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E423 (e423-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: E423 (e423-il)
Reynolds number: 1,000,000
Max Cl/Cd: 145.23 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e423-il-1000000-n5.txt
Download as CSV file: xf-e423-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250   0.2314   0.05498   0.05122  -0.1709   0.6286   0.0065
  -8.000   0.2166   0.04963   0.04582  -0.1745   0.6250   0.0064
  -7.750   0.2157   0.04478   0.04090  -0.1796   0.6210   0.0062
  -7.500   0.2236   0.03686   0.03282  -0.1919   0.6171   0.0063
  -7.250   0.2848   0.01694   0.01196  -0.2294   0.6140   0.0065
  -7.000   0.3159   0.01471   0.00950  -0.2322   0.6111   0.0066
  -6.750   0.3451   0.01374   0.00838  -0.2333   0.6079   0.0068
  -6.500   0.3734   0.01311   0.00763  -0.2339   0.6043   0.0071
  -6.250   0.4012   0.01262   0.00702  -0.2343   0.6006   0.0072
  -6.000   0.4288   0.01221   0.00649  -0.2345   0.5969   0.0075
  -5.750   0.4573   0.01184   0.00604  -0.2348   0.5944   0.0077
  -5.500   0.4857   0.01151   0.00562  -0.2350   0.5918   0.0080
  -5.250   0.5137   0.01123   0.00527  -0.2351   0.5889   0.0082
  -5.000   0.5415   0.01097   0.00493  -0.2352   0.5858   0.0085
  -4.750   0.5688   0.01073   0.00460  -0.2351   0.5825   0.0090
  -4.250   0.6237   0.01036   0.00412  -0.2350   0.5772   0.0101
  -4.000   0.6515   0.01021   0.00391  -0.2349   0.5749   0.0108
  -3.750   0.6792   0.01004   0.00371  -0.2349   0.5723   0.0120
  -3.500   0.7064   0.00992   0.00355  -0.2347   0.5694   0.0135
  -3.250   0.7334   0.00981   0.00341  -0.2345   0.5665   0.0162
  -3.000   0.7600   0.00973   0.00330  -0.2342   0.5636   0.0194
  -2.750   0.7868   0.00966   0.00321  -0.2340   0.5611   0.0234
  -2.500   0.8144   0.00957   0.00313  -0.2339   0.5592   0.0282
  -2.250   0.8417   0.00950   0.00306  -0.2338   0.5567   0.0330
  -2.000   0.8687   0.00944   0.00300  -0.2336   0.5541   0.0390
  -1.750   0.8954   0.00940   0.00296  -0.2333   0.5515   0.0458
  -1.500   0.9218   0.00938   0.00294  -0.2330   0.5489   0.0528
  -1.250   0.9478   0.00937   0.00293  -0.2326   0.5460   0.0607
  -1.000   0.9741   0.00938   0.00293  -0.2323   0.5435   0.0681
  -0.750   1.0012   0.00936   0.00293  -0.2321   0.5414   0.0755
  -0.500   1.0280   0.00936   0.00294  -0.2319   0.5392   0.0828
  -0.250   1.0545   0.00937   0.00296  -0.2316   0.5366   0.0901
   0.000   1.0806   0.00941   0.00300  -0.2312   0.5337   0.0971
   0.250   1.1064   0.00946   0.00305  -0.2308   0.5309   0.1047
   0.500   1.1317   0.00953   0.00311  -0.2303   0.5282   0.1117
   0.750   1.1579   0.00957   0.00317  -0.2300   0.5259   0.1214
   1.000   1.1843   0.00961   0.00323  -0.2297   0.5235   0.1279
   1.250   1.2103   0.00966   0.00330  -0.2294   0.5208   0.1361
   1.500   1.2358   0.00973   0.00337  -0.2289   0.5181   0.1422
   1.750   1.2609   0.00981   0.00345  -0.2284   0.5151   0.1493
   2.000   1.2852   0.00991   0.00355  -0.2278   0.5120   0.1567
   2.250   1.3099   0.01001   0.00365  -0.2272   0.5092   0.1619
   2.500   1.3358   0.01007   0.00374  -0.2269   0.5068   0.1706
   2.750   1.3610   0.01015   0.00383  -0.2264   0.5039   0.1768
   3.000   1.3858   0.01024   0.00394  -0.2259   0.5006   0.1846
   3.250   1.4098   0.01035   0.00406  -0.2253   0.4972   0.1926
   3.500   1.4331   0.01050   0.00420  -0.2245   0.4939   0.1998
   3.750   1.4578   0.01058   0.00433  -0.2240   0.4911   0.2107
   4.000   1.4822   0.01068   0.00446  -0.2234   0.4876   0.2200
   4.250   1.5056   0.01081   0.00461  -0.2227   0.4837   0.2324
   4.500   1.5277   0.01097   0.00478  -0.2217   0.4793   0.2470
   4.750   1.5505   0.01112   0.00496  -0.2209   0.4753   0.2623
   5.000   1.5741   0.01124   0.00513  -0.2203   0.4707   0.2836
   5.250   1.5963   0.01141   0.00534  -0.2194   0.4655   0.3113
   5.500   1.6170   0.01162   0.00558  -0.2182   0.4604   0.3450
   5.750   1.6403   0.01173   0.00579  -0.2176   0.4559   0.3993
   6.250   1.6803   0.01157   0.00647  -0.2153   0.4450   1.0000
   6.500   1.7020   0.01179   0.00669  -0.2143   0.4401   1.0000
   6.750   1.7225   0.01205   0.00694  -0.2132   0.4342   1.0000
   7.000   1.7402   0.01241   0.00727  -0.2116   0.4276   1.0000
   7.250   1.7604   0.01269   0.00755  -0.2104   0.4217   1.0000
   7.500   1.7773   0.01308   0.00791  -0.2087   0.4142   1.0000
   7.750   1.7959   0.01343   0.00826  -0.2074   0.4084   1.0000
   8.000   1.8128   0.01384   0.00866  -0.2057   0.4005   1.0000
   8.250   1.8282   0.01431   0.00912  -0.2038   0.3933   1.0000
   8.500   1.8447   0.01476   0.00956  -0.2022   0.3855   1.0000
   8.750   1.8578   0.01536   0.01013  -0.2000   0.3771   1.0000
   9.000   1.8716   0.01595   0.01071  -0.1980   0.3680   1.0000
   9.250   1.8838   0.01662   0.01137  -0.1958   0.3593   1.0000
   9.500   1.8934   0.01745   0.01216  -0.1932   0.3486   1.0000
   9.750   1.9048   0.01821   0.01292  -0.1911   0.3395   1.0000
  10.000   1.9132   0.01916   0.01385  -0.1885   0.3301   1.0000
  10.250   1.9202   0.02024   0.01490  -0.1859   0.3185   1.0000
  10.500   1.9266   0.02139   0.01604  -0.1833   0.3076   1.0000
  10.750   1.9300   0.02280   0.01741  -0.1804   0.2959   1.0000
  11.000   1.9316   0.02440   0.01898  -0.1775   0.2837   1.0000
  11.250   1.9353   0.02595   0.02052  -0.1750   0.2728   1.0000
  11.500   1.9366   0.02774   0.02229  -0.1724   0.2616   1.0000
  11.750   1.9365   0.02973   0.02426  -0.1698   0.2512   1.0000
  12.000   1.9376   0.03173   0.02626  -0.1675   0.2414   1.0000
  12.250   1.9368   0.03395   0.02847  -0.1652   0.2309   1.0000
  12.500   1.9347   0.03639   0.03090  -0.1630   0.2215   1.0000
  12.750   1.9339   0.03881   0.03332  -0.1610   0.2122   1.0000
  13.000   1.9329   0.04132   0.03585  -0.1592   0.2042   1.0000
  13.250   1.9287   0.04422   0.03874  -0.1573   0.1948   1.0000
  13.500   1.9292   0.04673   0.04128  -0.1558   0.1878   1.0000
  13.750   1.9252   0.04978   0.04432  -0.1542   0.1795   1.0000
  14.000   1.9252   0.05247   0.04704  -0.1529   0.1721   1.0000
  14.250   1.9201   0.05579   0.05036  -0.1516   0.1643   1.0000
  14.500   1.9196   0.05865   0.05325  -0.1505   0.1576   1.0000
  14.750   1.9164   0.06188   0.05649  -0.1494   0.1507   1.0000
  15.000   1.9160   0.06485   0.05949  -0.1485   0.1448   1.0000
  15.250   1.9120   0.06830   0.06295  -0.1476   0.1383   1.0000
  15.500   1.9124   0.07123   0.06592  -0.1470   0.1328   1.0000
  15.750   1.9091   0.07471   0.06941  -0.1463   0.1269   1.0000
  16.000   1.9090   0.07779   0.07253  -0.1458   0.1215   1.0000
  16.250   1.9057   0.08135   0.07611  -0.1453   0.1157   1.0000
  16.500   1.9051   0.08456   0.07934  -0.1449   0.1109   1.0000
  16.750   1.9030   0.08804   0.08286  -0.1446   0.1057   1.0000
  17.000   1.9008   0.09152   0.08635  -0.1444   0.1006   1.0000
  17.250   1.9002   0.09485   0.08974  -0.1443   0.0965   1.0000
  17.500   1.8984   0.09833   0.09323  -0.1442   0.0917   1.0000
  17.750   1.8969   0.10180   0.09675  -0.1443   0.0879   1.0000
  18.000   1.8965   0.10511   0.10009  -0.1443   0.0837   1.0000
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