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AG08 (ag08-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: AG08 (ag08-il)
Reynolds number: 50,000
Max Cl/Cd: 32.76 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ag08-il-50000.txt
Download as CSV file: xf-ag08-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG08                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.5646   0.10478   0.09829   0.0159   1.0000   0.1978
  -7.500  -0.5510   0.09987   0.09334   0.0170   1.0000   0.2060
  -7.250  -0.5576   0.09759   0.09119   0.0122   1.0000   0.2138
  -7.000  -0.5498   0.09404   0.08767   0.0110   1.0000   0.2260
  -6.750  -0.5391   0.08985   0.08351   0.0115   1.0000   0.2389
  -6.500  -0.5350   0.08677   0.08048   0.0075   1.0000   0.2544
  -6.000  -0.5150   0.07927   0.07306   0.0087   1.0000   0.2959
  -5.750  -0.5030   0.07510   0.06893   0.0106   1.0000   0.3146
  -5.500  -0.4943   0.07179   0.06566   0.0095   1.0000   0.3404
  -5.250  -0.4836   0.06831   0.06222   0.0107   1.0000   0.3684
  -5.000  -0.4719   0.06473   0.05868   0.0135   1.0000   0.3983
  -4.750  -0.3807   0.04724   0.03945  -0.0340   1.0000   0.1571
  -4.500  -0.3523   0.04155   0.03336  -0.0361   1.0000   0.1417
  -4.250  -0.3244   0.03731   0.02864  -0.0375   1.0000   0.1412
  -4.000  -0.2956   0.03328   0.02410  -0.0384   1.0000   0.1388
  -3.750  -0.2655   0.02982   0.01987  -0.0389   1.0000   0.1412
  -3.500  -0.2380   0.02743   0.01711  -0.0387   1.0000   0.1554
  -3.250  -0.2100   0.02497   0.01436  -0.0383   1.0000   0.1666
  -3.000  -0.1833   0.02319   0.01245  -0.0378   1.0000   0.1926
  -2.750  -0.1557   0.02138   0.01051  -0.0371   1.0000   0.2212
  -2.500  -0.1293   0.01991   0.00906  -0.0362   1.0000   0.2698
  -2.250  -0.1024   0.01836   0.00781  -0.0354   1.0000   0.3490
  -2.000  -0.0806   0.01595   0.00662  -0.0335   1.0000   0.5387
  -1.750  -0.0454   0.01403   0.00536  -0.0326   1.0000   1.0000
  -1.500  -0.0196   0.01402   0.00488  -0.0321   1.0000   1.0000
  -1.250   0.0056   0.01402   0.00451  -0.0317   1.0000   1.0000
  -1.000   0.0304   0.01404   0.00426  -0.0311   1.0000   1.0000
  -0.750   0.0550   0.01408   0.00409  -0.0306   1.0000   1.0000
  -0.500   0.0793   0.01414   0.00398  -0.0301   1.0000   1.0000
  -0.250   0.1036   0.01422   0.00392  -0.0296   1.0000   1.0000
   0.000   0.1277   0.01432   0.00389  -0.0291   1.0000   1.0000
   0.250   0.1515   0.01445   0.00395  -0.0286   1.0000   1.0000
   0.500   0.1751   0.01461   0.00406  -0.0282   1.0000   1.0000
   0.750   0.1984   0.01480   0.00424  -0.0278   1.0000   1.0000
   1.000   0.2215   0.01504   0.00448  -0.0275   1.0000   1.0000
   1.250   0.2443   0.01534   0.00480  -0.0273   1.0000   1.0000
   1.500   0.2666   0.01571   0.00522  -0.0272   1.0000   1.0000
   1.750   0.2881   0.01619   0.00576  -0.0273   1.0000   1.0000
   2.000   0.3085   0.01682   0.00647  -0.0277   1.0000   1.0000
   2.250   0.3273   0.01765   0.00744  -0.0285   1.0000   1.0000
   2.500   0.4004   0.01859   0.00866  -0.0394   0.9685   1.0000
   2.750   0.4958   0.01863   0.00920  -0.0514   0.9083   1.0000
   3.000   0.5511   0.01837   0.00920  -0.0538   0.8474   1.0000
   3.250   0.5814   0.01834   0.00921  -0.0510   0.7885   1.0000
   3.500   0.6029   0.01862   0.00939  -0.0472   0.7298   1.0000
   3.750   0.6235   0.01908   0.00978  -0.0437   0.6726   1.0000
   4.000   0.6447   0.01968   0.01022  -0.0407   0.6177   1.0000
   4.250   0.6667   0.02040   0.01077  -0.0381   0.5652   1.0000
   4.500   0.6892   0.02126   0.01151  -0.0361   0.5134   1.0000
   4.750   0.7119   0.02220   0.01230  -0.0341   0.4649   1.0000
   5.000   0.7345   0.02324   0.01331  -0.0324   0.4162   1.0000
   5.250   0.7571   0.02437   0.01425  -0.0307   0.3699   1.0000
   5.500   0.7795   0.02566   0.01553  -0.0292   0.3221   1.0000
   5.750   0.8015   0.02703   0.01678  -0.0277   0.2759   1.0000
   6.000   0.8235   0.02864   0.01824  -0.0262   0.2325   1.0000
   6.250   0.8457   0.03068   0.02040  -0.0249   0.1940   1.0000
   6.500   0.8677   0.03286   0.02238  -0.0237   0.1627   1.0000
   6.750   0.8893   0.03544   0.02535  -0.0225   0.1388   1.0000
   7.000   0.9110   0.03879   0.02902  -0.0214   0.1248   1.0000
   7.250   0.9290   0.04271   0.03355  -0.0205   0.1145   1.0000
   7.500   0.9457   0.04662   0.03779  -0.0197   0.1065   1.0000
   7.750   0.9566   0.05216   0.04405  -0.0192   0.1052   1.0000
   8.000   0.9624   0.05822   0.05071  -0.0192   0.1055   1.0000
   8.250   0.9640   0.06447   0.05740  -0.0198   0.1064   1.0000
   8.500   0.9626   0.07072   0.06396  -0.0208   0.1074   1.0000
   8.750   0.9605   0.07686   0.07028  -0.0220   0.1083   1.0000
   9.000   0.9590   0.08292   0.07649  -0.0232   0.1094   1.0000
   9.250   0.8981   0.09869   0.09236  -0.0404   0.1330   1.0000
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