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EPPLER 1210 AIRFOIL (e1210-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 1210 AIRFOIL (e1210-il)
Reynolds number: 100,000
Max Cl/Cd: 35.26 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e1210-il-100000.txt
Download as CSV file: xf-e1210-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.1720   0.11007   0.10560  -0.0318   1.0000   0.1234
  -9.250  -0.1784   0.10834   0.10400  -0.0326   1.0000   0.1281
  -9.000  -0.2154   0.10879   0.10471  -0.0338   1.0000   0.1297
  -8.750  -0.1903   0.10413   0.10014  -0.0334   0.9939   0.1321
  -8.500  -0.1507   0.09931   0.09530  -0.0386   0.9748   0.1383
  -8.250  -0.1488   0.09451   0.09050  -0.0514   0.9475   0.1447
  -8.000  -0.0928   0.08953   0.08544  -0.0530   0.9332   0.1519
  -7.750  -0.0874   0.08443   0.08027  -0.0671   0.9084   0.1599
  -7.500  -0.0297   0.08012   0.07580  -0.0681   0.8882   0.1685
  -7.250  -0.0666   0.07747   0.07306  -0.0802   0.8549   0.1757
  -7.000  -0.0014   0.07367   0.06908  -0.0744   0.8363   0.1817
  -6.750  -0.0151   0.07222   0.06756  -0.0771   0.8139   0.1909
  -6.500  -0.0168   0.06875   0.06403  -0.0793   0.7968   0.1952
  -6.250   0.0116   0.06691   0.06206  -0.0757   0.7800   0.2014
  -6.000  -0.0488   0.05166   0.04617  -0.0985   0.7721   0.1587
  -5.750  -0.0314   0.04892   0.04343  -0.0973   0.7589   0.1603
  -5.500  -0.0173   0.04522   0.03952  -0.0980   0.7457   0.1555
  -5.250  -0.0052   0.04096   0.03490  -0.0995   0.7340   0.1538
  -5.000   0.0102   0.03704   0.03044  -0.1007   0.7230   0.1552
  -4.750   0.0279   0.03399   0.02674  -0.1012   0.7112   0.1579
  -4.500   0.0509   0.03247   0.02510  -0.1006   0.7005   0.1620
  -4.250   0.0735   0.03158   0.02415  -0.0999   0.6877   0.1663
  -4.000   0.0986   0.03013   0.02222  -0.0997   0.6784   0.1715
  -3.750   0.1216   0.02878   0.02046  -0.0993   0.6661   0.1761
  -3.250   0.1718   0.02730   0.01881  -0.0981   0.6450   0.1868
  -3.000   0.1999   0.02659   0.01757  -0.0977   0.6367   0.1930
  -2.750   0.2234   0.02583   0.01690  -0.0971   0.6251   0.1985
  -2.500   0.2512   0.02535   0.01621  -0.0966   0.6169   0.2057
  -2.250   0.2765   0.02496   0.01561  -0.0960   0.6060   0.2123
  -2.000   0.3036   0.02439   0.01501  -0.0956   0.5977   0.2197
  -1.750   0.3293   0.02419   0.01469  -0.0950   0.5881   0.2278
  -1.500   0.3562   0.02373   0.01417  -0.0945   0.5795   0.2362
  -1.250   0.3829   0.02356   0.01391  -0.0940   0.5713   0.2461
  -1.000   0.4087   0.02328   0.01363  -0.0934   0.5620   0.2563
  -0.750   0.4376   0.02308   0.01327  -0.0930   0.5554   0.2695
  -0.500   0.4611   0.02299   0.01336  -0.0922   0.5460   0.2824
  -0.250   0.4883   0.02276   0.01310  -0.0917   0.5386   0.2998
   0.000   0.5141   0.02268   0.01309  -0.0911   0.5313   0.3217
   0.250   0.5386   0.02257   0.01316  -0.0903   0.5229   0.3519
   0.500   0.5658   0.02223   0.01299  -0.0898   0.5170   0.4056
   0.750   0.5864   0.02187   0.01334  -0.0883   0.5096   0.5426
   1.000   0.6250   0.02091   0.01333  -0.0884   0.5015   1.0000
   1.250   0.6545   0.02118   0.01321  -0.0884   0.4960   1.0000
   1.500   0.6755   0.02177   0.01378  -0.0874   0.4880   1.0000
   1.750   0.7015   0.02211   0.01394  -0.0869   0.4816   1.0000
   2.000   0.7309   0.02241   0.01394  -0.0868   0.4766   1.0000
   2.250   0.7509   0.02308   0.01467  -0.0857   0.4690   1.0000
   2.500   0.7764   0.02347   0.01493  -0.0851   0.4628   1.0000
   2.750   0.8055   0.02377   0.01500  -0.0850   0.4582   1.0000
   3.000   0.8256   0.02455   0.01583  -0.0840   0.4516   1.0000
   3.250   0.8491   0.02508   0.01631  -0.0833   0.4454   1.0000
   3.500   0.8774   0.02536   0.01642  -0.0831   0.4406   1.0000
   3.750   0.9008   0.02607   0.01707  -0.0824   0.4354   1.0000
   4.000   0.9199   0.02692   0.01801  -0.0813   0.4293   1.0000
   4.250   0.9455   0.02737   0.01837  -0.0809   0.4243   1.0000
   4.500   0.9756   0.02767   0.01846  -0.0809   0.4203   1.0000
   4.750   0.9905   0.02883   0.01978  -0.0794   0.4144   1.0000
   5.000   1.0106   0.02964   0.02062  -0.0785   0.4089   1.0000
   5.250   1.0369   0.03010   0.02099  -0.0782   0.4048   1.0000
   5.500   1.0677   0.03047   0.02118  -0.0783   0.4014   1.0000
   5.750   1.0746   0.03214   0.02311  -0.0762   0.3955   1.0000
   6.000   1.0923   0.03311   0.02413  -0.0750   0.3905   1.0000
   6.250   1.1191   0.03351   0.02445  -0.0747   0.3865   1.0000
   6.500   1.1511   0.03381   0.02459  -0.0750   0.3834   1.0000
   6.750   1.1493   0.03616   0.02724  -0.0723   0.3783   1.0000
   7.000   1.1542   0.03803   0.02926  -0.0702   0.3733   1.0000
   7.250   1.1788   0.03856   0.02974  -0.0697   0.3696   1.0000
   7.500   1.2129   0.03858   0.02963  -0.0701   0.3665   1.0000
   7.750   1.2163   0.04070   0.03189  -0.0680   0.3625   1.0000
   8.000   0.9069   0.07234   0.06445  -0.0602   0.3463   1.0000
   8.250   0.9710   0.06687   0.05888  -0.0574   0.3462   1.0000
   8.500   1.0402   0.06150   0.05342  -0.0552   0.3461   1.0000
   8.750   1.1347   0.05514   0.04691  -0.0549   0.3459   1.0000
  10.250   0.6946   0.13810   0.13076  -0.0824   0.3546   1.0000
  10.500   0.7144   0.14042   0.13306  -0.0824   0.3508   1.0000
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