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AG10 (ag10-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: AG10 (ag10-il)
Reynolds number: 50,000
Max Cl/Cd: 31.19 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ag10-il-50000.txt
Download as CSV file: xf-ag10-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG10                                            
  
 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  -0.6084   0.10979   0.10309   0.0224   1.0000   0.1640
  -7.500  -0.5904   0.10361   0.09691   0.0258   1.0000   0.1705
  -7.250  -0.5916   0.10152   0.09489   0.0201   1.0000   0.1785
  -6.750  -0.5756   0.09357   0.08703   0.0155   1.0000   0.1958
  -6.500  -0.5660   0.09046   0.08391   0.0119   1.0000   0.2092
  -6.250  -0.5531   0.08564   0.07914   0.0153   1.0000   0.2213
  -6.000  -0.5418   0.08167   0.07521   0.0145   1.0000   0.2340
  -5.750  -0.5301   0.07798   0.07151   0.0125   1.0000   0.2503
  -5.500  -0.5180   0.07443   0.06797   0.0085   1.0000   0.2705
  -5.250  -0.5050   0.07043   0.06401   0.0108   1.0000   0.2894
  -5.000  -0.4925   0.06691   0.06052   0.0105   1.0000   0.3176
  -4.750  -0.4812   0.06361   0.05728   0.0130   1.0000   0.3533
  -4.500  -0.4737   0.06060   0.05435   0.0161   1.0000   0.4047
  -4.250  -0.4667   0.05739   0.05123   0.0235   1.0000   0.4552
  -4.000  -0.4618   0.05451   0.04846   0.0314   1.0000   0.5178
  -3.500  -0.2715   0.03700   0.02808  -0.0300   1.0000   0.1627
  -3.250  -0.2352   0.03309   0.02338  -0.0318   1.0000   0.1489
  -3.000  -0.2046   0.02992   0.01983  -0.0323   1.0000   0.1471
  -2.750  -0.1746   0.02732   0.01687  -0.0325   1.0000   0.1531
  -2.500  -0.1444   0.02511   0.01426  -0.0324   1.0000   0.1601
  -2.250  -0.1152   0.02321   0.01211  -0.0321   1.0000   0.1743
  -2.000  -0.0862   0.02159   0.01021  -0.0316   1.0000   0.1949
  -1.750  -0.0585   0.02005   0.00866  -0.0308   1.0000   0.2249
  -1.500  -0.0304   0.01852   0.00730  -0.0301   1.0000   0.2740
  -1.250  -0.0042   0.01655   0.00599  -0.0293   1.0000   0.3845
  -1.000   0.0235   0.01377   0.00459  -0.0270   1.0000   1.0000
  -0.750   0.0501   0.01377   0.00418  -0.0264   1.0000   1.0000
  -0.500   0.0762   0.01379   0.00392  -0.0260   1.0000   1.0000
  -0.250   0.1021   0.01381   0.00374  -0.0255   1.0000   1.0000
   0.000   0.1278   0.01385   0.00364  -0.0250   1.0000   1.0000
   0.250   0.1532   0.01391   0.00360  -0.0246   1.0000   1.0000
   0.500   0.1785   0.01398   0.00361  -0.0241   1.0000   1.0000
   0.750   0.2035   0.01407   0.00369  -0.0236   1.0000   1.0000
   1.000   0.2282   0.01419   0.00381  -0.0232   1.0000   1.0000
   1.250   0.2527   0.01433   0.00400  -0.0228   1.0000   1.0000
   1.500   0.2770   0.01450   0.00426  -0.0224   1.0000   1.0000
   1.750   0.3009   0.01473   0.00462  -0.0222   1.0000   1.0000
   2.000   0.3242   0.01502   0.00507  -0.0220   1.0000   1.0000
   2.250   0.3464   0.01546   0.00569  -0.0222   1.0000   1.0000
   2.500   0.3663   0.01628   0.00673  -0.0233   1.0000   1.0000
   2.750   0.4932   0.01628   0.00733  -0.0409   0.8670   1.0000
   3.000   0.5206   0.01669   0.00747  -0.0372   0.7550   1.0000
   3.250   0.5388   0.01747   0.00788  -0.0329   0.6699   1.0000
   3.500   0.5594   0.01839   0.00842  -0.0298   0.5994   1.0000
   3.750   0.5823   0.01939   0.00915  -0.0278   0.5369   1.0000
   4.000   0.6057   0.02045   0.01000  -0.0261   0.4820   1.0000
   4.250   0.6300   0.02161   0.01098  -0.0247   0.4320   1.0000
   4.500   0.6545   0.02283   0.01214  -0.0236   0.3853   1.0000
   4.750   0.6790   0.02412   0.01332  -0.0224   0.3424   1.0000
   5.000   0.7034   0.02546   0.01456  -0.0213   0.3016   1.0000
   5.250   0.7280   0.02697   0.01613  -0.0204   0.2619   1.0000
   5.500   0.7520   0.02857   0.01760  -0.0193   0.2269   1.0000
   5.750   0.7765   0.03056   0.01982  -0.0185   0.1945   1.0000
   6.000   0.8005   0.03274   0.02200  -0.0176   0.1688   1.0000
   6.250   0.8244   0.03573   0.02551  -0.0170   0.1492   1.0000
   6.500   0.8469   0.03903   0.02925  -0.0165   0.1351   1.0000
   6.750   0.8679   0.04263   0.03317  -0.0160   0.1251   1.0000
   7.000   0.8854   0.04765   0.03894  -0.0162   0.1198   1.0000
   7.250   0.9006   0.05286   0.04464  -0.0165   0.1174   1.0000
   7.500   0.9150   0.05754   0.04949  -0.0165   0.1135   1.0000
   7.750   0.9227   0.06390   0.05630  -0.0178   0.1137   1.0000
   8.000   0.9097   0.07524   0.06835  -0.0247   0.1252   1.0000
   8.250   0.9218   0.08068   0.07380  -0.0244   0.1277   1.0000
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