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E423 (e423-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E423 (e423-il)
Reynolds number: 200,000
Max Cl/Cd: 84.29 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e423-il-200000-n5.txt
Download as CSV file: xf-e423-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750   0.3176   0.09387   0.08891  -0.1629   0.7885   0.0265
  -9.500   0.3338   0.09121   0.08617  -0.1636   0.7774   0.0269
  -9.250   0.3435   0.08918   0.08407  -0.1644   0.7663   0.0269
  -9.000   0.3540   0.08715   0.08198  -0.1649   0.7569   0.0272
  -8.750   0.3629   0.08520   0.07998  -0.1653   0.7478   0.0275
  -8.500   0.3716   0.08325   0.07798  -0.1658   0.7402   0.0276
  -8.000   0.3870   0.07938   0.07403  -0.1664   0.7258   0.0277
  -7.500   0.3931   0.07394   0.06855  -0.1667   0.7130   0.0192
  -7.250   0.3999   0.07201   0.06658  -0.1667   0.7071   0.0189
  -7.000   0.4065   0.07030   0.06488  -0.1664   0.7015   0.0184
  -6.750   0.4101   0.06837   0.06295  -0.1660   0.6959   0.0181
  -6.500   0.4124   0.06638   0.06096  -0.1655   0.6910   0.0181
  -6.250   0.4140   0.06457   0.05914  -0.1648   0.6866   0.0179
  -6.000   0.4148   0.06268   0.05728  -0.1642   0.6817   0.0177
  -5.750   0.4195   0.06052   0.05513  -0.1647   0.6768   0.0178
  -5.500   0.4264   0.05811   0.05270  -0.1659   0.6726   0.0178
  -5.250   0.4363   0.05539   0.04994  -0.1682   0.6688   0.0185
  -4.750   0.5312   0.02238   0.01568  -0.2238   0.6616   0.0208
  -4.500   0.5671   0.02019   0.01298  -0.2275   0.6578   0.0222
  -4.250   0.5986   0.01919   0.01172  -0.2291   0.6542   0.0237
  -4.000   0.6304   0.01842   0.01064  -0.2304   0.6509   0.0263
  -3.750   0.6580   0.01796   0.01009  -0.2308   0.6469   0.0294
  -3.500   0.6864   0.01751   0.00952  -0.2312   0.6430   0.0334
  -3.250   0.7152   0.01714   0.00901  -0.2316   0.6396   0.0383
  -3.000   0.7443   0.01687   0.00860  -0.2320   0.6364   0.0442
  -2.750   0.7739   0.01669   0.00826  -0.2325   0.6335   0.0507
  -2.500   0.8009   0.01654   0.00807  -0.2324   0.6300   0.0575
  -2.250   0.8277   0.01642   0.00791  -0.2323   0.6263   0.0644
  -2.000   0.8550   0.01632   0.00776  -0.2323   0.6230   0.0715
  -1.750   0.8828   0.01624   0.00760  -0.2323   0.6200   0.0792
  -1.500   0.9113   0.01620   0.00745  -0.2324   0.6170   0.0878
  -1.250   0.9397   0.01622   0.00739  -0.2326   0.6142   0.0967
  -1.000   0.9651   0.01622   0.00742  -0.2321   0.6108   0.1052
  -0.750   0.9912   0.01624   0.00741  -0.2318   0.6075   0.1143
  -0.500   1.0175   0.01631   0.00744  -0.2315   0.6044   0.1240
  -0.250   1.0444   0.01636   0.00747  -0.2314   0.6014   0.1329
   0.000   1.0723   0.01644   0.00743  -0.2314   0.5986   0.1427
   0.250   1.0996   0.01652   0.00751  -0.2313   0.5959   0.1515
   0.500   1.1240   0.01661   0.00759  -0.2307   0.5927   0.1604
   0.750   1.1490   0.01668   0.00771  -0.2302   0.5895   0.1690
   1.000   1.1743   0.01678   0.00776  -0.2298   0.5863   0.1780
   1.250   1.2005   0.01685   0.00785  -0.2295   0.5833   0.1869
   1.500   1.2281   0.01696   0.00790  -0.2295   0.5808   0.1967
   1.750   1.2547   0.01708   0.00803  -0.2294   0.5781   0.2064
   2.000   1.2772   0.01721   0.00821  -0.2284   0.5748   0.2162
   2.250   1.3006   0.01733   0.00839  -0.2277   0.5714   0.2268
   2.500   1.3250   0.01745   0.00855  -0.2271   0.5682   0.2379
   2.750   1.3504   0.01759   0.00868  -0.2268   0.5654   0.2512
   3.000   1.3775   0.01771   0.00880  -0.2268   0.5628   0.2668
   3.250   1.4017   0.01788   0.00902  -0.2262   0.5598   0.2835
   3.500   1.4227   0.01805   0.00930  -0.2251   0.5564   0.3042
   3.750   1.4451   0.01821   0.00956  -0.2242   0.5530   0.3324
   4.000   1.4683   0.01833   0.00978  -0.2235   0.5497   0.3750
   4.250   1.4891   0.01778   0.01000  -0.2222   0.5469   0.9314
   4.500   1.5163   0.01799   0.01011  -0.2222   0.5443   1.0000
   4.750   1.5339   0.01829   0.01045  -0.2204   0.5407   1.0000
   5.000   1.5517   0.01856   0.01077  -0.2187   0.5369   1.0000
   5.250   1.5711   0.01882   0.01102  -0.2172   0.5334   1.0000
   5.500   1.5930   0.01906   0.01123  -0.2162   0.5302   1.0000
   5.750   1.6186   0.01929   0.01139  -0.2160   0.5273   1.0000
   6.000   1.6322   0.01964   0.01182  -0.2135   0.5233   1.0000
   6.250   1.6473   0.01999   0.01224  -0.2114   0.5191   1.0000
   6.500   1.6647   0.02029   0.01255  -0.2096   0.5150   1.0000
   6.750   1.6865   0.02053   0.01275  -0.2087   0.5114   1.0000
   7.000   1.7016   0.02091   0.01318  -0.2066   0.5072   1.0000
   7.250   1.7132   0.02136   0.01372  -0.2040   0.5022   1.0000
   7.500   1.7287   0.02173   0.01411  -0.2020   0.4977   1.0000
   7.750   1.7493   0.02200   0.01434  -0.2010   0.4938   1.0000
   8.000   1.7581   0.02260   0.01507  -0.1980   0.4886   1.0000
   8.250   1.7692   0.02314   0.01568  -0.1955   0.4833   1.0000
   8.500   1.7854   0.02355   0.01608  -0.1938   0.4787   1.0000
   8.750   1.7965   0.02417   0.01676  -0.1914   0.4736   1.0000
   9.000   1.8048   0.02491   0.01760  -0.1887   0.4678   1.0000
   9.250   1.8181   0.02547   0.01816  -0.1867   0.4624   1.0000
   9.500   1.8264   0.02630   0.01907  -0.1841   0.4567   1.0000
   9.750   1.8333   0.02722   0.02006  -0.1814   0.4503   1.0000
  10.000   1.8457   0.02790   0.02075  -0.1795   0.4446   1.0000
  10.250   1.8480   0.02918   0.02215  -0.1765   0.4376   1.0000
  10.500   1.8553   0.03023   0.02323  -0.1742   0.4310   1.0000
  10.750   1.8602   0.03149   0.02456  -0.1717   0.4242   1.0000
  11.000   1.8634   0.03293   0.02606  -0.1692   0.4167   1.0000
  11.250   1.8683   0.03431   0.02749  -0.1669   0.4094   1.0000
  11.500   1.8689   0.03610   0.02936  -0.1644   0.4012   1.0000
  11.750   1.8723   0.03774   0.03103  -0.1623   0.3933   1.0000
  12.000   1.8718   0.03980   0.03316  -0.1600   0.3846   1.0000
  12.250   1.8723   0.04184   0.03524  -0.1579   0.3758   1.0000
  12.500   1.8715   0.04409   0.03754  -0.1559   0.3665   1.0000
  12.750   1.8697   0.04655   0.04006  -0.1540   0.3571   1.0000
  13.000   1.8687   0.04895   0.04245  -0.1522   0.3476   1.0000
  13.250   1.8649   0.05180   0.04538  -0.1505   0.3374   1.0000
  13.500   1.8618   0.05463   0.04824  -0.1489   0.3272   1.0000
  13.750   1.8581   0.05756   0.05118  -0.1474   0.3167   1.0000
  14.000   1.8538   0.06073   0.05440  -0.1461   0.3061   1.0000
  14.250   1.8496   0.06391   0.05761  -0.1449   0.2958   1.0000
  14.500   1.8444   0.06725   0.06095  -0.1437   0.2853   1.0000
  14.750   1.8402   0.07063   0.06438  -0.1427   0.2747   1.0000
  15.000   1.8357   0.07407   0.06783  -0.1419   0.2649   1.0000
  15.250   1.8301   0.07768   0.07145  -0.1411   0.2548   1.0000
  15.500   1.8267   0.08113   0.07496  -0.1405   0.2451   1.0000
  15.750   1.8219   0.08477   0.07861  -0.1399   0.2361   1.0000
  16.000   1.8179   0.08837   0.08225  -0.1395   0.2268   1.0000
  16.250   1.8145   0.09193   0.08585  -0.1392   0.2182   1.0000
  16.500   1.8098   0.09568   0.08962  -0.1390   0.2096   1.0000
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