  -0.0886   0.4423   0.1590
  -0.750   0.4333   0.01492   0.00530  -0.0882   0.4361   0.1657
  -0.500   0.4606   0.01489   0.00526  -0.0879   0.4292   0.1735
  -0.250   0.4874   0.01486   0.00524  -0.0875   0.4230   0.1819
   0.000   0.5143   0.01489   0.00522  -0.0871   0.4175   0.1923
   0.250   0.5414   0.01485   0.00525  -0.0867   0.4112   0.2052
   0.500   0.5681   0.01485   0.00526  -0.0863   0.4051   0.2210
   0.750   0.5946   0.01487   0.00530  -0.0859   0.3998   0.2423
   1.000   0.6215   0.01484   0.00537  -0.0856   0.3940   0.2713
   1.250   0.6479   0.01481   0.00545  -0.0852   0.3885   0.3122
   1.500   0.6735   0.01478   0.00554  -0.0847   0.3834   0.3691
   1.750   0.6993   0.01467   0.00569  -0.0843   0.3782   0.4483
   2.000   0.7238   0.01450   0.00585  -0.0835   0.3728   0.5553
   2.250   0.7456   0.01428   0.00601  -0.0820   0.3682   0.6935
   2.500   0.7822   0.01397   0.00611  -0.0829   0.3633   1.0000
   2.750   0.8085   0.01415   0.00625  -0.0825   0.3582   1.0000
   3.000   0.8344   0.01436   0.00637  -0.0820   0.3532   1.0000
   3.250   0.8598   0.01460   0.00650  -0.0814   0.3489   1.0000
   3.500   0.8856   0.01483   0.00667  -0.0809   0.3450   1.0000
   3.750   0.9115   0.01505   0.00686  -0.0805   0.3405   1.0000
   4.000   0.9369   0.01528   0.00704  -0.0800   0.3360   1.0000
   4.250   0.9618   0.01555   0.00721  -0.0794   0.3320   1.0000
   4.500   0.9868   0.01582   0.00742  -0.0788   0.3282   1.0000
   4.750   1.0123   0.01606   0.00767  -0.0783   0.3242   1.0000
   5.000   1.0372   0.01633   0.00791  -0.0777   0.3203   1.0000
   5.250   1.0616   0.01661   0.00814  -0.0771   0.3166   1.0000
   5.500   1.0855   0.01694   0.00839  -0.0764   0.3133   1.0000
   5.750   1.1101   0.01722   0.00868  -0.0758   0.3095   1.0000
   6.000   1.1343   0.01751   0.00897  -0.0752   0.3057   1.0000
   6.250   1.1579   0.01782   0.00927  -0.0745   0.3021   1.0000
   6.500   1.1811   0.01816   0.00957  -0.0738   0.2990   1.0000
   6.750   1.2039   0.01854   0.00988  -0.0730   0.2962   1.0000
   7.000   1.2272   0.01886   0.01026  -0.0723   0.2930   1.0000
   7.250   1.2497   0.01920   0.01063  -0.0715   0.2895   1.0000
   7.500   1.2716   0.01955   0.01098  -0.0706   0.2861   1.0000
   7.750   1.2929   0.01994   0.01135  -0.0696   0.2831   1.0000
   8.000   1.3138   0.02037   0.01172  -0.0687   0.2804   1.0000
   8.250   1.3348   0.02077   0.01217  -0.0677   0.2777   1.0000
   8.500   1.3552   0.02118   0.01265  -0.0666   0.2748   1.0000
   8.750   1.3746   0.02160   0.01311  -0.0655   0.2719   1.0000
   9.000   1.3924   0.02203   0.01355  -0.0641   0.2690   1.0000
   9.250   1.4090   0.02249   0.01400  -0.0625   0.2665   1.0000
   9.500   1.4256   0.02301   0.01448  -0.0610   0.2639   1.0000
   9.750   1.4412   0.02352   0.01509  -0.0594   0.2614   1.0000
  10.000   1.4566   0.02407   0.01571  -0.0578   0.2588   1.0000
  10.250   1.4713   0.02465   0.01635  -0.0562   0.2564   1.0000
  10.500   1.4853   0.02527   0.01701  -0.0546   0.2539   1.0000
  10.750   1.4990   0.02592   0.01767  -0.0531   0.2516   1.0000
  11.000   1.5132   0.02662   0.01834  -0.0517   0.2494   1.0000
  11.250   1.5253   0.02741   0.01922  -0.0502   0.2470   1.0000
  11.500   1.5362   0.02829   0.02020  -0.0488   0.2446   1.0000
  11.750   1.5469   0.02922   0.02122  -0.0474   0.2423   1.0000
  12.000   1.5572   0.03021   0.02228  -0.0461   0.2400   1.0000
  12.250   1.5672   0.03124   0.02335  -0.0449   0.2378   1.0000
  12.500   1.5782   0.03227   0.02439  -0.0439   0.2357   1.0000
  12.750   1.5901   0.03331   0.02542  -0.0429   0.2336   1.0000
  13.000   1.5953   0.03480   0.02708  -0.0419   0.2314   1.0000
  13.250   1.6008   0.03636   0.02876  -0.0410   0.2291   1.0000
  13.500   1.6058   0.03800   0.03049  -0.0402   0.2267   1.0000
  13.750   1.6112   0.03966   0.03223  -0.0395   0.2244   1.0000
  14.000   1.6183   0.04121   0.03382  -0.0389   0.2222   1.0000
  14.250   1.6280   0.04257   0.03518  -0.0384   0.2202   1.0000
  14.500   1.6302   0.04468   0.03740  -0.0379   0.2181   1.0000
  14.750   1.6270   0.04737   0.04025  -0.0377   0.2156   1.0000
  15.000   1.6247   0.05006   0.04307  -0.0376   0.2130   1.0000
  15.250   1.6237   0.05269   0.04579  -0.0377   0.2105   1.0000
  15.500   1.6271   0.05487   0.04802  -0.0376   0.2082   1.0000
  15.750   1.6361   0.05646   0.04960  -0.0375   0.2061   1.0000
  16.000   1.6266   0.06031   0.05362  -0.0381   0.2036   1.0000
  16.250   1.6126   0.06490   0.05839  -0.0391   0.2007   1.0000
  16.500   1.6027   0.06910   0.06272  -0.0401   0.1979   1.0000
  16.750   1.5997   0.07248   0.06617  -0.0409   0.1953   1.0000
  17.000   1.6089   0.07423   0.06791  -0.0411   0.1932   1.0000
  17.250   1.5961   0.07910   0.07292  -0.0426   0.1905   1.0000
  17.500   1.5585   0.08785   0.08193  -0.0458   0.1867   1.0000
  17.750   1.5406   0.09388   0.08809  -0.0481   0.1835   1.0000
  18.000   1.5471   0.09616   0.09038  -0.0488   0.1811   1.0000
  18.250   1.5691   0.09600   0.09017  -0.0483   0.1793   1.0000
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