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E374 (e374-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: E374 (e374-il)
Reynolds number: 50,000
Max Cl/Cd: 34.15 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e374-il-50000.txt
Download as CSV file: xf-e374-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E374                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4142   0.10747   0.10070  -0.0187   1.0000   0.2541
  -9.000  -0.4308   0.10599   0.09938  -0.0199   1.0000   0.2647
  -8.750  -0.4210   0.10232   0.09573  -0.0191   1.0000   0.2778
  -8.500  -0.4110   0.09838   0.09183  -0.0183   1.0000   0.2908
  -8.250  -0.4052   0.09501   0.08852  -0.0176   1.0000   0.3041
  -8.000  -0.4094   0.09252   0.08612  -0.0169   1.0000   0.3202
  -7.750  -0.3980   0.08878   0.08244  -0.0152   1.0000   0.3406
  -7.500  -0.3929   0.08582   0.07953  -0.0138   1.0000   0.3597
  -7.250  -0.4167   0.08479   0.07870  -0.0117   1.0000   0.3795
  -6.000  -0.5296   0.05557   0.04901  -0.0293   1.0000   0.1330
  -5.750  -0.5344   0.05151   0.04442  -0.0269   1.0000   0.1206
  -5.500  -0.5297   0.04827   0.04101  -0.0245   1.0000   0.1167
  -5.250  -0.5255   0.04503   0.03736  -0.0221   1.0000   0.1132
  -5.000  -0.5181   0.04217   0.03405  -0.0199   1.0000   0.1124
  -4.750  -0.5072   0.03968   0.03119  -0.0178   1.0000   0.1139
  -4.500  -0.4934   0.03715   0.02820  -0.0159   1.0000   0.1147
  -4.250  -0.4766   0.03472   0.02529  -0.0141   1.0000   0.1159
  -4.000  -0.4582   0.03289   0.02283  -0.0124   1.0000   0.1214
  -3.750  -0.4392   0.03109   0.02098  -0.0112   1.0000   0.1318
  -3.500  -0.4180   0.02935   0.01903  -0.0099   1.0000   0.1436
  -3.250  -0.3970   0.02802   0.01750  -0.0085   1.0000   0.1644
  -3.000  -0.1682   0.02262   0.01536  -0.0324   1.0000   1.0000
  -2.750  -0.1819   0.02247   0.01499  -0.0280   1.0000   1.0000
  -2.500  -0.1888   0.02240   0.01469  -0.0241   1.0000   1.0000
  -2.250  -0.1905   0.02240   0.01443  -0.0208   1.0000   1.0000
  -2.000  -0.1882   0.02248   0.01423  -0.0180   1.0000   1.0000
  -1.750  -0.1828   0.02262   0.01409  -0.0156   1.0000   1.0000
  -1.500  -0.1753   0.02281   0.01401  -0.0135   1.0000   1.0000
  -1.250  -0.1661   0.02306   0.01399  -0.0116   1.0000   1.0000
  -1.000  -0.1556   0.02335   0.01404  -0.0099   1.0000   1.0000
  -0.750  -0.1419   0.02371   0.01413  -0.0088   0.9994   1.0000
  -0.500  -0.1041   0.02452   0.01465  -0.0123   0.9907   1.0000
  -0.250  -0.0666   0.02539   0.01527  -0.0156   0.9820   1.0000
   0.000  -0.0338   0.02613   0.01578  -0.0181   0.9732   1.0000
   0.250  -0.0034   0.02686   0.01633  -0.0200   0.9647   1.0000
   0.500   0.0333   0.02780   0.01709  -0.0230   0.9564   1.0000
   0.750   0.0570   0.02843   0.01758  -0.0237   0.9475   1.0000
   1.000   0.0869   0.02926   0.01829  -0.0254   0.9392   1.0000
   1.250   0.1162   0.03009   0.01903  -0.0270   0.9308   1.0000
   1.500   0.1394   0.03086   0.01972  -0.0275   0.9221   1.0000
   1.750   0.1745   0.03187   0.02065  -0.0300   0.9138   1.0000
   2.000   0.1919   0.03260   0.02134  -0.0295   0.9048   1.0000
   2.250   0.2183   0.03353   0.02224  -0.0306   0.8962   1.0000
   2.500   0.2484   0.03451   0.02321  -0.0321   0.8869   1.0000
   2.750   0.2655   0.03537   0.02406  -0.0316   0.8775   1.0000
   3.000   0.2928   0.03639   0.02509  -0.0327   0.8678   1.0000
   3.250   0.3246   0.03744   0.02617  -0.0344   0.8576   1.0000
   3.500   0.3401   0.03839   0.02715  -0.0336   0.8468   1.0000
   3.750   0.3623   0.03943   0.02826  -0.0338   0.8357   1.0000
   4.000   0.3887   0.04050   0.02939  -0.0346   0.8238   1.0000
   4.250   0.4170   0.04158   0.03055  -0.0355   0.8112   1.0000
   4.500   0.4452   0.04263   0.03171  -0.0364   0.7978   1.0000
   4.750   0.4710   0.04366   0.03289  -0.0367   0.7835   1.0000
   5.000   0.4938   0.04469   0.03404  -0.0366   0.7681   1.0000
   5.250   0.5160   0.04572   0.03519  -0.0363   0.7519   1.0000
   5.500   0.5410   0.04668   0.03634  -0.0363   0.7346   1.0000
   5.750   0.5761   0.04736   0.03724  -0.0370   0.7163   1.0000
   6.000   0.6083   0.04797   0.03806  -0.0371   0.6970   1.0000
   6.250   0.6308   0.04869   0.03898  -0.0361   0.6760   1.0000
   6.500   0.6766   0.04836   0.03902  -0.0365   0.6542   1.0000
   6.750   0.7225   0.04739   0.03842  -0.0362   0.6299   1.0000
   7.000   0.7710   0.04560   0.03705  -0.0351   0.6034   1.0000
   7.250   0.8782   0.03784   0.03013  -0.0347   0.5703   1.0000
   7.500   0.9311   0.03278   0.02553  -0.0307   0.5238   1.0000
   7.750   0.9621   0.02882   0.02160  -0.0248   0.4532   1.0000
   8.000   0.9623   0.02818   0.02028  -0.0176   0.3595   1.0000
   8.250   0.9513   0.03005   0.02122  -0.0113   0.2777   1.0000
   8.500   0.9440   0.03263   0.02308  -0.0065   0.2156   1.0000
   8.750   0.9518   0.03544   0.02536  -0.0036   0.1670   1.0000
   9.000   0.9785   0.03842   0.02808  -0.0029   0.1333   1.0000
   9.250   1.0159   0.04177   0.03148  -0.0034   0.1151   1.0000
   9.500   1.0382   0.04488   0.03485  -0.0025   0.1046   1.0000
   9.750   1.0682   0.04889   0.03893  -0.0028   0.0982   1.0000
  10.000   1.0780   0.05265   0.04318  -0.0006   0.0962   1.0000
  10.250   1.0773   0.05601   0.04707   0.0024   0.0944   1.0000
  10.500   1.0723   0.05941   0.05090   0.0054   0.0926   1.0000
  10.750   1.0646   0.06293   0.05478   0.0082   0.0917   1.0000
  11.000   1.0512   0.06640   0.05855   0.0111   0.0911   1.0000
  11.250   1.0323   0.06989   0.06228   0.0140   0.0913   1.0000
  11.500   1.0105   0.07378   0.06639   0.0160   0.0921   1.0000
  11.750   0.9874   0.07824   0.07104   0.0167   0.0934   1.0000
  12.000   0.9634   0.08325   0.07619   0.0163   0.0945   1.0000
  12.250   0.9424   0.08883   0.08187   0.0150   0.0958   1.0000
  12.500   0.9243   0.09490   0.08801   0.0132   0.0968   1.0000
  12.750   0.9138   0.10104   0.09419   0.0114   0.0975   1.0000
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