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E374 (e374-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E374 (e374-il)
Reynolds number: 100,000
Max Cl/Cd: 53.8 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e374-il-100000.txt
Download as CSV file: xf-e374-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4265   0.10137   0.09654  -0.0299   1.0000   0.1034
  -9.250  -0.4433   0.09818   0.09346  -0.0347   1.0000   0.1070
  -9.000  -0.4751   0.09452   0.08996  -0.0423   1.0000   0.1078
  -8.750  -0.4334   0.09032   0.08569  -0.0342   1.0000   0.1122
  -8.500  -0.4341   0.08702   0.08242  -0.0350   1.0000   0.1171
  -8.250  -0.4608   0.08329   0.07886  -0.0398   1.0000   0.1205
  -8.000  -0.5026   0.08063   0.07621  -0.0428   1.0000   0.1217
  -7.750  -0.4728   0.07612   0.07183  -0.0389   1.0000   0.1255
  -7.500  -0.4740   0.07327   0.06900  -0.0378   1.0000   0.1296
  -7.250  -0.5223   0.07166   0.06724  -0.0389   1.0000   0.1357
  -7.000  -0.5063   0.06695   0.06274  -0.0365   1.0000   0.1385
  -6.750  -0.5054   0.06471   0.06055  -0.0334   1.0000   0.1423
  -6.500  -0.5517   0.06485   0.06040  -0.0295   1.0000   0.1503
  -5.500  -0.5369   0.04079   0.03468  -0.0233   0.9947   0.0642
  -5.250  -0.5049   0.03559   0.02823  -0.0239   0.9870   0.0547
  -5.000  -0.4720   0.03177   0.02385  -0.0256   0.9804   0.0551
  -4.750  -0.4378   0.02910   0.02102  -0.0277   0.9736   0.0595
  -4.500  -0.4008   0.02668   0.01813  -0.0291   0.9672   0.0615
  -4.250  -0.3621   0.02504   0.01601  -0.0306   0.9601   0.0674
  -4.000  -0.3245   0.02313   0.01408  -0.0326   0.9543   0.0792
  -3.750  -0.2910   0.02157   0.01262  -0.0338   0.9468   0.0983
  -3.500  -0.2565   0.02010   0.01139  -0.0351   0.9404   0.1401
  -3.250  -0.2313   0.01836   0.01047  -0.0351   0.9323   0.2612
  -3.000  -0.2128   0.01635   0.01035  -0.0332   0.9257   0.6162
  -2.750  -0.1549   0.01658   0.01109  -0.0351   0.9243   0.8833
  -2.500  -0.0317   0.01747   0.01143  -0.0505   0.9316   0.9536
  -2.250   0.0826   0.01726   0.01077  -0.0669   0.9365   0.9877
  -2.000   0.1542   0.01673   0.00995  -0.0763   0.9337   1.0000
  -1.750   0.1947   0.01646   0.00951  -0.0797   0.9252   1.0000
  -1.500   0.2322   0.01623   0.00913  -0.0823   0.9162   1.0000
  -1.250   0.2613   0.01615   0.00892  -0.0833   0.9053   1.0000
  -1.000   0.2912   0.01607   0.00873  -0.0843   0.8957   1.0000
  -0.750   0.3212   0.01599   0.00855  -0.0851   0.8866   1.0000
  -0.500   0.3416   0.01611   0.00860  -0.0843   0.8753   1.0000
  -0.250   0.3636   0.01622   0.00864  -0.0836   0.8654   1.0000
   0.000   0.3895   0.01623   0.00857  -0.0834   0.8573   1.0000
   0.250   0.4064   0.01648   0.00880  -0.0818   0.8466   1.0000
   0.500   0.4262   0.01668   0.00896  -0.0806   0.8373   1.0000
   0.750   0.4492   0.01679   0.00902  -0.0798   0.8293   1.0000
   1.000   0.4656   0.01713   0.00936  -0.0781   0.8193   1.0000
   1.250   0.4873   0.01732   0.00952  -0.0771   0.8117   1.0000
   1.500   0.5058   0.01761   0.00981  -0.0756   0.8025   1.0000
   1.750   0.5235   0.01797   0.01020  -0.0740   0.7936   1.0000
   2.000   0.5466   0.01811   0.01034  -0.0729   0.7863   1.0000
   2.250   0.5621   0.01857   0.01082  -0.0711   0.7764   1.0000
   2.500   0.5845   0.01876   0.01103  -0.0699   0.7690   1.0000
   2.750   0.6031   0.01909   0.01141  -0.0683   0.7595   1.0000
   3.000   0.6206   0.01947   0.01184  -0.0665   0.7497   1.0000
   3.250   0.6472   0.01944   0.01182  -0.0656   0.7424   1.0000
   3.500   0.6634   0.01984   0.01229  -0.0636   0.7312   1.0000
   3.750   0.6824   0.02012   0.01267  -0.0618   0.7207   1.0000
   4.000   0.7072   0.02010   0.01269  -0.0606   0.7116   1.0000
   4.250   0.7296   0.02015   0.01281  -0.0591   0.7008   1.0000
   4.500   0.7491   0.02032   0.01307  -0.0572   0.6887   1.0000
   4.750   0.7705   0.02037   0.01323  -0.0555   0.6765   1.0000
   5.000   0.7933   0.02029   0.01324  -0.0538   0.6637   1.0000
   5.250   0.8165   0.02013   0.01316  -0.0522   0.6501   1.0000
   5.500   0.8398   0.01992   0.01305  -0.0504   0.6353   1.0000
   5.750   0.8632   0.01963   0.01285  -0.0487   0.6192   1.0000
   6.000   0.8878   0.01920   0.01252  -0.0469   0.6015   1.0000
   6.250   0.9083   0.01887   0.01231  -0.0446   0.5802   1.0000
   6.500   0.9304   0.01839   0.01189  -0.0424   0.5561   1.0000
   6.750   0.9467   0.01810   0.01171  -0.0395   0.5245   1.0000
   7.000   0.9598   0.01784   0.01147  -0.0359   0.4771   1.0000
   7.250   0.9678   0.01803   0.01143  -0.0317   0.4070   1.0000
   7.500   0.9688   0.01898   0.01184  -0.0269   0.3162   1.0000
   7.750   0.9630   0.02067   0.01289  -0.0218   0.2271   1.0000
   8.000   0.9540   0.02278   0.01437  -0.0165   0.1550   1.0000
   8.250   0.9459   0.02495   0.01607  -0.0114   0.1126   1.0000
   8.500   0.9443   0.02673   0.01767  -0.0070   0.0904   1.0000
   8.750   0.9490   0.02836   0.01920  -0.0038   0.0775   1.0000
   9.000   0.9639   0.03034   0.02108  -0.0019   0.0692   1.0000
   9.250   0.9859   0.03221   0.02291  -0.0012   0.0618   1.0000
   9.500   1.0158   0.03465   0.02554  -0.0015   0.0555   1.0000
   9.750   1.0454   0.03725   0.02832  -0.0016   0.0520   1.0000
  10.000   1.0768   0.04165   0.03273  -0.0029   0.0480   1.0000
  10.250   1.0829   0.04339   0.03494   0.0001   0.0462   1.0000
  10.500   1.0915   0.04648   0.03846   0.0024   0.0454   1.0000
  10.750   1.0952   0.04980   0.04218   0.0049   0.0453   1.0000
  11.000   1.0924   0.05324   0.04600   0.0079   0.0453   1.0000
  11.250   1.0845   0.05657   0.04964   0.0112   0.0457   1.0000
  11.500   1.0731   0.05991   0.05325   0.0143   0.0460   1.0000
  11.750   1.0578   0.06324   0.05684   0.0170   0.0460   1.0000
  12.000   1.0422   0.06701   0.06083   0.0187   0.0464   1.0000
  12.250   1.0265   0.07123   0.06525   0.0197   0.0469   1.0000
  12.500   1.0081   0.07576   0.06995   0.0200   0.0472   1.0000
  12.750   0.9878   0.08038   0.07475   0.0195   0.0474   1.0000
  13.000   0.9809   0.08669   0.08116   0.0188   0.0482   1.0000
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