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AG16 (ag16-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: AG16 (ag16-il)
Reynolds number: 500,000
Max Cl/Cd: 82.4 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ag16-il-500000.txt
Download as CSV file: xf-ag16-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG16                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4684   0.08352   0.08150  -0.0022   1.0000   0.0165
  -8.500  -0.4676   0.07950   0.07750  -0.0032   1.0000   0.0168
  -8.250  -0.4677   0.07537   0.07338  -0.0044   1.0000   0.0171
  -8.000  -0.4686   0.07107   0.06910  -0.0059   1.0000   0.0173
  -7.750  -0.4707   0.06653   0.06458  -0.0078   1.0000   0.0175
  -7.500  -0.4737   0.06190   0.05998  -0.0101   1.0000   0.0178
  -7.250  -0.4760   0.05638   0.05448  -0.0145   1.0000   0.0180
  -7.000  -0.4734   0.04918   0.04728  -0.0226   1.0000   0.0182
  -6.750  -0.4676   0.03915   0.03714  -0.0339   1.0000   0.0182
  -6.500  -0.4580   0.03100   0.02876  -0.0405   1.0000   0.0187
  -6.250  -0.4444   0.02486   0.02234  -0.0442   1.0000   0.0196
  -6.000  -0.4275   0.01979   0.01692  -0.0464   1.0000   0.0205
  -5.750  -0.4221   0.01802   0.01309  -0.0495   1.0000   0.0103
  -5.500  -0.3964   0.01591   0.01069  -0.0493   1.0000   0.0108
  -5.250  -0.3703   0.01464   0.00924  -0.0491   1.0000   0.0116
  -5.000  -0.3440   0.01352   0.00797  -0.0488   1.0000   0.0124
  -4.750  -0.3178   0.01270   0.00704  -0.0484   1.0000   0.0135
  -4.500  -0.2916   0.01218   0.00645  -0.0480   1.0000   0.0149
  -4.250  -0.2654   0.01139   0.00556  -0.0475   1.0000   0.0155
  -4.000  -0.2387   0.00984   0.00383  -0.0473   1.0000   0.0185
  -3.750  -0.2121   0.00934   0.00328  -0.0469   1.0000   0.0233
  -3.500  -0.1851   0.00866   0.00263  -0.0467   1.0000   0.0445
  -3.250  -0.1586   0.00816   0.00231  -0.0466   1.0000   0.0888
  -3.000  -0.1321   0.00776   0.00212  -0.0465   1.0000   0.1411
  -2.750  -0.1056   0.00744   0.00199  -0.0465   1.0000   0.1963
  -2.500  -0.0752   0.00714   0.00189  -0.0472   0.9985   0.2537
  -2.250  -0.0357   0.00687   0.00177  -0.0498   0.9932   0.3099
  -2.000   0.0026   0.00662   0.00167  -0.0521   0.9860   0.3618
  -1.750   0.0399   0.00640   0.00158  -0.0541   0.9769   0.4102
  -1.500   0.0756   0.00620   0.00149  -0.0556   0.9648   0.4577
  -1.250   0.1080   0.00598   0.00144  -0.0564   0.9480   0.5141
  -1.000   0.1370   0.00580   0.00138  -0.0563   0.9270   0.5673
  -0.750   0.1627   0.00563   0.00134  -0.0555   0.9016   0.6251
  -0.500   0.1873   0.00544   0.00130  -0.0544   0.8744   0.6950
  -0.250   0.2098   0.00517   0.00128  -0.0527   0.8459   0.7962
   0.000   0.2357   0.00485   0.00120  -0.0514   0.8167   1.0000
   0.250   0.2624   0.00498   0.00117  -0.0510   0.7862   1.0000
   0.500   0.2893   0.00512   0.00115  -0.0505   0.7552   1.0000
   0.750   0.3164   0.00528   0.00115  -0.0502   0.7246   1.0000
   1.000   0.3435   0.00544   0.00116  -0.0498   0.6941   1.0000
   1.250   0.3708   0.00561   0.00118  -0.0496   0.6635   1.0000
   1.500   0.3981   0.00578   0.00123  -0.0493   0.6330   1.0000
   1.750   0.4255   0.00597   0.00128  -0.0491   0.6024   1.0000
   2.000   0.4528   0.00616   0.00134  -0.0489   0.5718   1.0000
   2.500   0.5076   0.00657   0.00151  -0.0486   0.5102   1.0000
   2.750   0.5349   0.00679   0.00164  -0.0484   0.4789   1.0000
   3.000   0.5622   0.00703   0.00176  -0.0483   0.4474   1.0000
   3.250   0.5894   0.00728   0.00189  -0.0481   0.4149   1.0000
   3.500   0.6166   0.00755   0.00205  -0.0480   0.3817   1.0000
   4.000   0.6707   0.00814   0.00243  -0.0477   0.3170   1.0000
   4.250   0.6976   0.00847   0.00265  -0.0476   0.2836   1.0000
   4.500   0.7243   0.00883   0.00289  -0.0475   0.2516   1.0000
   4.750   0.7511   0.00919   0.00315  -0.0473   0.2214   1.0000
   5.000   0.7777   0.00956   0.00345  -0.0472   0.1937   1.0000
   5.250   0.8041   0.00998   0.00376  -0.0470   0.1634   1.0000
   5.500   0.8304   0.01044   0.00411  -0.0468   0.1344   1.0000
   5.750   0.8565   0.01092   0.00449  -0.0467   0.1081   1.0000
   6.000   0.8823   0.01145   0.00492  -0.0464   0.0828   1.0000
   6.250   0.9078   0.01205   0.00545  -0.0462   0.0595   1.0000
   6.500   0.9329   0.01273   0.00604  -0.0458   0.0414   1.0000
   6.750   0.9582   0.01339   0.00669  -0.0455   0.0292   1.0000
   7.000   0.9828   0.01419   0.00750  -0.0450   0.0200   1.0000
   7.250   1.0053   0.01557   0.00898  -0.0442   0.0133   1.0000
   7.500   1.0302   0.01624   0.00975  -0.0437   0.0115   1.0000
   7.750   1.0537   0.01720   0.01082  -0.0431   0.0099   1.0000
   8.000   1.0748   0.01865   0.01239  -0.0422   0.0088   1.0000
   8.250   1.0917   0.02110   0.01513  -0.0407   0.0082   1.0000
   8.500   1.1083   0.02372   0.01802  -0.0393   0.0079   1.0000
   8.750   1.1315   0.02445   0.01889  -0.0387   0.0074   1.0000
   9.000   1.1521   0.02574   0.02036  -0.0379   0.0070   1.0000
   9.250   1.1692   0.02783   0.02270  -0.0367   0.0067   1.0000
   9.500   1.1842   0.03021   0.02537  -0.0354   0.0065   1.0000
   9.750   1.1967   0.03283   0.02828  -0.0341   0.0063   1.0000
  10.000   1.2059   0.03569   0.03144  -0.0326   0.0061   1.0000
  10.250   1.2111   0.03877   0.03483  -0.0311   0.0059   1.0000
  10.500   1.2100   0.04231   0.03869  -0.0294   0.0058   1.0000
  10.750   1.2017   0.04587   0.04252  -0.0275   0.0058   1.0000
  11.000   1.1856   0.04978   0.04668  -0.0262   0.0058   1.0000
  11.250   1.1645   0.05534   0.05250  -0.0279   0.0058   1.0000
  11.500   1.1432   0.06257   0.05997  -0.0329   0.0059   1.0000
  11.750   1.1223   0.07132   0.06893  -0.0399   0.0060   1.0000
  12.000   1.0991   0.08180   0.07959  -0.0482   0.0062   1.0000
  12.250   1.0735   0.09352   0.09145  -0.0564   0.0064   1.0000
  12.500   1.0442   0.10651   0.10455  -0.0642   0.0067   1.0000
  12.750   1.0084   0.12146   0.11955  -0.0717   0.0071   1.0000
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