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EPPLER EA 8(-1)-006 AIRFOIL (ea81006-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER EA 8(-1)-006 AIRFOIL (ea81006-il)
Reynolds number: 1,000,000
Max Cl/Cd: 67.43 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ea81006-il-1000000.txt
Download as CSV file: xf-ea81006-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER EA 8(-1)-006 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.6729   0.12269   0.12098   0.0174   1.0000   0.0110
 -11.250  -0.6728   0.11776   0.11606   0.0154   1.0000   0.0111
  -9.750  -0.9719   0.02776   0.02459  -0.0153   1.0000   0.0069
  -9.500  -0.9623   0.02423   0.02066  -0.0136   1.0000   0.0071
  -9.250  -0.9453   0.02230   0.01847  -0.0125   1.0000   0.0073
  -9.000  -0.9265   0.02075   0.01670  -0.0114   1.0000   0.0074
  -8.750  -0.9091   0.01876   0.01441  -0.0101   1.0000   0.0076
  -8.500  -0.8942   0.01615   0.01140  -0.0084   1.0000   0.0081
  -8.250  -0.8730   0.01507   0.01015  -0.0074   1.0000   0.0086
  -8.000  -0.8503   0.01433   0.00933  -0.0066   1.0000   0.0091
  -7.750  -0.8275   0.01364   0.00854  -0.0058   1.0000   0.0097
  -7.500  -0.8043   0.01303   0.00784  -0.0050   1.0000   0.0104
  -7.250  -0.7807   0.01257   0.00730  -0.0043   1.0000   0.0109
  -7.000  -0.7593   0.01166   0.00626  -0.0031   1.0000   0.0122
  -6.750  -0.7364   0.01111   0.00567  -0.0022   1.0000   0.0137
  -6.500  -0.7131   0.01069   0.00520  -0.0013   1.0000   0.0151
  -6.250  -0.6900   0.01022   0.00471  -0.0003   1.0000   0.0182
  -6.000  -0.6654   0.01008   0.00459   0.0003   1.0000   0.0218
  -5.750  -0.6386   0.01032   0.00494   0.0006   1.0000   0.0265
  -5.500  -0.6115   0.01072   0.00535   0.0009   1.0000   0.0289
  -5.250  -0.5850   0.01113   0.00576   0.0013   1.0000   0.0297
  -5.000  -0.5633   0.01059   0.00520   0.0024   1.0000   0.0322
  -4.750  -0.5389   0.01071   0.00533   0.0031   1.0000   0.0336
  -4.500  -0.5153   0.01077   0.00538   0.0040   1.0000   0.0352
  -4.250  -0.4925   0.01076   0.00534   0.0050   1.0000   0.0368
  -4.000  -0.4703   0.01063   0.00519   0.0061   1.0000   0.0380
  -3.750  -0.4438   0.01081   0.00535   0.0064   0.9996   0.0391
  -3.500  -0.4096   0.00990   0.00443   0.0047   0.9975   0.0415
  -3.250  -0.3663   0.00944   0.00400   0.0012   0.9935   0.0435
  -3.000  -0.3293   0.00906   0.00364  -0.0009   0.9884   0.0446
  -2.750  -0.2905   0.00868   0.00326  -0.0033   0.9838   0.0455
  -2.500  -0.2550   0.00832   0.00290  -0.0050   0.9746   0.0462
  -2.250  -0.2194   0.00800   0.00257  -0.0067   0.9609   0.0470
  -2.000  -0.1882   0.00776   0.00227  -0.0072   0.9284   0.0479
  -1.750  -0.1646   0.00768   0.00204  -0.0059   0.8771   0.0490
  -1.500  -0.1436   0.00787   0.00187  -0.0041   0.7776   0.0503
  -1.250  -0.1304   0.00949   0.00185  -0.0017   0.2740   0.0509
  -1.000  -0.1064   0.01006   0.00186  -0.0012   0.0677   0.0515
  -0.750  -0.0803   0.00983   0.00159  -0.0008   0.0619   0.0533
  -0.500  -0.0537   0.00975   0.00150  -0.0005   0.0597   0.0547
  -0.250  -0.0269   0.00971   0.00145  -0.0003   0.0582   0.0559
   0.000   0.0000   0.00970   0.00144   0.0000   0.0570   0.0570
   0.250   0.0268   0.00971   0.00145   0.0003   0.0559   0.0582
   0.500   0.0536   0.00975   0.00150   0.0005   0.0547   0.0598
   0.750   0.0803   0.00983   0.00159   0.0008   0.0533   0.0619
   1.000   0.1064   0.01006   0.00185   0.0012   0.0514   0.0673
   1.250   0.1304   0.00950   0.00185   0.0017   0.0509   0.2720
   1.500   0.1437   0.00788   0.00187   0.0041   0.0503   0.7752
   1.750   0.1646   0.00768   0.00204   0.0059   0.0490   0.8772
   2.000   0.1882   0.00776   0.00227   0.0072   0.0479   0.9280
   2.250   0.2194   0.00800   0.00257   0.0067   0.0470   0.9609
   2.500   0.2549   0.00833   0.00290   0.0050   0.0462   0.9745
   2.750   0.2906   0.00868   0.00326   0.0033   0.0455   0.9839
   3.000   0.3294   0.00907   0.00364   0.0008   0.0446   0.9885
   3.250   0.3669   0.00943   0.00399  -0.0013   0.0434   0.9938
   3.500   0.4087   0.00989   0.00443  -0.0045   0.0415   0.9974
   3.750   0.4441   0.01082   0.00536  -0.0064   0.0391   0.9996
   4.000   0.4700   0.01063   0.00520  -0.0061   0.0380   1.0000
   4.250   0.4923   0.01074   0.00532  -0.0049   0.0368   1.0000
   4.500   0.5152   0.01075   0.00536  -0.0039   0.0351   1.0000
   4.750   0.5388   0.01069   0.00531  -0.0031   0.0336   1.0000
   5.000   0.5631   0.01059   0.00520  -0.0023   0.0322   1.0000
   5.250   0.5849   0.01113   0.00576  -0.0012   0.0297   1.0000
   5.500   0.6114   0.01072   0.00535  -0.0009   0.0289   1.0000
   5.750   0.6384   0.01034   0.00496  -0.0006   0.0266   1.0000
   6.000   0.6651   0.01009   0.00460  -0.0003   0.0219   1.0000
   6.250   0.6898   0.01023   0.00471   0.0004   0.0183   1.0000
   6.500   0.7129   0.01069   0.00520   0.0013   0.0151   1.0000
   6.750   0.7362   0.01112   0.00568   0.0022   0.0137   1.0000
   7.000   0.7592   0.01164   0.00624   0.0031   0.0123   1.0000
   7.250   0.7806   0.01256   0.00730   0.0043   0.0109   1.0000
   7.500   0.8043   0.01301   0.00781   0.0050   0.0104   1.0000
   7.750   0.8274   0.01363   0.00853   0.0058   0.0098   1.0000
   8.000   0.8503   0.01433   0.00933   0.0066   0.0092   1.0000
   8.250   0.8730   0.01507   0.01015   0.0074   0.0086   1.0000
   8.500   0.8942   0.01619   0.01144   0.0084   0.0081   1.0000
   8.750   0.9100   0.01859   0.01421   0.0100   0.0076   1.0000
   9.000   0.9275   0.02057   0.01649   0.0113   0.0074   1.0000
   9.250   0.9466   0.02207   0.01821   0.0123   0.0073   1.0000
   9.500   0.9630   0.02413   0.02055   0.0135   0.0071   1.0000
   9.750   0.9740   0.02735   0.02414   0.0151   0.0069   1.0000
  10.250   0.7765   0.07559   0.07404   0.0059   0.0076   1.0000
  10.500   0.7670   0.08183   0.08025   0.0013   0.0076   1.0000
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