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E180 (8.59%) (e180-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E180 (8.59%) (e180-il)
Reynolds number: 100,000
Max Cl/Cd: 51.84 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e180-il-100000-n5.txt
Download as CSV file: xf-e180-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5065   0.10623   0.10158   0.0040   1.0000   0.0359
  -8.750  -0.5124   0.09308   0.08853  -0.0055   1.0000   0.0216
  -8.500  -0.5087   0.08944   0.08492  -0.0066   1.0000   0.0212
  -8.250  -0.5079   0.08504   0.08059  -0.0094   1.0000   0.0211
  -8.000  -0.5087   0.08044   0.07606  -0.0129   1.0000   0.0211
  -7.750  -0.5091   0.07591   0.07159  -0.0166   1.0000   0.0209
  -7.500  -0.5057   0.07111   0.06679  -0.0205   1.0000   0.0205
  -7.250  -0.5019   0.06499   0.06063  -0.0255   1.0000   0.0206
  -7.000  -0.4956   0.05944   0.05498  -0.0290   1.0000   0.0205
  -6.750  -0.4877   0.05389   0.04925  -0.0318   1.0000   0.0204
  -6.500  -0.4778   0.04855   0.04365  -0.0338   1.0000   0.0204
  -6.250  -0.4656   0.04373   0.03851  -0.0350   1.0000   0.0203
  -6.000  -0.4518   0.03927   0.03367  -0.0354   1.0000   0.0201
  -5.750  -0.4330   0.03514   0.02908  -0.0361   0.9845   0.0199
  -5.500  -0.4027   0.03078   0.02403  -0.0382   0.9570   0.0200
  -5.250  -0.3729   0.02749   0.02006  -0.0391   0.9371   0.0202
  -5.000  -0.3443   0.02489   0.01689  -0.0393   0.9195   0.0207
  -4.750  -0.3171   0.02290   0.01445  -0.0389   0.9037   0.0213
  -4.500  -0.2921   0.02120   0.01250  -0.0382   0.8891   0.0225
  -4.250  -0.2677   0.02030   0.01150  -0.0376   0.8752   0.0261
  -4.000  -0.2431   0.01930   0.01026  -0.0366   0.8625   0.0295
  -3.750  -0.2200   0.01804   0.00885  -0.0355   0.8506   0.0332
  -3.500  -0.1958   0.01718   0.00780  -0.0344   0.8396   0.0415
  -3.250  -0.1722   0.01631   0.00702  -0.0336   0.8296   0.0701
  -3.000  -0.1484   0.01551   0.00645  -0.0329   0.8197   0.1252
  -2.750  -0.1242   0.01480   0.00600  -0.0323   0.8099   0.1989
  -2.500  -0.1005   0.01412   0.00563  -0.0316   0.8014   0.3057
  -2.250  -0.0773   0.01340   0.00540  -0.0308   0.7927   0.4484
  -2.000  -0.0555   0.01266   0.00526  -0.0291   0.7844   0.6253
  -1.750  -0.0195   0.01205   0.00519  -0.0291   0.7776   0.8424
  -1.500   0.0460   0.01194   0.00487  -0.0360   0.7705   0.9660
  -1.250   0.0917   0.01192   0.00458  -0.0396   0.7635   1.0000
  -1.000   0.1161   0.01198   0.00445  -0.0391   0.7551   1.0000
  -0.750   0.1402   0.01205   0.00432  -0.0383   0.7482   1.0000
  -0.500   0.1653   0.01214   0.00426  -0.0379   0.7399   1.0000
  -0.250   0.1897   0.01223   0.00418  -0.0372   0.7335   1.0000
   0.000   0.2151   0.01234   0.00419  -0.0368   0.7254   1.0000
   0.250   0.2398   0.01245   0.00417  -0.0361   0.7193   1.0000
   0.500   0.2653   0.01258   0.00422  -0.0358   0.7114   1.0000
   0.750   0.2902   0.01270   0.00423  -0.0351   0.7055   1.0000
   1.000   0.3160   0.01285   0.00434  -0.0348   0.6977   1.0000
   1.250   0.3410   0.01298   0.00439  -0.0342   0.6919   1.0000
   1.500   0.3669   0.01314   0.00456  -0.0339   0.6841   1.0000
   1.750   0.3922   0.01328   0.00464  -0.0333   0.6781   1.0000
   2.000   0.4181   0.01346   0.00484  -0.0330   0.6702   1.0000
   2.250   0.4435   0.01360   0.00497  -0.0324   0.6640   1.0000
   2.500   0.4694   0.01378   0.00520  -0.0322   0.6554   1.0000
   2.750   0.4949   0.01393   0.00534  -0.0316   0.6483   1.0000
   3.000   0.5206   0.01409   0.00555  -0.0311   0.6391   1.0000
   3.250   0.5462   0.01424   0.00577  -0.0306   0.6296   1.0000
   3.500   0.5716   0.01434   0.00591  -0.0300   0.6201   1.0000
   3.750   0.5971   0.01446   0.00608  -0.0294   0.6090   1.0000
   4.000   0.6225   0.01458   0.00629  -0.0288   0.5967   1.0000
   4.250   0.6479   0.01468   0.00652  -0.0282   0.5836   1.0000
   4.500   0.6732   0.01477   0.00669  -0.0275   0.5693   1.0000
   4.750   0.6984   0.01484   0.00685  -0.0268   0.5532   1.0000
   5.000   0.7235   0.01494   0.00707  -0.0261   0.5340   1.0000
   5.250   0.7483   0.01504   0.00727  -0.0253   0.5122   1.0000
   5.500   0.7729   0.01517   0.00755  -0.0246   0.4853   1.0000
   5.750   0.7962   0.01536   0.00771  -0.0235   0.4412   1.0000
   6.000   0.8161   0.01591   0.00790  -0.0222   0.3522   1.0000
   6.250   0.8307   0.01736   0.00860  -0.0209   0.2346   1.0000
   6.500   0.8470   0.01880   0.00958  -0.0200   0.1552   1.0000
   6.750   0.8642   0.02013   0.01060  -0.0191   0.0995   1.0000
   7.000   0.8809   0.02153   0.01185  -0.0180   0.0608   1.0000
   7.250   0.8973   0.02294   0.01323  -0.0168   0.0442   1.0000
   7.500   0.9134   0.02431   0.01462  -0.0155   0.0367   1.0000
   7.750   0.9307   0.02546   0.01590  -0.0144   0.0321   1.0000
   8.000   0.9457   0.02684   0.01739  -0.0130   0.0298   1.0000
   8.250   0.9581   0.02853   0.01916  -0.0115   0.0281   1.0000
   8.500   0.9735   0.03001   0.02081  -0.0100   0.0272   1.0000
   8.750   0.9896   0.03165   0.02261  -0.0087   0.0262   1.0000
   9.000   1.0067   0.03348   0.02461  -0.0074   0.0253   1.0000
   9.250   1.0244   0.03550   0.02688  -0.0063   0.0245   1.0000
   9.500   1.0404   0.03746   0.02905  -0.0052   0.0233   1.0000
   9.750   1.0532   0.03927   0.03101  -0.0041   0.0218   1.0000
  10.000   1.0645   0.04167   0.03355  -0.0031   0.0207   1.0000
  10.250   1.0740   0.04505   0.03716  -0.0020   0.0202   1.0000
  10.500   1.0787   0.04794   0.04042  -0.0004   0.0200   1.0000
  10.750   1.0770   0.05086   0.04367   0.0015   0.0198   1.0000
  11.000   1.0710   0.05398   0.04710   0.0031   0.0197   1.0000
  11.250   1.0617   0.05742   0.05084   0.0040   0.0196   1.0000
  11.500   1.0498   0.06125   0.05495   0.0043   0.0195   1.0000
  11.750   1.0370   0.06539   0.05933   0.0038   0.0196   1.0000
  12.000   1.0211   0.07016   0.06434   0.0024   0.0195   1.0000
  12.250   1.0047   0.07535   0.06973   0.0003   0.0196   1.0000
  12.500   0.9873   0.08115   0.07571  -0.0025   0.0197   1.0000
  12.750   0.9691   0.08758   0.08231  -0.0062   0.0197   1.0000
  13.000   0.9496   0.09487   0.08974  -0.0107   0.0198   1.0000
  13.250   0.9312   0.10273   0.09771  -0.0158   0.0200   1.0000
  13.500   0.9138   0.11121   0.10628  -0.0212   0.0201   1.0000
  13.750   0.8914   0.12308   0.11827  -0.0291   0.0206   1.0000
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