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E176 (8.83%) (e176-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: E176 (8.83%) (e176-il)
Reynolds number: 1,000,000
Max Cl/Cd: 119.63 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e176-il-1000000-n5.txt
Download as CSV file: xf-e176-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3929   0.08174   0.07978  -0.0315   0.8496   0.0060
  -8.500  -0.3955   0.07810   0.07602  -0.0327   0.8185   0.0059
  -8.250  -0.4021   0.07379   0.07165  -0.0344   0.7950   0.0060
  -8.000  -0.4149   0.06911   0.06693  -0.0365   0.7754   0.0064
  -7.750  -0.4168   0.06382   0.06159  -0.0417   0.7602   0.0063
  -7.500  -0.4160   0.05682   0.05450  -0.0486   0.7476   0.0063
  -7.250  -0.4152   0.04626   0.04375  -0.0564   0.7378   0.0066
  -7.000  -0.4254   0.02754   0.02422  -0.0620   0.7311   0.0067
  -6.750  -0.4090   0.02301   0.01917  -0.0623   0.7221   0.0067
  -6.500  -0.3875   0.02048   0.01624  -0.0623   0.7137   0.0068
  -6.250  -0.3638   0.01877   0.01423  -0.0622   0.7052   0.0069
  -6.000  -0.3382   0.01783   0.01309  -0.0621   0.6976   0.0070
  -5.750  -0.3126   0.01685   0.01190  -0.0620   0.6897   0.0071
  -5.500  -0.2872   0.01552   0.01032  -0.0618   0.6827   0.0071
  -5.250  -0.2614   0.01438   0.00896  -0.0617   0.6758   0.0072
  -5.000  -0.2349   0.01351   0.00790  -0.0615   0.6694   0.0072
  -4.750  -0.2097   0.01183   0.00596  -0.0612   0.6630   0.0074
  -4.500  -0.1834   0.01090   0.00488  -0.0610   0.6574   0.0078
  -4.250  -0.1563   0.01041   0.00431  -0.0609   0.6514   0.0081
  -4.000  -0.1289   0.01005   0.00387  -0.0608   0.6456   0.0084
  -3.750  -0.1013   0.00973   0.00350  -0.0608   0.6402   0.0088
  -3.500  -0.0737   0.00943   0.00313  -0.0607   0.6346   0.0092
  -3.250  -0.0459   0.00917   0.00280  -0.0607   0.6295   0.0096
  -3.000  -0.0181   0.00890   0.00249  -0.0606   0.6243   0.0099
  -2.750   0.0098   0.00868   0.00220  -0.0606   0.6193   0.0102
  -2.500   0.0378   0.00849   0.00196  -0.0606   0.6145   0.0105
  -2.250   0.0658   0.00834   0.00177  -0.0606   0.6093   0.0110
  -2.000   0.0939   0.00820   0.00159  -0.0606   0.6045   0.0113
  -1.750   0.1220   0.00806   0.00141  -0.0606   0.5999   0.0114
  -1.500   0.1502   0.00793   0.00121  -0.0605   0.5947   0.0122
  -1.000   0.2065   0.00771   0.00098  -0.0606   0.5855   0.0230
  -0.750   0.2344   0.00751   0.00090  -0.0606   0.5804   0.0642
  -0.250   0.2901   0.00710   0.00081  -0.0608   0.5708   0.1823
   0.000   0.3175   0.00679   0.00080  -0.0609   0.5656   0.2869
   0.250   0.3444   0.00639   0.00081  -0.0610   0.5607   0.4404
   0.500   0.3714   0.00606   0.00084  -0.0609   0.5556   0.5661
   0.750   0.3985   0.00587   0.00086  -0.0608   0.5500   0.6512
   1.000   0.4244   0.00560   0.00090  -0.0604   0.5446   0.7606
   1.250   0.4471   0.00529   0.00095  -0.0591   0.5376   0.8841
   1.500   0.4837   0.00520   0.00097  -0.0608   0.5294   0.9837
   1.750   0.5167   0.00527   0.00099  -0.0620   0.5205   1.0000
   2.000   0.5442   0.00534   0.00103  -0.0619   0.5113   1.0000
   2.250   0.5717   0.00543   0.00107  -0.0618   0.5015   1.0000
   2.500   0.5991   0.00553   0.00112  -0.0617   0.4916   1.0000
   2.750   0.6267   0.00562   0.00118  -0.0617   0.4814   1.0000
   3.000   0.6542   0.00572   0.00126  -0.0616   0.4706   1.0000
   3.250   0.6815   0.00584   0.00134  -0.0616   0.4581   1.0000
   3.500   0.7087   0.00598   0.00143  -0.0615   0.4424   1.0000
   3.750   0.7357   0.00615   0.00154  -0.0614   0.4241   1.0000
   4.000   0.7624   0.00638   0.00168  -0.0612   0.3983   1.0000
   4.250   0.7861   0.00702   0.00196  -0.0608   0.3222   1.0000
   4.500   0.8069   0.00808   0.00247  -0.0601   0.2100   1.0000
   4.750   0.8305   0.00873   0.00284  -0.0597   0.1521   1.0000
   5.000   0.8544   0.00932   0.00321  -0.0593   0.1064   1.0000
   5.250   0.8787   0.00983   0.00355  -0.0590   0.0727   1.0000
   5.500   0.9025   0.01041   0.00395  -0.0585   0.0392   1.0000
   5.750   0.9251   0.01111   0.00448  -0.0579   0.0081   1.0000
   6.000   0.9505   0.01144   0.00481  -0.0576   0.0062   1.0000
   6.250   0.9759   0.01176   0.00518  -0.0573   0.0054   1.0000
   6.500   1.0009   0.01211   0.00556  -0.0569   0.0050   1.0000
   6.750   1.0259   0.01244   0.00593  -0.0566   0.0048   1.0000
   7.000   1.0504   0.01282   0.00635  -0.0562   0.0046   1.0000
   7.250   1.0745   0.01323   0.00680  -0.0557   0.0043   1.0000
   7.500   1.0980   0.01368   0.00732  -0.0552   0.0041   1.0000
   7.750   1.1210   0.01419   0.00787  -0.0546   0.0039   1.0000
   8.000   1.1434   0.01473   0.00847  -0.0539   0.0037   1.0000
   8.250   1.1653   0.01530   0.00909  -0.0532   0.0035   1.0000
   8.500   1.1865   0.01590   0.00973  -0.0524   0.0033   1.0000
   8.750   1.2063   0.01661   0.01050  -0.0514   0.0031   1.0000
   9.000   1.2232   0.01757   0.01155  -0.0500   0.0029   1.0000
   9.250   1.2390   0.01855   0.01264  -0.0485   0.0029   1.0000
   9.500   1.2513   0.01978   0.01398  -0.0466   0.0028   1.0000
   9.750   1.2667   0.02063   0.01491  -0.0451   0.0027   1.0000
  10.000   1.2815   0.02146   0.01581  -0.0435   0.0027   1.0000
  10.250   1.2916   0.02236   0.01680  -0.0412   0.0027   1.0000
  10.500   1.3000   0.02328   0.01780  -0.0387   0.0026   1.0000
  10.750   1.3072   0.02435   0.01894  -0.0364   0.0026   1.0000
  11.000   1.3129   0.02564   0.02033  -0.0342   0.0026   1.0000
  11.250   1.3206   0.02686   0.02164  -0.0325   0.0025   1.0000
  11.500   1.3259   0.02839   0.02327  -0.0309   0.0025   1.0000
  11.750   1.3309   0.03005   0.02506  -0.0294   0.0025   1.0000
  12.000   1.3368   0.03170   0.02681  -0.0283   0.0024   1.0000
  12.250   1.3401   0.03371   0.02893  -0.0272   0.0024   1.0000
  12.500   1.3445   0.03567   0.03100  -0.0263   0.0023   1.0000
  12.750   1.3451   0.03815   0.03361  -0.0256   0.0023   1.0000
  13.000   1.3476   0.04047   0.03605  -0.0251   0.0022   1.0000
  13.250   1.3496   0.04292   0.03861  -0.0248   0.0022   1.0000
  13.500   1.3463   0.04612   0.04195  -0.0246   0.0022   1.0000
  13.750   1.3452   0.04912   0.04508  -0.0247   0.0021   1.0000
  14.000   1.3397   0.05282   0.04893  -0.0251   0.0021   1.0000
  14.250   1.3354   0.05646   0.05270  -0.0257   0.0021   1.0000
  14.500   1.3308   0.06029   0.05666  -0.0266   0.0020   1.0000
  14.750   1.3236   0.06470   0.06120  -0.0279   0.0020   1.0000
  15.000   1.3146   0.06963   0.06628  -0.0295   0.0020   1.0000
  15.250   1.3053   0.07487   0.07167  -0.0316   0.0019   1.0000
  15.500   1.2920   0.08105   0.07800  -0.0342   0.0020   1.0000
  15.750   1.2808   0.08722   0.08432  -0.0372   0.0019   1.0000
  16.000   1.2668   0.09424   0.09149  -0.0407   0.0019   1.0000
  16.250   1.2513   0.10188   0.09928  -0.0448   0.0019   1.0000
  16.500   1.2322   0.11076   0.10833  -0.0497   0.0020   1.0000
  16.750   1.2136   0.11997   0.11769  -0.0550   0.0020   1.0000
  17.000   1.1996   0.12848   0.12631  -0.0600   0.0019   1.0000
  17.250   1.1822   0.13823   0.13620  -0.0658   0.0019   1.0000
  17.500   1.1603   0.14960   0.14772  -0.0725   0.0020   1.0000
  17.750   1.1382   0.16165   0.15990  -0.0796   0.0020   1.0000
  18.000   1.1138   0.17522   0.17360  -0.0874   0.0021   1.0000
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