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EPPLER 420 AIRFOIL (e420-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 420 AIRFOIL (e420-il)
Reynolds number: 200,000
Max Cl/Cd: 75.62 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e420-il-200000-n5.txt
Download as CSV file: xf-e420-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 420 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000   0.3718   0.09694   0.09118  -0.1587   0.6731   0.0300
  -9.750   0.3775   0.09505   0.08923  -0.1593   0.6656   0.0302
  -9.500   0.3843   0.09318   0.08735  -0.1597   0.6582   0.0302
  -9.250   0.3890   0.09132   0.08547  -0.1603   0.6513   0.0303
  -9.000   0.3981   0.08933   0.08343  -0.1603   0.6451   0.0304
  -8.750   0.4095   0.08724   0.08134  -0.1600   0.6386   0.0307
  -8.500   0.4183   0.08550   0.07957  -0.1600   0.6325   0.0310
  -8.250   0.4264   0.08377   0.07779  -0.1600   0.6271   0.0313
  -8.000   0.4342   0.08199   0.07601  -0.1601   0.6220   0.0316
  -7.750   0.4417   0.08027   0.07430  -0.1601   0.6167   0.0319
  -7.500   0.4483   0.07852   0.07253  -0.1600   0.6117   0.0325
  -7.250   0.4545   0.07683   0.07080  -0.1598   0.6071   0.0328
  -6.750   0.4655   0.07336   0.06737  -0.1593   0.5979   0.0331
  -6.250   0.4605   0.06822   0.06222  -0.1579   0.5905   0.0227
  -5.750   0.4664   0.06542   0.05944  -0.1554   0.5834   0.0218
  -5.500   0.4695   0.06356   0.05762  -0.1551   0.5798   0.0214
  -5.000   0.4728   0.05711   0.05118  -0.1581   0.5736   0.0196
  -4.750   0.4837   0.05487   0.04892  -0.1596   0.5705   0.0195
  -4.250   0.6077   0.02310   0.01564  -0.2181   0.5660   0.0202
  -4.000   0.6400   0.02197   0.01429  -0.2203   0.5623   0.0216
  -3.750   0.6736   0.02062   0.01252  -0.2226   0.5585   0.0230
  -3.500   0.7029   0.02005   0.01184  -0.2234   0.5549   0.0238
  -3.250   0.7329   0.01949   0.01108  -0.2242   0.5518   0.0250
  -3.000   0.7635   0.01898   0.01032  -0.2250   0.5490   0.0265
  -2.750   0.7930   0.01865   0.00990  -0.2256   0.5463   0.0284
  -2.500   0.8218   0.01831   0.00947  -0.2259   0.5435   0.0312
  -2.250   0.8502   0.01808   0.00917  -0.2262   0.5406   0.0360
  -2.000   0.8785   0.01788   0.00888  -0.2264   0.5377   0.0431
  -1.750   0.9066   0.01773   0.00868  -0.2266   0.5349   0.0525
  -1.500   0.9347   0.01765   0.00852  -0.2267   0.5323   0.0635
  -1.250   0.9630   0.01765   0.00842  -0.2269   0.5298   0.0763
  -1.000   0.9902   0.01768   0.00844  -0.2268   0.5274   0.0885
  -0.750   1.0166   0.01772   0.00847  -0.2266   0.5249   0.1003
  -0.500   1.0430   0.01777   0.00852  -0.2263   0.5225   0.1118
  -0.250   1.0695   0.01785   0.00858  -0.2261   0.5201   0.1229
   0.000   1.0958   0.01793   0.00863  -0.2259   0.5178   0.1339
   0.250   1.1223   0.01805   0.00869  -0.2256   0.5155   0.1451
   0.500   1.1491   0.01817   0.00878  -0.2255   0.5133   0.1556
   0.750   1.1767   0.01832   0.00884  -0.2255   0.5112   0.1669
   1.000   1.2029   0.01848   0.00899  -0.2253   0.5091   0.1778
   1.250   1.2276   0.01862   0.00916  -0.2247   0.5069   0.1878
   1.500   1.2523   0.01878   0.00934  -0.2242   0.5048   0.1987
   1.750   1.2772   0.01894   0.00952  -0.2238   0.5027   0.2085
   2.000   1.3018   0.01911   0.00968  -0.2232   0.5005   0.2193
   2.250   1.3264   0.01926   0.00986  -0.2228   0.4984   0.2293
   2.500   1.3515   0.01944   0.01000  -0.2223   0.4963   0.2403
   2.750   1.3776   0.01962   0.01018  -0.2222   0.4943   0.2512
   3.000   1.4050   0.01983   0.01035  -0.2223   0.4926   0.2631
   3.250   1.4301   0.02006   0.01061  -0.2220   0.4909   0.2756
   3.500   1.4520   0.02029   0.01092  -0.2210   0.4890   0.2877
   3.750   1.4737   0.02052   0.01122  -0.2201   0.4869   0.3016
   4.000   1.4953   0.02075   0.01151  -0.2191   0.4846   0.3175
   4.250   1.5171   0.02097   0.01179  -0.2182   0.4824   0.3363
   4.500   1.5393   0.02118   0.01207  -0.2174   0.4804   0.3615
   4.750   1.5623   0.02138   0.01236  -0.2168   0.4786   0.4014
   5.000   1.5822   0.02098   0.01266  -0.2154   0.4770   1.0000
   5.250   1.6078   0.02129   0.01289  -0.2153   0.4753   1.0000
   5.500   1.6348   0.02162   0.01315  -0.2154   0.4735   1.0000
   5.750   1.6489   0.02202   0.01362  -0.2131   0.4714   1.0000
   6.000   1.6648   0.02243   0.01408  -0.2112   0.4692   1.0000
   6.250   1.6822   0.02285   0.01453  -0.2097   0.4672   1.0000
   6.500   1.7001   0.02326   0.01498  -0.2082   0.4651   1.0000
   6.750   1.7185   0.02365   0.01539  -0.2069   0.4629   1.0000
   7.000   1.7377   0.02402   0.01576  -0.2056   0.4608   1.0000
   7.250   1.7586   0.02438   0.01611  -0.2048   0.4590   1.0000
   7.500   1.7827   0.02473   0.01644  -0.2045   0.4573   1.0000
   7.750   1.8048   0.02514   0.01685  -0.2039   0.4554   1.0000
   8.000   1.8111   0.02583   0.01767  -0.2007   0.4530   1.0000
   8.250   1.8201   0.02650   0.01844  -0.1980   0.4504   1.0000
   8.500   1.8314   0.02714   0.01917  -0.1957   0.4478   1.0000
   8.750   1.8448   0.02771   0.01979  -0.1938   0.4453   1.0000
   9.000   1.8603   0.02823   0.02034  -0.1923   0.4429   1.0000
   9.250   1.8795   0.02864   0.02075  -0.1914   0.4408   1.0000
   9.500   1.9051   0.02891   0.02099  -0.1914   0.4387   1.0000
   9.750   1.8993   0.03023   0.02250  -0.1870   0.4356   1.0000
  10.000   1.8986   0.03148   0.02389  -0.1835   0.4322   1.0000
  10.250   1.9037   0.03254   0.02504  -0.1809   0.4290   1.0000
  10.500   1.9138   0.03337   0.02593  -0.1791   0.4261   1.0000
  10.750   1.9313   0.03387   0.02644  -0.1781   0.4235   1.0000
  11.000   1.9407   0.03484   0.02747  -0.1763   0.4205   1.0000
  11.250   1.9235   0.03743   0.03027  -0.1719   0.4161   1.0000
  11.500   1.9194   0.03940   0.03235  -0.1691   0.4120   1.0000
  11.750   1.9270   0.04062   0.03363  -0.1675   0.4087   1.0000
  12.000   1.9484   0.04088   0.03387  -0.1671   0.4059   1.0000
  12.250   1.9171   0.04534   0.03858  -0.1628   0.4004   1.0000
  12.500   1.9023   0.04881   0.04219  -0.1602   0.3951   1.0000
  12.750   1.9145   0.04987   0.04326  -0.1593   0.3915   1.0000
  13.000   1.9034   0.05330   0.04681  -0.1574   0.3865   1.0000
  13.250   1.8650   0.05993   0.05363  -0.1548   0.3787   1.0000
  13.500   1.8848   0.06025   0.05395  -0.1544   0.3753   1.0000
  13.750   1.8222   0.07054   0.06448  -0.1521   0.3645   1.0000
  14.000   1.8396   0.07114   0.06509  -0.1517   0.3605   1.0000
  14.500   1.8089   0.08102   0.07516  -0.1503   0.3454   1.0000
  15.000   1.7919   0.08945   0.08373  -0.1496   0.3304   1.0000
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