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AG10 (ag10-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: AG10 (ag10-il)
Reynolds number: 1,000,000
Max Cl/Cd: 81.86 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ag10-il-1000000.txt
Download as CSV file: xf-ag10-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5174   0.12383   0.12227   0.0252   1.0000   0.0087
 -10.500  -0.5168   0.11963   0.11807   0.0248   1.0000   0.0089
  -9.250  -0.6453   0.11331   0.11168   0.0361   1.0000   0.0089
  -9.000  -0.6396   0.11028   0.10866   0.0353   1.0000   0.0090
  -8.750  -0.6344   0.10709   0.10548   0.0340   1.0000   0.0092
  -8.500  -0.6295   0.10377   0.10217   0.0325   1.0000   0.0094
  -8.250  -0.6249   0.10033   0.09874   0.0308   1.0000   0.0097
  -7.250  -0.5982   0.08146   0.07990   0.0129   1.0000   0.0115
  -7.000  -0.5830   0.07598   0.07441   0.0067   1.0000   0.0115
  -6.750  -0.5656   0.07025   0.06864   0.0004   1.0000   0.0115
  -6.500  -0.5502   0.06202   0.06035  -0.0075   1.0000   0.0118
  -6.250  -0.5314   0.05871   0.05699  -0.0105   1.0000   0.0120
  -6.000  -0.5078   0.01850   0.01485  -0.0305   1.0000   0.0091
  -5.750  -0.4814   0.01657   0.01263  -0.0308   1.0000   0.0094
  -5.500  -0.4543   0.01538   0.01124  -0.0309   1.0000   0.0098
  -5.250  -0.4269   0.01398   0.00959  -0.0309   1.0000   0.0103
  -5.000  -0.3992   0.01275   0.00813  -0.0309   1.0000   0.0107
  -4.750  -0.3714   0.01177   0.00696  -0.0308   1.0000   0.0110
  -4.500  -0.3434   0.01104   0.00610  -0.0307   1.0000   0.0114
  -4.250  -0.3156   0.00996   0.00485  -0.0307   1.0000   0.0119
  -4.000  -0.2877   0.00943   0.00430  -0.0307   1.0000   0.0129
  -3.750  -0.2596   0.00904   0.00386  -0.0306   1.0000   0.0139
  -3.500  -0.2315   0.00866   0.00344  -0.0305   1.0000   0.0148
  -3.250  -0.2034   0.00806   0.00279  -0.0304   1.0000   0.0164
  -3.000  -0.1752   0.00781   0.00253  -0.0303   1.0000   0.0182
  -2.750  -0.1471   0.00745   0.00215  -0.0302   1.0000   0.0205
  -2.500  -0.1190   0.00724   0.00198  -0.0302   1.0000   0.0234
  -2.250  -0.0909   0.00697   0.00170  -0.0301   1.0000   0.0276
  -2.000  -0.0629   0.00682   0.00158  -0.0300   1.0000   0.0315
  -1.750  -0.0349   0.00658   0.00138  -0.0298   1.0000   0.0399
  -1.500  -0.0070   0.00639   0.00124  -0.0297   1.0000   0.0518
  -1.250   0.0207   0.00620   0.00114  -0.0296   1.0000   0.0701
  -1.000   0.0536   0.00605   0.00107  -0.0306   0.9894   0.0909
  -0.750   0.0889   0.00590   0.00102  -0.0321   0.9574   0.1224
  -0.500   0.1132   0.00586   0.00100  -0.0309   0.9053   0.1637
  -0.250   0.1372   0.00582   0.00097  -0.0298   0.8449   0.2314
   0.000   0.1630   0.00573   0.00095  -0.0293   0.7766   0.3475
   0.250   0.1845   0.00437   0.00098  -0.0283   0.7084   0.8818
   0.500   0.2107   0.00440   0.00088  -0.0275   0.6337   1.0000
   0.750   0.2383   0.00470   0.00089  -0.0274   0.5620   1.0000
   1.000   0.2661   0.00498   0.00092  -0.0273   0.5001   1.0000
   1.250   0.2941   0.00522   0.00095  -0.0273   0.4514   1.0000
   1.500   0.3221   0.00543   0.00100  -0.0273   0.4111   1.0000
   1.750   0.3501   0.00563   0.00105  -0.0273   0.3765   1.0000
   2.000   0.3782   0.00581   0.00111  -0.0272   0.3467   1.0000
   2.250   0.4062   0.00600   0.00118  -0.0272   0.3184   1.0000
   2.500   0.4342   0.00618   0.00126  -0.0272   0.2918   1.0000
   2.750   0.4622   0.00637   0.00135  -0.0272   0.2668   1.0000
   3.000   0.4902   0.00658   0.00145  -0.0271   0.2412   1.0000
   3.250   0.5181   0.00678   0.00157  -0.0271   0.2166   1.0000
   3.500   0.5459   0.00700   0.00170  -0.0271   0.1925   1.0000
   3.750   0.5737   0.00725   0.00184  -0.0270   0.1686   1.0000
   4.000   0.6014   0.00750   0.00200  -0.0270   0.1455   1.0000
   4.250   0.6290   0.00777   0.00218  -0.0269   0.1238   1.0000
   4.500   0.6565   0.00808   0.00238  -0.0269   0.1019   1.0000
   4.750   0.6840   0.00836   0.00260  -0.0268   0.0834   1.0000
   5.000   0.7114   0.00869   0.00284  -0.0268   0.0660   1.0000
   5.250   0.7387   0.00903   0.00312  -0.0267   0.0503   1.0000
   5.500   0.7659   0.00942   0.00343  -0.0266   0.0363   1.0000
   5.750   0.7929   0.00984   0.00380  -0.0265   0.0255   1.0000
   6.000   0.8199   0.01028   0.00423  -0.0264   0.0190   1.0000
   6.250   0.8468   0.01079   0.00474  -0.0262   0.0151   1.0000
   6.500   0.8737   0.01120   0.00519  -0.0260   0.0132   1.0000
   6.750   0.9001   0.01183   0.00588  -0.0258   0.0115   1.0000
   7.000   0.9268   0.01224   0.00634  -0.0256   0.0105   1.0000
   7.250   0.9531   0.01277   0.00691  -0.0254   0.0097   1.0000
   7.500   0.9777   0.01390   0.00818  -0.0250   0.0089   1.0000
   7.750   1.0036   0.01446   0.00882  -0.0247   0.0086   1.0000
   8.000   1.0290   0.01516   0.00961  -0.0244   0.0083   1.0000
   8.250   1.0540   0.01593   0.01048  -0.0240   0.0080   1.0000
   8.500   1.0785   0.01677   0.01142  -0.0236   0.0077   1.0000
   8.750   1.1027   0.01762   0.01239  -0.0232   0.0074   1.0000
   9.000   1.1265   0.01853   0.01339  -0.0228   0.0072   1.0000
   9.250   1.1490   0.01970   0.01467  -0.0223   0.0069   1.0000
   9.500   1.1669   0.02204   0.01724  -0.0214   0.0066   1.0000
   9.750   1.1821   0.02498   0.02052  -0.0204   0.0064   1.0000
  10.000   1.2009   0.02675   0.02253  -0.0196   0.0064   1.0000
  10.250   1.2164   0.02908   0.02513  -0.0188   0.0063   1.0000
  10.500   1.2278   0.03203   0.02840  -0.0178   0.0063   1.0000
  10.750   1.2341   0.03554   0.03225  -0.0168   0.0063   1.0000
  11.000   1.2365   0.03922   0.03626  -0.0159   0.0063   1.0000
  11.250   1.2307   0.04355   0.04090  -0.0153   0.0063   1.0000
  11.500   1.2157   0.04786   0.04545  -0.0147   0.0063   1.0000
  11.750   1.1914   0.05517   0.05299  -0.0206   0.0063   1.0000
  12.250   1.1425   0.07981   0.07795  -0.0429   0.0065   1.0000
  12.500   1.1316   0.08749   0.08569  -0.0477   0.0065   1.0000
  12.750   1.1139   0.09651   0.09478  -0.0529   0.0066   1.0000
  13.000   1.0984   0.10494   0.10326  -0.0573   0.0066   1.0000
  13.250   0.9578   0.09401   0.09226  -0.0354   0.0067   1.0000
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