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E423 (e423-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E423 (e423-il)
Reynolds number: 100,000
Max Cl/Cd: 51.9 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e423-il-100000-n5.txt
Download as CSV file: xf-e423-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250   0.2438   0.10172   0.09599  -0.1370   0.8342   0.0452
  -9.000   0.2569   0.09932   0.09354  -0.1405   0.8240   0.0456
  -8.750   0.2754   0.09652   0.09064  -0.1455   0.8163   0.0457
  -8.500   0.2950   0.09303   0.08712  -0.1464   0.8075   0.0464
  -8.250   0.3162   0.09022   0.08423  -0.1492   0.7999   0.0484
  -8.000   0.3287   0.08806   0.08202  -0.1509   0.7910   0.0497
  -7.750   0.3411   0.08591   0.07982  -0.1533   0.7830   0.0510
  -7.500   0.3445   0.08457   0.07847  -0.1553   0.7747   0.0518
  -7.250   0.3626   0.08156   0.07543  -0.1553   0.7680   0.0537
  -7.000   0.3768   0.07934   0.07314  -0.1570   0.7621   0.0544
  -6.750   0.3827   0.07770   0.07152  -0.1567   0.7549   0.0556
  -6.500   0.3885   0.07592   0.06973  -0.1568   0.7482   0.0562
  -6.250   0.3985   0.07386   0.06761  -0.1578   0.7430   0.0561
  -6.000   0.3971   0.07254   0.06634  -0.1560   0.7359   0.0556
  -5.500   0.4004   0.06620   0.05991  -0.1593   0.7255   0.0350
  -5.250   0.4079   0.06446   0.05820  -0.1591   0.7202   0.0346
  -5.000   0.4153   0.06251   0.05626  -0.1595   0.7147   0.0342
  -4.750   0.4287   0.06013   0.05384  -0.1616   0.7100   0.0337
  -4.500   0.4490   0.05712   0.05075  -0.1658   0.7063   0.0334
  -4.250   0.4586   0.05477   0.04843  -0.1674   0.7008   0.0336
  -4.000   0.4824   0.04999   0.04358  -0.1750   0.6960   0.0351
  -3.750   0.5055   0.04889   0.04244  -0.1764   0.6921   0.0370
  -3.500   0.5494   0.04372   0.03706  -0.1869   0.6889   0.0385
  -3.250   0.6034   0.03693   0.02997  -0.2006   0.6850   0.0421
  -2.750   0.7164   0.02560   0.01699  -0.2226   0.6769   0.0601
  -2.500   0.7490   0.02494   0.01605  -0.2241   0.6735   0.0681
  -2.250   0.7833   0.02438   0.01518  -0.2256   0.6706   0.0768
  -2.000   0.8088   0.02432   0.01507  -0.2254   0.6667   0.0840
  -1.750   0.8316   0.02423   0.01492  -0.2247   0.6622   0.0913
  -1.500   0.8594   0.02396   0.01445  -0.2249   0.6583   0.1005
  -1.250   0.8892   0.02382   0.01411  -0.2254   0.6551   0.1109
  -1.000   0.9202   0.02380   0.01403  -0.2260   0.6523   0.1207
  -0.750   0.9450   0.02382   0.01396  -0.2256   0.6488   0.1307
  -0.500   0.9653   0.02399   0.01406  -0.2244   0.6443   0.1408
  -0.250   0.9894   0.02409   0.01416  -0.2238   0.6405   0.1501
   0.000   1.0177   0.02408   0.01399  -0.2239   0.6373   0.1619
   0.250   1.0482   0.02409   0.01392  -0.2245   0.6347   0.1730
   0.500   1.0745   0.02418   0.01395  -0.2243   0.6315   0.1834
   0.750   1.0905   0.02453   0.01432  -0.2223   0.6270   0.1929
   1.000   1.1123   0.02473   0.01453  -0.2214   0.6231   0.2025
   1.250   1.1388   0.02486   0.01456  -0.2212   0.6200   0.2148
   1.500   1.1688   0.02489   0.01457  -0.2217   0.6172   0.2265
   1.750   1.2008   0.02492   0.01451  -0.2225   0.6148   0.2399
   2.000   1.2096   0.02553   0.01519  -0.2193   0.6098   0.2499
   2.250   1.2278   0.02589   0.01561  -0.2177   0.6058   0.2611
   2.500   1.2517   0.02611   0.01583  -0.2171   0.6025   0.2757
   2.750   1.2808   0.02618   0.01588  -0.2174   0.5997   0.2931
   3.000   1.3138   0.02620   0.01585  -0.2184   0.5974   0.3159
   3.250   1.3193   0.02696   0.01678  -0.2147   0.5925   0.3323
   3.500   1.3326   0.02751   0.01744  -0.2125   0.5882   0.3569
   3.750   1.3554   0.02772   0.01778  -0.2118   0.5847   0.4036
   4.000   1.3786   0.02711   0.01789  -0.2109   0.5819   1.0000
   4.250   1.4127   0.02722   0.01782  -0.2120   0.5796   1.0000
   4.500   1.4057   0.02844   0.01916  -0.2064   0.5742   1.0000
   4.750   1.4124   0.02927   0.02000  -0.2030   0.5695   1.0000
   5.000   1.4345   0.02964   0.02032  -0.2022   0.5661   1.0000
   5.250   1.4659   0.02976   0.02034  -0.2029   0.5635   1.0000
   5.500   1.4937   0.03002   0.02054  -0.2030   0.5607   1.0000
   5.750   1.4620   0.03225   0.02297  -0.1940   0.5532   1.0000
   6.000   1.4786   0.03283   0.02357  -0.1924   0.5493   1.0000
   6.250   1.5083   0.03289   0.02358  -0.1927   0.5466   1.0000
   6.500   1.5471   0.03265   0.02325  -0.1944   0.5445   1.0000
   6.750   1.4877   0.03668   0.02756  -0.1827   0.5343   1.0000
   7.000   1.5105   0.03698   0.02784  -0.1821   0.5309   1.0000
   7.250   1.5461   0.03659   0.02743  -0.1830   0.5286   1.0000
   7.750   1.5091   0.04214   0.03321  -0.1728   0.5137   1.0000
   8.000   1.5465   0.04135   0.03239  -0.1736   0.5117   1.0000
   8.250   1.5910   0.04020   0.03121  -0.1752   0.5101   1.0000
   8.500   1.5145   0.04767   0.03891  -0.1658   0.4956   1.0000
   8.750   1.5542   0.04642   0.03765  -0.1664   0.4942   1.0000
   9.250   1.5120   0.05475   0.04619  -0.1596   0.4752   1.0000
   9.750   1.5179   0.05903   0.05059  -0.1565   0.4617   1.0000
  10.000   1.5567   0.05731   0.04889  -0.1565   0.4606   1.0000
  10.500   1.5483   0.06324   0.05498  -0.1531   0.4445   1.0000
  11.000   1.5460   0.06880   0.06069  -0.1504   0.4286   1.0000
  11.500   1.5345   0.07587   0.06793  -0.1480   0.4104   1.0000
  12.000   1.5523   0.07917   0.07137  -0.1463   0.3971   1.0000
  12.500   1.5597   0.08398   0.07634  -0.1447   0.3815   1.0000
  12.750   1.5391   0.08999   0.08246  -0.1441   0.3687   1.0000
  13.000   1.5694   0.08855   0.08108  -0.1434   0.3660   1.0000
  13.250   1.6033   0.08661   0.07916  -0.1426   0.3636   1.0000
  13.500   1.5812   0.09289   0.08556  -0.1422   0.3506   1.0000
  13.750   1.6116   0.09138   0.08410  -0.1414   0.3472   1.0000
  14.000   1.5947   0.09702   0.08986  -0.1412   0.3351   1.0000
  14.250   1.6237   0.09566   0.08853  -0.1404   0.3311   1.0000
  14.500   1.6100   0.10089   0.09387  -0.1404   0.3196   1.0000
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