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E423 (e423-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: E423 (e423-il)
Reynolds number: 500,000
Max Cl/Cd: 120.55 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e423-il-500000-n5.txt
Download as CSV file: xf-e423-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E423                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000   0.3319   0.09186   0.08759  -0.1660   0.7036   0.0148
  -9.750   0.3399   0.08982   0.08553  -0.1664   0.6969   0.0150
  -6.250   0.3787   0.01900   0.01342  -0.2251   0.6325   0.0097
  -6.000   0.4119   0.01684   0.01097  -0.2284   0.6292   0.0101
  -5.750   0.4420   0.01580   0.00973  -0.2298   0.6256   0.0104
  -5.500   0.4711   0.01507   0.00881  -0.2306   0.6220   0.0107
  -5.250   0.5000   0.01438   0.00796  -0.2314   0.6183   0.0112
  -5.000   0.5284   0.01392   0.00734  -0.2319   0.6148   0.0117
  -4.750   0.5572   0.01349   0.00682  -0.2323   0.6118   0.0123
  -4.500   0.5857   0.01314   0.00636  -0.2326   0.6087   0.0131
  -4.250   0.6140   0.01281   0.00594  -0.2328   0.6056   0.0141
  -4.000   0.6419   0.01257   0.00561  -0.2329   0.6023   0.0160
  -3.750   0.6696   0.01236   0.00531  -0.2330   0.5992   0.0182
  -3.500   0.6974   0.01218   0.00507  -0.2330   0.5962   0.0214
  -3.250   0.7254   0.01201   0.00486  -0.2331   0.5935   0.0256
  -3.000   0.7533   0.01187   0.00469  -0.2331   0.5908   0.0299
  -2.750   0.7807   0.01177   0.00455  -0.2330   0.5878   0.0348
  -2.500   0.8079   0.01169   0.00443  -0.2329   0.5848   0.0403
  -2.250   0.8348   0.01164   0.00434  -0.2327   0.5818   0.0460
  -1.750   0.8894   0.01154   0.00421  -0.2325   0.5769   0.0596
  -1.500   0.9166   0.01150   0.00417  -0.2323   0.5742   0.0670
  -1.250   0.9433   0.01147   0.00414  -0.2321   0.5713   0.0747
  -1.000   0.9696   0.01146   0.00413  -0.2318   0.5684   0.0824
  -0.750   0.9958   0.01148   0.00412  -0.2314   0.5658   0.0901
  -0.500   1.0218   0.01153   0.00413  -0.2310   0.5632   0.0978
  -0.250   1.0479   0.01156   0.00417  -0.2307   0.5607   0.1060
   0.000   1.0740   0.01158   0.00419  -0.2303   0.5581   0.1137
   0.250   1.0998   0.01160   0.00424  -0.2299   0.5554   0.1229
   0.500   1.1254   0.01165   0.00429  -0.2295   0.5527   0.1309
   0.750   1.1505   0.01171   0.00435  -0.2289   0.5498   0.1390
   1.000   1.1753   0.01179   0.00440  -0.2283   0.5470   0.1457
   1.250   1.2002   0.01189   0.00449  -0.2278   0.5444   0.1539
   1.500   1.2256   0.01195   0.00457  -0.2273   0.5421   0.1607
   1.750   1.2509   0.01201   0.00467  -0.2269   0.5394   0.1687
   2.000   1.2756   0.01209   0.00476  -0.2263   0.5364   0.1762
   2.250   1.3001   0.01219   0.00487  -0.2257   0.5334   0.1838
   2.500   1.3243   0.01230   0.00498  -0.2251   0.5306   0.1922
   2.750   1.3482   0.01243   0.00510  -0.2244   0.5279   0.2004
   3.000   1.3726   0.01254   0.00524  -0.2238   0.5252   0.2100
   3.250   1.3968   0.01263   0.00539  -0.2232   0.5222   0.2201
   3.500   1.4206   0.01274   0.00554  -0.2225   0.5192   0.2313
   3.750   1.4439   0.01287   0.00570  -0.2217   0.5159   0.2450
   4.000   1.4668   0.01301   0.00587  -0.2209   0.5129   0.2607
   4.250   1.4894   0.01318   0.00605  -0.2201   0.5099   0.2789
   4.500   1.5131   0.01328   0.00625  -0.2194   0.5068   0.3045
   4.750   1.5359   0.01340   0.00646  -0.2187   0.5033   0.3389
   5.000   1.5580   0.01352   0.00669  -0.2178   0.4995   0.3899
   5.500   1.5985   0.01326   0.00724  -0.2153   0.4921   1.0000
   5.750   1.6202   0.01346   0.00745  -0.2144   0.4880   1.0000
   6.000   1.6406   0.01369   0.00770  -0.2131   0.4833   1.0000
   6.250   1.6591   0.01399   0.00796  -0.2116   0.4787   1.0000
   6.500   1.6790   0.01425   0.00823  -0.2103   0.4744   1.0000
   6.750   1.6989   0.01451   0.00852  -0.2091   0.4694   1.0000
   7.000   1.7172   0.01483   0.00884  -0.2076   0.4645   1.0000
   7.250   1.7341   0.01521   0.00920  -0.2059   0.4597   1.0000
   7.500   1.7532   0.01551   0.00954  -0.2046   0.4544   1.0000
   7.750   1.7701   0.01591   0.00994  -0.2029   0.4488   1.0000
   8.000   1.7849   0.01637   0.01040  -0.2010   0.4432   1.0000
   8.250   1.8022   0.01677   0.01084  -0.1994   0.4371   1.0000
   8.500   1.8159   0.01732   0.01138  -0.1974   0.4306   1.0000
   8.750   1.8307   0.01784   0.01193  -0.1955   0.4248   1.0000
   9.000   1.8446   0.01842   0.01253  -0.1936   0.4177   1.0000
   9.250   1.8554   0.01915   0.01325  -0.1912   0.4109   1.0000
   9.500   1.8686   0.01981   0.01395  -0.1893   0.4033   1.0000
   9.750   1.8768   0.02074   0.01486  -0.1867   0.3958   1.0000
  10.000   1.8885   0.02153   0.01569  -0.1847   0.3877   1.0000
  10.250   1.8944   0.02267   0.01682  -0.1820   0.3794   1.0000
  10.500   1.9037   0.02368   0.01786  -0.1799   0.3703   1.0000
  10.750   1.9085   0.02501   0.01919  -0.1773   0.3618   1.0000
  11.000   1.9141   0.02636   0.02056  -0.1750   0.3522   1.0000
  11.250   1.9176   0.02792   0.02213  -0.1725   0.3427   1.0000
  11.500   1.9173   0.02983   0.02404  -0.1698   0.3323   1.0000
  11.750   1.9206   0.03158   0.02581  -0.1676   0.3219   1.0000
  12.000   1.9191   0.03378   0.02801  -0.1652   0.3110   1.0000
  12.250   1.9149   0.03632   0.03054  -0.1627   0.2998   1.0000
  12.500   1.9142   0.03868   0.03292  -0.1606   0.2890   1.0000
  12.750   1.9106   0.04137   0.03561  -0.1585   0.2782   1.0000
  13.000   1.9044   0.04442   0.03866  -0.1565   0.2676   1.0000
  13.250   1.9009   0.04730   0.04156  -0.1547   0.2571   1.0000
  13.500   1.8967   0.05035   0.04462  -0.1531   0.2472   1.0000
  13.750   1.8898   0.05377   0.04804  -0.1515   0.2377   1.0000
  14.000   1.8865   0.05689   0.05119  -0.1502   0.2280   1.0000
  14.250   1.8816   0.06025   0.05456  -0.1489   0.2193   1.0000
  14.500   1.8772   0.06364   0.05797  -0.1478   0.2104   1.0000
  14.750   1.8743   0.06690   0.06125  -0.1469   0.2022   1.0000
  15.250   1.8674   0.07373   0.06813  -0.1453   0.1861   1.0000
  15.500   1.8612   0.07760   0.07201  -0.1446   0.1785   1.0000
  15.750   1.8601   0.08083   0.07528  -0.1441   0.1707   1.0000
  16.000   1.8554   0.08458   0.07905  -0.1436   0.1640   1.0000
  16.250   1.8544   0.08788   0.08239  -0.1433   0.1569   1.0000
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