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EPPLER E1212 AIRFOIL (e1212-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER E1212 AIRFOIL (e1212-il)
Reynolds number: 500,000
Max Cl/Cd: 85.46 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e1212-il-500000-n5.txt
Download as CSV file: xf-e1212-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.250  -0.8303   0.08938   0.08517  -0.0392   1.0000   0.0231
 -16.000  -0.8445   0.08387   0.07960  -0.0421   1.0000   0.0236
 -15.750  -0.8609   0.07819   0.07385  -0.0452   1.0000   0.0240
 -15.500  -0.8783   0.07259   0.06818  -0.0482   1.0000   0.0242
 -15.250  -0.9037   0.06621   0.06171  -0.0517   1.0000   0.0245
 -15.000  -0.9334   0.05941   0.05480  -0.0555   1.0000   0.0245
 -14.750  -0.9688   0.05193   0.04719  -0.0597   1.0000   0.0245
 -14.500  -1.0077   0.04378   0.03887  -0.0645   1.0000   0.0243
 -14.250  -1.0388   0.03587   0.03075  -0.0701   1.0000   0.0242
 -14.000  -1.0591   0.02986   0.02454  -0.0750   1.0000   0.0245
 -13.750  -1.0725   0.02692   0.02147  -0.0752   1.0000   0.0250
 -13.500  -1.0815   0.02543   0.01990  -0.0722   1.0000   0.0257
 -13.250  -1.0812   0.02422   0.01863  -0.0695   1.0000   0.0268
 -13.000  -1.0749   0.02315   0.01751  -0.0674   1.0000   0.0281
 -12.750  -1.0646   0.02226   0.01657  -0.0655   1.0000   0.0298
 -12.500  -1.0537   0.02134   0.01562  -0.0636   1.0000   0.0318
 -12.250  -1.0401   0.02057   0.01482  -0.0618   1.0000   0.0339
 -12.000  -1.0171   0.01970   0.01393  -0.0618   0.9977   0.0370
 -11.750  -0.9859   0.01882   0.01303  -0.0634   0.9897   0.0411
 -11.500  -0.9569   0.01802   0.01222  -0.0643   0.9774   0.0454
 -11.250  -0.9238   0.01724   0.01142  -0.0659   0.9523   0.0507
 -11.000  -0.8682   0.01631   0.01047  -0.0720   0.9189   0.0588
 -10.750  -0.8295   0.01567   0.00970  -0.0744   0.8682   0.0664
 -10.500  -0.8069   0.01530   0.00919  -0.0735   0.8288   0.0724
 -10.000  -0.7617   0.01465   0.00832  -0.0715   0.7749   0.0841
  -9.750  -0.7383   0.01432   0.00791  -0.0707   0.7539   0.0899
  -9.500  -0.7141   0.01403   0.00755  -0.0700   0.7344   0.0954
  -9.250  -0.6892   0.01379   0.00722  -0.0693   0.7162   0.1011
  -9.000  -0.6642   0.01350   0.00689  -0.0687   0.6996   0.1076
  -8.750  -0.6387   0.01325   0.00660  -0.0681   0.6844   0.1142
  -8.500  -0.6128   0.01306   0.00633  -0.0676   0.6697   0.1213
  -8.250  -0.5868   0.01283   0.00609  -0.0671   0.6555   0.1283
  -8.000  -0.5602   0.01266   0.00586  -0.0666   0.6423   0.1342
  -7.750  -0.5336   0.01251   0.00566  -0.0661   0.6296   0.1398
  -7.500  -0.5064   0.01238   0.00545  -0.0658   0.6169   0.1442
  -7.250  -0.4795   0.01224   0.00528  -0.0653   0.6054   0.1489
  -7.000  -0.4520   0.01213   0.00510  -0.0650   0.5934   0.1534
  -6.750  -0.4245   0.01203   0.00493  -0.0646   0.5828   0.1569
  -6.500  -0.3972   0.01191   0.00477  -0.0642   0.5713   0.1609
  -6.250  -0.3695   0.01182   0.00463  -0.0639   0.5613   0.1649
  -6.000  -0.3416   0.01176   0.00448  -0.0636   0.5508   0.1683
  -5.750  -0.3139   0.01165   0.00433  -0.0633   0.5411   0.1716
  -5.500  -0.2862   0.01157   0.00421  -0.0629   0.5309   0.1752
  -5.250  -0.2582   0.01150   0.00410  -0.0627   0.5222   0.1788
  -5.000  -0.2301   0.01146   0.00398  -0.0624   0.5123   0.1819
  -4.750  -0.2021   0.01139   0.00386  -0.0621   0.5035   0.1847
  -4.500  -0.1742   0.01131   0.00375  -0.0618   0.4943   0.1880
  -4.250  -0.1463   0.01127   0.00366  -0.0615   0.4862   0.1913
  -4.000  -0.1180   0.01122   0.00357  -0.0613   0.4774   0.1946
  -3.500  -0.0616   0.01115   0.00340  -0.0607   0.4613   0.2000
  -3.250  -0.0337   0.01110   0.00332  -0.0605   0.4533   0.2034
  -3.000  -0.0056   0.01107   0.00326  -0.0602   0.4457   0.2064
  -2.750   0.0227   0.01105   0.00321  -0.0600   0.4376   0.2097
  -2.250   0.0793   0.01104   0.00310  -0.0595   0.4239   0.2151
  -2.000   0.1072   0.01100   0.00305  -0.0592   0.4164   0.2186
  -1.750   0.1351   0.01100   0.00302  -0.0589   0.4093   0.2223
  -1.500   0.1635   0.01098   0.00300  -0.0587   0.4025   0.2258
  -1.250   0.1916   0.01100   0.00297  -0.0585   0.3958   0.2290
  -1.000   0.2198   0.01104   0.00296  -0.0582   0.3896   0.2319
  -0.750   0.2479   0.01101   0.00294  -0.0580   0.3829   0.2360
  -0.500   0.2757   0.01103   0.00294  -0.0577   0.3760   0.2399
  -0.250   0.3038   0.01105   0.00295  -0.0575   0.3705   0.2442
   0.000   0.3320   0.01108   0.00296  -0.0573   0.3643   0.2484
   0.250   0.3598   0.01112   0.00297  -0.0570   0.3578   0.2524
   0.500   0.3876   0.01114   0.00300  -0.0568   0.3523   0.2572
   0.750   0.4157   0.01117   0.00303  -0.0565   0.3468   0.2625
   1.000   0.4434   0.01123   0.00307  -0.0563   0.3406   0.2679
   1.250   0.4710   0.01128   0.00312  -0.0560   0.3353   0.2742
   1.500   0.4989   0.01131   0.00317  -0.0558   0.3303   0.2811
   1.750   0.5266   0.01137   0.00323  -0.0555   0.3251   0.2878
   2.000   0.5537   0.01145   0.00330  -0.0552   0.3198   0.2959
   2.250   0.5815   0.01149   0.00337  -0.0549   0.3152   0.3055
   2.500   0.6090   0.01153   0.00345  -0.0547   0.3101   0.3170
   3.000   0.6631   0.01169   0.00366  -0.0540   0.3012   0.3444
   3.250   0.6906   0.01173   0.00376  -0.0538   0.2973   0.3607
   3.500   0.7176   0.01179   0.00387  -0.0535   0.2925   0.3797
   3.750   0.7441   0.01187   0.00400  -0.0531   0.2877   0.4041
   4.000   0.7706   0.01194   0.00414  -0.0527   0.2837   0.4332
   4.250   0.7973   0.01196   0.00428  -0.0524   0.2801   0.4676
   4.500   0.8237   0.01200   0.00443  -0.0520   0.2761   0.5048
   4.750   0.8494   0.01206   0.00460  -0.0515   0.2722   0.5479
   5.000   0.8744   0.01212   0.00479  -0.0509   0.2683   0.5993
   5.250   0.8996   0.01208   0.00497  -0.0502   0.2650   0.6661
   5.500   0.9231   0.01202   0.00516  -0.0492   0.2611   0.7459
   5.750   0.9435   0.01194   0.00536  -0.0475   0.2573   0.8443
   6.000   0.9893   0.01206   0.00562  -0.0509   0.2528   1.0000
   6.250   1.0147   0.01223   0.00580  -0.0504   0.2501   1.0000
   6.500   1.0399   0.01242   0.00598  -0.0498   0.2469   1.0000
   6.750   1.0646   0.01264   0.00618  -0.0492   0.2433   1.0000
   7.000   1.0885   0.01290   0.00641  -0.0484   0.2396   1.0000
   7.250   1.1122   0.01316   0.00665  -0.0477   0.2363   1.0000
   7.500   1.1370   0.01337   0.00686  -0.0470   0.2336   1.0000
   7.750   1.1611   0.01360   0.00710  -0.0464   0.2306   1.0000
   8.000   1.1845   0.01386   0.00736  -0.0456   0.2276   1.0000
   8.250   1.2071   0.01415   0.00763  -0.0447   0.2247   1.0000
   8.500   1.2288   0.01448   0.00794  -0.0437   0.2217   1.0000
   8.750   1.2521   0.01471   0.00820  -0.0429   0.2194   1.0000
   9.000   1.2745   0.01498   0.00849  -0.0420   0.2165   1.0000
   9.250   1.2958   0.01528   0.00880  -0.0409   0.2136   1.0000
   9.500   1.3160   0.01562   0.00914  -0.0398   0.2110   1.0000
   9.750   1.3343   0.01599   0.00950  -0.0383   0.2085   1.0000
  10.000   1.3513   0.01634   0.00987  -0.0365   0.2064   1.0000
  10.250   1.3693   0.01665   0.01022  -0.0350   0.2045   1.0000
  10.500   1.3863   0.01700   0.01061  -0.0333   0.2021   1.0000
  10.750   1.4022   0.01741   0.01104  -0.0316   0.1998   1.0000
  11.000   1.4169   0.01788   0.01152  -0.0298   0.1974   1.0000
  11.250   1.4303   0.01842   0.01207  -0.0280   0.1953   1.0000
  11.500   1.4422   0.01905   0.01271  -0.0260   0.1931   1.0000
  11.750   1.4578   0.01956   0.01328  -0.0247   0.1914   1.0000
  12.000   1.4722   0.02015   0.01392  -0.0233   0.1894   1.0000
  12.250   1.4851   0.02084   0.01466  -0.0218   0.1873   1.0000
  12.500   1.4968   0.02164   0.01551  -0.0205   0.1852   1.0000
  12.750   1.5066   0.02260   0.01649  -0.0191   0.1830   1.0000
  13.000   1.5148   0.02373   0.01764  -0.0178   0.1809   1.0000
  13.250   1.5241   0.02486   0.01881  -0.0167   0.1789   1.0000
  13.500   1.5360   0.02588   0.01991  -0.0159   0.1771   1.0000
  13.750   1.5463   0.02706   0.02115  -0.0151   0.1751   1.0000
  14.000   1.5546   0.02843   0.02257  -0.0144   0.1728   1.0000
  14.250   1.5610   0.03000   0.02419  -0.0137   0.1706   1.0000
  14.500   1.5653   0.03181   0.02603  -0.0131   0.1684   1.0000
  14.750   1.5685   0.03376   0.02802  -0.0126   0.1664   1.0000
  15.000   1.5768   0.03534   0.02968  -0.0123   0.1647   1.0000
  15.250   1.5830   0.03712   0.03154  -0.0120   0.1629   1.0000
  15.500   1.5868   0.03916   0.03364  -0.0118   0.1606   1.0000
  15.750   1.5886   0.04143   0.03597  -0.0117   0.1585   1.0000
  16.000   1.5874   0.04405   0.03863  -0.0117   0.1563   1.0000
  16.250   1.5842   0.04693   0.04154  -0.0119   0.1542   1.0000
  16.500   1.5880   0.04919   0.04390  -0.0121   0.1524   1.0000
  16.750   1.5893   0.05177   0.04657  -0.0124   0.1503   1.0000
  17.000   1.5879   0.05468   0.04955  -0.0128   0.1478   1.0000
  17.250   1.5844   0.05791   0.05284  -0.0134   0.1456   1.0000
  17.500   1.5778   0.06158   0.05655  -0.0143   0.1433   1.0000
  17.750   1.5751   0.06486   0.05991  -0.0150   0.1413   1.0000
  18.000   1.5734   0.06807   0.06321  -0.0159   0.1388   1.0000
  18.250   1.5689   0.07171   0.06692  -0.0169   0.1363   1.0000
  18.500   1.5598   0.07600   0.07127  -0.0183   0.1336   1.0000
  18.750   1.5499   0.08045   0.07577  -0.0198   0.1312   1.0000
  19.000   1.5471   0.08405   0.07946  -0.0210   0.1287   1.0000
  19.250   1.5388   0.08847   0.08396  -0.0226   0.1257   1.0000
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