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E176 (8.83%) (e176-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E176 (8.83%) (e176-il)
Reynolds number: 100,000
Max Cl/Cd: 59.09 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e176-il-100000.txt
Download as CSV file: xf-e176-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E176  (8.83%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3871   0.09535   0.09076  -0.0224   1.0000   0.0903
  -8.000  -0.4002   0.09361   0.08917  -0.0278   1.0000   0.0923
  -7.750  -0.4103   0.09097   0.08661  -0.0375   1.0000   0.0929
  -7.500  -0.3826   0.08546   0.08110  -0.0268   1.0000   0.0967
  -7.250  -0.3775   0.08257   0.07826  -0.0273   1.0000   0.1002
  -7.000  -0.3783   0.07943   0.07521  -0.0324   1.0000   0.1048
  -6.750  -0.3836   0.07521   0.07104  -0.0422   1.0000   0.1077
  -6.500  -0.3722   0.07226   0.06820  -0.0361   1.0000   0.1105
  -6.250  -0.3710   0.06997   0.06597  -0.0350   1.0000   0.1141
  -6.000  -0.3858   0.06860   0.06468  -0.0333   1.0000   0.1169
  -5.750  -0.4103   0.06736   0.06328  -0.0381   0.9995   0.1214
  -5.500  -0.3845   0.06310   0.05918  -0.0364   0.9941   0.1252
  -5.250  -0.3460   0.05780   0.05370  -0.0456   0.9846   0.1383
  -5.000  -0.3101   0.05338   0.04912  -0.0520   0.9749   0.1526
  -4.750  -0.2739   0.04944   0.04506  -0.0572   0.9665   0.1683
  -4.500  -0.2358   0.04576   0.04118  -0.0629   0.9584   0.1949
  -4.250  -0.1747   0.03249   0.02587  -0.0726   0.9499   0.0775
  -4.000  -0.1323   0.02817   0.02098  -0.0759   0.9440   0.0706
  -3.750  -0.0936   0.02588   0.01778  -0.0770   0.9350   0.0655
  -3.500  -0.0518   0.02336   0.01486  -0.0794   0.9290   0.0651
  -3.250  -0.0187   0.02161   0.01285  -0.0801   0.9194   0.0663
  -3.000   0.0176   0.01997   0.01121  -0.0815   0.9123   0.0717
  -2.750   0.0483   0.01894   0.01015  -0.0818   0.9028   0.0835
  -2.500   0.0767   0.01790   0.00916  -0.0815   0.8934   0.1049
  -2.250   0.1019   0.01553   0.00826  -0.0812   0.8861   0.3787
  -2.000   0.1708   0.01347   0.00779  -0.0865   0.8835   1.0000
  -1.750   0.1955   0.01362   0.00760  -0.0859   0.8731   1.0000
  -1.500   0.2186   0.01383   0.00754  -0.0851   0.8625   1.0000
  -1.250   0.2433   0.01402   0.00747  -0.0845   0.8536   1.0000
  -1.000   0.2679   0.01421   0.00742  -0.0837   0.8447   1.0000
  -0.750   0.2914   0.01449   0.00751  -0.0831   0.8352   1.0000
  -0.500   0.3170   0.01466   0.00750  -0.0823   0.8281   1.0000
  -0.250   0.3406   0.01498   0.00768  -0.0818   0.8185   1.0000
   0.000   0.3654   0.01525   0.00780  -0.0811   0.8107   1.0000
   0.250   0.3903   0.01550   0.00794  -0.0806   0.8028   1.0000
   0.500   0.4148   0.01584   0.00819  -0.0801   0.7946   1.0000
   0.750   0.4404   0.01608   0.00832  -0.0795   0.7876   1.0000
   1.000   0.4646   0.01647   0.00867  -0.0791   0.7791   1.0000
   1.250   0.4906   0.01670   0.00881  -0.0784   0.7727   1.0000
   1.500   0.5147   0.01714   0.00924  -0.0781   0.7639   1.0000
   1.750   0.5410   0.01736   0.00939  -0.0775   0.7579   1.0000
   2.000   0.5648   0.01784   0.00991  -0.0772   0.7488   1.0000
   2.250   0.5915   0.01803   0.01004  -0.0765   0.7431   1.0000
   2.500   0.6149   0.01855   0.01061  -0.0762   0.7335   1.0000
   2.750   0.6407   0.01883   0.01088  -0.0755   0.7266   1.0000
   3.000   0.6653   0.01920   0.01131  -0.0750   0.7177   1.0000
   3.250   0.6896   0.01959   0.01175  -0.0744   0.7089   1.0000
   3.500   0.7161   0.01971   0.01188  -0.0736   0.7014   1.0000
   3.750   0.7397   0.02014   0.01239  -0.0730   0.6910   1.0000
   4.000   0.7649   0.02034   0.01269  -0.0721   0.6817   1.0000
   4.250   0.7915   0.02033   0.01271  -0.0711   0.6727   1.0000
   4.500   0.8155   0.02057   0.01305  -0.0702   0.6610   1.0000
   4.750   0.8403   0.02070   0.01328  -0.0692   0.6495   1.0000
   5.000   0.8658   0.02069   0.01335  -0.0681   0.6380   1.0000
   5.250   0.8920   0.02055   0.01332  -0.0669   0.6259   1.0000
   5.500   0.9179   0.02035   0.01322  -0.0656   0.6124   1.0000
   5.750   0.9429   0.02016   0.01315  -0.0643   0.5968   1.0000
   6.000   0.9680   0.01989   0.01300  -0.0629   0.5797   1.0000
   6.250   0.9937   0.01947   0.01272  -0.0615   0.5613   1.0000
   6.500   1.0182   0.01909   0.01248  -0.0599   0.5394   1.0000
   6.750   1.0419   0.01865   0.01216  -0.0582   0.5121   1.0000
   7.000   1.0620   0.01814   0.01168  -0.0559   0.4645   1.0000
   7.250   1.0773   0.01823   0.01157  -0.0533   0.3832   1.0000
   7.500   1.0840   0.01967   0.01224  -0.0504   0.2677   1.0000
   7.750   1.0852   0.02208   0.01389  -0.0475   0.1630   1.0000
   8.000   1.0768   0.02558   0.01649  -0.0435   0.0787   1.0000
   8.250   1.0793   0.02793   0.01870  -0.0404   0.0587   1.0000
   8.500   1.0843   0.03010   0.02077  -0.0377   0.0519   1.0000
   8.750   1.0984   0.03188   0.02267  -0.0357   0.0474   1.0000
   9.000   1.1162   0.03387   0.02465  -0.0343   0.0441   1.0000
   9.250   1.1468   0.03735   0.02808  -0.0343   0.0411   1.0000
   9.500   1.1680   0.03945   0.03050  -0.0332   0.0393   1.0000
   9.750   1.1873   0.04193   0.03329  -0.0321   0.0373   1.0000
  10.000   1.2047   0.04507   0.03678  -0.0310   0.0366   1.0000
  10.250   1.2166   0.04863   0.04075  -0.0294   0.0368   1.0000
  10.500   1.2216   0.05238   0.04493  -0.0275   0.0371   1.0000
  10.750   1.2210   0.05627   0.04922  -0.0254   0.0377   1.0000
  11.000   1.2142   0.05995   0.05324  -0.0229   0.0382   1.0000
  11.250   1.2032   0.06367   0.05724  -0.0207   0.0388   1.0000
  11.500   1.1892   0.06764   0.06147  -0.0191   0.0392   1.0000
  11.750   1.1740   0.07184   0.06589  -0.0184   0.0397   1.0000
  12.000   1.1585   0.07648   0.07073  -0.0184   0.0401   1.0000
  12.250   1.1425   0.08169   0.07611  -0.0191   0.0406   1.0000
  12.500   1.1375   0.08759   0.08214  -0.0197   0.0416   1.0000
  12.750   1.1169   0.09179   0.08657  -0.0216   0.0421   1.0000
  13.000   1.0879   0.09812   0.09315  -0.0255   0.0426   1.0000
  13.250   1.0526   0.10674   0.10197  -0.0317   0.0430   1.0000
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