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E180 (8.59%) (e180-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: E180 (8.59%) (e180-il)
Reynolds number: 200,000
Max Cl/Cd: 71 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e180-il-200000.txt
Download as CSV file: xf-e180-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E180  (8.59%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.5148   0.09422   0.09110  -0.0092   1.0000   0.0394
  -8.250  -0.5161   0.08977   0.08669  -0.0138   1.0000   0.0394
  -8.000  -0.5179   0.08350   0.08049  -0.0127   1.0000   0.0405
  -7.750  -0.5108   0.08041   0.07742  -0.0122   1.0000   0.0415
  -7.500  -0.5050   0.07692   0.07395  -0.0139   1.0000   0.0425
  -7.250  -0.4989   0.07285   0.06990  -0.0171   1.0000   0.0437
  -7.000  -0.4915   0.06837   0.06541  -0.0211   1.0000   0.0450
  -6.750  -0.4825   0.06343   0.06042  -0.0255   1.0000   0.0469
  -6.500  -0.4692   0.05780   0.05426  -0.0333   1.0000   0.0514
  -6.250  -0.4623   0.05071   0.04709  -0.0355   1.0000   0.0528
  -6.000  -0.4454   0.04748   0.04396  -0.0361   1.0000   0.0544
  -5.750  -0.4259   0.04447   0.04088  -0.0375   0.9918   0.0569
  -5.500  -0.3922   0.03906   0.03475  -0.0428   0.9651   0.0662
  -5.250  -0.3621   0.03007   0.02500  -0.0433   0.9468   0.0365
  -5.000  -0.3395   0.02594   0.02029  -0.0425   0.9286   0.0336
  -4.750  -0.3185   0.02319   0.01700  -0.0408   0.9111   0.0329
  -4.500  -0.2957   0.02042   0.01351  -0.0385   0.8966   0.0299
  -4.250  -0.2724   0.01882   0.01157  -0.0370   0.8835   0.0295
  -4.000  -0.2492   0.01720   0.00972  -0.0355   0.8719   0.0300
  -3.750  -0.2256   0.01590   0.00832  -0.0343   0.8606   0.0317
  -3.500  -0.2012   0.01497   0.00728  -0.0333   0.8497   0.0347
  -3.250  -0.1772   0.01408   0.00630  -0.0323   0.8398   0.0419
  -3.000  -0.1539   0.01308   0.00531  -0.0310   0.8312   0.0676
  -2.750  -0.1302   0.01208   0.00474  -0.0304   0.8213   0.1552
  -2.500  -0.1081   0.01116   0.00448  -0.0297   0.8128   0.3132
  -2.250  -0.0876   0.01033   0.00427  -0.0284   0.8048   0.4931
  -2.000  -0.0696   0.00950   0.00422  -0.0260   0.7964   0.6991
  -1.750  -0.0159   0.00905   0.00419  -0.0294   0.7904   0.9323
  -1.500   0.0555   0.00907   0.00396  -0.0381   0.7833   0.9954
  -1.250   0.0863   0.00909   0.00377  -0.0388   0.7761   1.0000
  -1.000   0.1111   0.00914   0.00368  -0.0384   0.7678   1.0000
  -0.750   0.1351   0.00921   0.00358  -0.0376   0.7612   1.0000
  -0.500   0.1606   0.00928   0.00354  -0.0372   0.7530   1.0000
  -0.250   0.1851   0.00937   0.00349  -0.0365   0.7469   1.0000
   0.000   0.2110   0.00946   0.00351  -0.0362   0.7388   1.0000
   0.500   0.2619   0.00966   0.00355  -0.0352   0.7250   1.0000
   0.750   0.2870   0.00978   0.00355  -0.0346   0.7192   1.0000
   1.000   0.3132   0.00990   0.00366  -0.0344   0.7115   1.0000
   1.250   0.3386   0.01001   0.00370  -0.0338   0.7055   1.0000
   1.500   0.3648   0.01014   0.00382  -0.0335   0.6978   1.0000
   1.750   0.3903   0.01026   0.00387  -0.0329   0.6915   1.0000
   2.000   0.4165   0.01038   0.00401  -0.0326   0.6833   1.0000
   2.250   0.4420   0.01049   0.00406  -0.0319   0.6768   1.0000
   2.500   0.4681   0.01060   0.00422  -0.0316   0.6676   1.0000
   2.750   0.4938   0.01070   0.00429  -0.0310   0.6595   1.0000
   3.000   0.5196   0.01077   0.00436  -0.0305   0.6505   1.0000
   3.250   0.5455   0.01086   0.00449  -0.0300   0.6408   1.0000
   3.500   0.5714   0.01093   0.00458  -0.0294   0.6318   1.0000
   3.750   0.5972   0.01098   0.00464  -0.0288   0.6216   1.0000
   4.000   0.6232   0.01103   0.00475  -0.0283   0.6099   1.0000
   4.250   0.6491   0.01107   0.00483  -0.0278   0.5978   1.0000
   4.500   0.6750   0.01110   0.00494  -0.0272   0.5851   1.0000
   4.750   0.7008   0.01111   0.00501  -0.0266   0.5708   1.0000
   5.000   0.7264   0.01109   0.00502  -0.0259   0.5528   1.0000
   5.250   0.7513   0.01102   0.00497  -0.0250   0.5241   1.0000
   5.500   0.7757   0.01105   0.00498  -0.0242   0.4825   1.0000
   5.750   0.8002   0.01127   0.00516  -0.0235   0.4403   1.0000
   6.000   0.8219   0.01185   0.00543  -0.0226   0.3571   1.0000
   6.250   0.8399   0.01308   0.00610  -0.0217   0.2481   1.0000
   6.500   0.8556   0.01476   0.00713  -0.0208   0.1363   1.0000
   6.750   0.8676   0.01707   0.00880  -0.0193   0.0490   1.0000
   7.000   0.8867   0.01824   0.01005  -0.0181   0.0405   1.0000
   7.250   0.9017   0.01985   0.01169  -0.0166   0.0362   1.0000
   7.500   0.9197   0.02111   0.01304  -0.0153   0.0346   1.0000
   7.750   0.9384   0.02235   0.01439  -0.0140   0.0328   1.0000
   8.000   0.9577   0.02353   0.01564  -0.0129   0.0304   1.0000
   8.250   0.9768   0.02497   0.01713  -0.0117   0.0289   1.0000
   8.500   0.9967   0.02676   0.01903  -0.0106   0.0280   1.0000
   8.750   1.0177   0.02909   0.02148  -0.0097   0.0272   1.0000
   9.000   1.0387   0.03184   0.02445  -0.0087   0.0269   1.0000
   9.250   1.0575   0.03480   0.02770  -0.0077   0.0268   1.0000
   9.500   1.0693   0.03948   0.03277  -0.0065   0.0262   1.0000
  10.000   1.0838   0.04717   0.04121  -0.0034   0.0261   1.0000
  10.250   1.0934   0.04904   0.04335  -0.0018   0.0266   1.0000
  10.500   1.0692   0.05463   0.04987   0.0025   0.0309   1.0000
  11.500   0.9121   0.06322   0.05945   0.0072   0.0318   1.0000
  11.750   0.8860   0.06960   0.06599   0.0050   0.0319   1.0000
  12.000   0.8594   0.07668   0.07320   0.0019   0.0320   1.0000
  12.250   0.8319   0.08456   0.08121  -0.0023   0.0321   1.0000
  12.500   0.8019   0.09368   0.09044  -0.0077   0.0322   1.0000
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