Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

EPPLER E1212 AIRFOIL (e1212-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER E1212 AIRFOIL (e1212-il)
Reynolds number: 1,000,000
Max Cl/Cd: 109.83 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e1212-il-1000000.txt
Download as CSV file: xf-e1212-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E1212 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
  ------ -------- --------- --------- -------- -------- --------
 -16.750  -0.9006   0.08689   0.08334  -0.0403   1.0000   0.0199
 -16.500  -0.9221   0.08045   0.07682  -0.0439   1.0000   0.0203
 -16.250  -0.9449   0.07400   0.07029  -0.0475   1.0000   0.0203
 -16.000  -0.9817   0.06611   0.06228  -0.0520   1.0000   0.0203
 -15.750  -1.0230   0.05781   0.05383  -0.0568   1.0000   0.0202
 -15.500  -1.0676   0.04910   0.04496  -0.0619   1.0000   0.0198
 -15.250  -1.1256   0.03778   0.03339  -0.0694   1.0000   0.0195
 -15.000  -1.1511   0.03016   0.02555  -0.0760   1.0000   0.0195
 -14.750  -1.1629   0.02631   0.02155  -0.0784   1.0000   0.0197
 -14.500  -1.1733   0.02424   0.01937  -0.0768   1.0000   0.0201
 -14.250  -1.1832   0.02295   0.01801  -0.0728   1.0000   0.0206
 -14.000  -1.1793   0.02184   0.01686  -0.0704   1.0000   0.0213
 -13.750  -1.1704   0.02094   0.01592  -0.0682   1.0000   0.0223
 -13.500  -1.1587   0.02015   0.01508  -0.0662   1.0000   0.0233
 -13.250  -1.1475   0.01926   0.01416  -0.0642   1.0000   0.0248
 -13.000  -1.1328   0.01857   0.01344  -0.0624   1.0000   0.0265
 -12.750  -1.1186   0.01779   0.01265  -0.0606   1.0000   0.0287
 -12.500  -1.1029   0.01708   0.01194  -0.0589   1.0000   0.0315
 -12.250  -1.0862   0.01645   0.01130  -0.0572   1.0000   0.0345
 -12.000  -1.0653   0.01577   0.01063  -0.0564   0.9996   0.0387
 -11.750  -1.0281   0.01501   0.00990  -0.0587   0.9966   0.0445
 -11.500  -0.9895   0.01431   0.00924  -0.0612   0.9929   0.0516
 -11.250  -0.9554   0.01368   0.00863  -0.0627   0.9868   0.0583
 -11.000  -0.9186   0.01306   0.00806  -0.0647   0.9793   0.0655
 -10.750  -0.8877   0.01253   0.00756  -0.0654   0.9586   0.0723
 -10.500  -0.8321   0.01192   0.00696  -0.0711   0.9298   0.0816
 -10.250  -0.7983   0.01164   0.00652  -0.0721   0.8721   0.0883
 -10.000  -0.7747   0.01149   0.00622  -0.0710   0.8321   0.0938
  -9.750  -0.7507   0.01129   0.00593  -0.0701   0.8021   0.0997
  -9.500  -0.7259   0.01109   0.00566  -0.0693   0.7775   0.1051
  -9.250  -0.7000   0.01094   0.00542  -0.0687   0.7559   0.1104
  -8.750  -0.6475   0.01061   0.00498  -0.0676   0.7182   0.1209
  -8.500  -0.6211   0.01041   0.00476  -0.0671   0.7020   0.1264
  -8.250  -0.5939   0.01030   0.00458  -0.0667   0.6863   0.1309
  -8.000  -0.5670   0.01016   0.00439  -0.0662   0.6712   0.1361
  -7.750  -0.5394   0.01004   0.00425  -0.0659   0.6572   0.1416
  -7.500  -0.5118   0.00993   0.00409  -0.0655   0.6440   0.1470
  -7.250  -0.4842   0.00986   0.00399  -0.0652   0.6304   0.1528
  -7.000  -0.4558   0.00980   0.00388  -0.0649   0.6185   0.1566
  -6.750  -0.4283   0.00968   0.00374  -0.0646   0.6064   0.1616
  -6.500  -0.4000   0.00962   0.00364  -0.0643   0.5943   0.1656
  -6.250  -0.3714   0.00960   0.00355  -0.0641   0.5837   0.1685
  -6.000  -0.3436   0.00950   0.00341  -0.0638   0.5724   0.1725
  -5.750  -0.3153   0.00942   0.00331  -0.0635   0.5619   0.1763
  -5.500  -0.2870   0.00940   0.00324  -0.0633   0.5511   0.1796
  -5.250  -0.2581   0.00938   0.00316  -0.0631   0.5418   0.1823
  -5.000  -0.2299   0.00933   0.00306  -0.0628   0.5314   0.1853
  -4.750  -0.2016   0.00923   0.00296  -0.0626   0.5220   0.1893
  -4.500  -0.1732   0.00920   0.00289  -0.0624   0.5125   0.1926
  -4.250  -0.1444   0.00919   0.00284  -0.0622   0.5039   0.1954
  -4.000  -0.1156   0.00919   0.00278  -0.0620   0.4946   0.1977
  -3.750  -0.0872   0.00915   0.00270  -0.0617   0.4857   0.2004
  -3.500  -0.0588   0.00907   0.00261  -0.0615   0.4774   0.2045
  -3.250  -0.0305   0.00907   0.00257  -0.0613   0.4685   0.2077
  -3.000  -0.0015   0.00904   0.00253  -0.0612   0.4615   0.2106
  -2.750   0.0271   0.00906   0.00249  -0.0610   0.4527   0.2131
  -2.500   0.0560   0.00908   0.00247  -0.0608   0.4452   0.2147
  -2.250   0.0842   0.00900   0.00238  -0.0606   0.4378   0.2192
  -2.000   0.1124   0.00900   0.00235  -0.0603   0.4295   0.2231
  -1.750   0.1414   0.00898   0.00233  -0.0602   0.4231   0.2264
  -1.500   0.1699   0.00900   0.00231  -0.0600   0.4152   0.2292
  -1.250   0.1986   0.00904   0.00231  -0.0598   0.4084   0.2314
  -1.000   0.2272   0.00900   0.00227  -0.0597   0.4018   0.2359
  -0.750   0.2553   0.00901   0.00226  -0.0595   0.3941   0.2403
  -0.500   0.2840   0.00901   0.00226  -0.0593   0.3879   0.2443
  -0.250   0.3127   0.00904   0.00226  -0.0591   0.3814   0.2480
   0.000   0.3408   0.00911   0.00228  -0.0589   0.3738   0.2509
   0.250   0.3694   0.00908   0.00227  -0.0588   0.3685   0.2572
   0.500   0.3978   0.00910   0.00229  -0.0586   0.3624   0.2627
   0.750   0.4258   0.00918   0.00233  -0.0583   0.3554   0.2674
   1.000   0.4545   0.00917   0.00235  -0.0582   0.3507   0.2737
   1.250   0.4827   0.00919   0.00238  -0.0580   0.3448   0.2811
   1.500   0.5105   0.00928   0.00243  -0.0578   0.3382   0.2876
   1.750   0.5389   0.00927   0.00247  -0.0576   0.3340   0.2981
   2.000   0.5672   0.00931   0.00252  -0.0575   0.3291   0.3081
   2.250   0.5949   0.00935   0.00259  -0.0572   0.3235   0.3219
   2.500   0.6226   0.00940   0.00266  -0.0570   0.3181   0.3369
   2.750   0.6508   0.00941   0.00272  -0.0568   0.3138   0.3550
   3.000   0.6785   0.00944   0.00280  -0.0566   0.3090   0.3773
   3.250   0.7055   0.00949   0.00291  -0.0563   0.3035   0.4055
   3.500   0.7332   0.00949   0.00300  -0.0561   0.2999   0.4381
   3.750   0.7608   0.00948   0.00310  -0.0558   0.2960   0.4762
   4.000   0.7877   0.00949   0.00321  -0.0555   0.2914   0.5197
   4.250   0.8138   0.00953   0.00336  -0.0551   0.2859   0.5705
   4.500   0.8407   0.00948   0.00348  -0.0547   0.2826   0.6309
   4.750   0.8666   0.00939   0.00361  -0.0542   0.2790   0.7088
   5.000   0.8903   0.00929   0.00377  -0.0531   0.2751   0.8011
   5.250   0.9110   0.00917   0.00396  -0.0512   0.2707   0.9263
   5.500   0.9639   0.00932   0.00412  -0.0563   0.2664   1.0000
   5.750   0.9899   0.00945   0.00424  -0.0558   0.2630   1.0000
   6.000   1.0155   0.00962   0.00437  -0.0552   0.2589   1.0000
   6.250   1.0404   0.00984   0.00454  -0.0545   0.2544   1.0000
   6.500   1.0661   0.01000   0.00470  -0.0540   0.2512   1.0000
   6.750   1.0923   0.01014   0.00484  -0.0536   0.2485   1.0000
   7.000   1.1180   0.01031   0.00500  -0.0530   0.2451   1.0000
   7.250   1.1430   0.01052   0.00518  -0.0524   0.2415   1.0000
   7.500   1.1668   0.01081   0.00542  -0.0517   0.2369   1.0000
   7.750   1.1930   0.01094   0.00557  -0.0513   0.2348   1.0000
   8.000   1.2186   0.01111   0.00575  -0.0508   0.2319   1.0000
   8.250   1.2433   0.01132   0.00594  -0.0502   0.2287   1.0000
   8.500   1.2671   0.01157   0.00618  -0.0494   0.2253   1.0000
   8.750   1.2897   0.01188   0.00646  -0.0485   0.2216   1.0000
   9.000   1.3150   0.01205   0.00665  -0.0480   0.2198   1.0000
   9.250   1.3394   0.01224   0.00686  -0.0474   0.2173   1.0000
   9.500   1.3629   0.01248   0.00710  -0.0466   0.2145   1.0000
   9.750   1.3851   0.01276   0.00737  -0.0457   0.2115   1.0000
  10.000   1.4051   0.01314   0.00772  -0.0444   0.2079   1.0000
  10.250   1.4276   0.01337   0.00798  -0.0435   0.2060   1.0000
  10.500   1.4504   0.01358   0.00823  -0.0427   0.2041   1.0000
  10.750   1.4717   0.01384   0.00850  -0.0416   0.2018   1.0000
  11.000   1.4904   0.01414   0.00880  -0.0401   0.1994   1.0000
  11.250   1.5058   0.01449   0.00916  -0.0381   0.1968   1.0000
  11.500   1.5176   0.01496   0.00962  -0.0356   0.1937   1.0000
  11.750   1.5351   0.01527   0.00996  -0.0340   0.1921   1.0000
  12.000   1.5533   0.01556   0.01030  -0.0325   0.1904   1.0000
  12.250   1.5700   0.01592   0.01069  -0.0310   0.1885   1.0000
  12.500   1.5850   0.01635   0.01114  -0.0293   0.1862   1.0000
  12.750   1.5978   0.01689   0.01169  -0.0274   0.1840   1.0000
  13.000   1.6072   0.01760   0.01241  -0.0252   0.1813   1.0000
  13.250   1.6175   0.01833   0.01317  -0.0234   0.1791   1.0000
  13.500   1.6332   0.01886   0.01375  -0.0222   0.1778   1.0000
  13.750   1.6474   0.01949   0.01443  -0.0210   0.1761   1.0000
  14.000   1.6595   0.02027   0.01525  -0.0197   0.1741   1.0000
  14.250   1.6695   0.02123   0.01623  -0.0184   0.1719   1.0000
  14.500   1.6768   0.02243   0.01746  -0.0171   0.1697   1.0000
  14.750   1.6795   0.02401   0.01907  -0.0157   0.1670   1.0000
  15.000   1.6911   0.02508   0.02020  -0.0150   0.1657   1.0000
  15.250   1.7029   0.02616   0.02135  -0.0144   0.1642   1.0000
  15.500   1.7129   0.02743   0.02266  -0.0138   0.1623   1.0000
  15.750   1.7199   0.02897   0.02425  -0.0132   0.1602   1.0000
  16.000   1.7233   0.03086   0.02618  -0.0126   0.1580   1.0000
  16.250   1.7227   0.03316   0.02851  -0.0121   0.1558   1.0000
  16.500   1.7244   0.03530   0.03071  -0.0118   0.1537   1.0000
  16.750   1.7324   0.03693   0.03241  -0.0116   0.1520   1.0000
  17.000   1.7367   0.03891   0.03446  -0.0114   0.1501   1.0000
  17.250   1.7368   0.04136   0.03695  -0.0113   0.1479   1.0000
  17.500   1.7335   0.04419   0.03983  -0.0114   0.1459   1.0000
  17.750   1.7243   0.04771   0.04339  -0.0117   0.1433   1.0000
  18.000   1.7231   0.05049   0.04625  -0.0120   0.1416   1.0000
  18.250   1.7249   0.05300   0.04883  -0.0123   0.1397   1.0000
  18.500   1.7225   0.05600   0.05189  -0.0127   0.1373   1.0000
  18.750   1.7141   0.05977   0.05571  -0.0135   0.1348   1.0000
  19.000   1.6992   0.06438   0.06037  -0.0146   0.1320   1.0000
  19.250   1.6946   0.06786   0.06392  -0.0155   0.1300   1.0000
<< Back to EPPLER E1212 AIRFOIL (e1212-il)

Polar data table (+)

Polar graphs


<< Back to EPPLER E1212 AIRFOIL (e1212-il)