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AG46c -03f (ag46c03-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: AG46c -03f (ag46c03-il)
Reynolds number: 500,000
Max Cl/Cd: 74.6 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ag46c03-il-500000.txt
Download as CSV file: xf-ag46c03-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG46c -03f                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.6093   0.11314   0.11096   0.0341   1.0000   0.0133
  -8.000  -0.6051   0.10921   0.10704   0.0317   1.0000   0.0137
  -7.750  -0.6010   0.10523   0.10308   0.0288   1.0000   0.0140
  -7.500  -0.5961   0.10131   0.09918   0.0260   1.0000   0.0142
  -7.250  -0.5908   0.09747   0.09536   0.0234   1.0000   0.0143
  -7.000  -0.5860   0.09348   0.09139   0.0206   1.0000   0.0144
  -6.750  -0.5808   0.08932   0.08723   0.0172   1.0000   0.0144
  -6.500  -0.5714   0.08449   0.08242   0.0117   1.0000   0.0145
  -6.250  -0.5586   0.07917   0.07710   0.0054   1.0000   0.0145
  -6.000  -0.4920   0.05730   0.05536  -0.0059   1.0000   0.0150
  -5.750  -0.4860   0.05137   0.04940  -0.0103   1.0000   0.0153
  -5.500  -0.4759   0.04648   0.04447  -0.0134   1.0000   0.0157
  -5.250  -0.4630   0.04163   0.03954  -0.0164   1.0000   0.0161
  -5.000  -0.4479   0.03679   0.03462  -0.0193   1.0000   0.0165
  -4.750  -0.4307   0.03190   0.02959  -0.0220   1.0000   0.0172
  -4.500  -0.4116   0.02704   0.02456  -0.0243   1.0000   0.0180
  -4.250  -0.3907   0.02240   0.01970  -0.0260   1.0000   0.0193
  -4.000  -0.3631   0.01980   0.01679  -0.0263   1.0000   0.0218
  -3.750  -0.3393   0.01701   0.01363  -0.0265   1.0000   0.0221
  -3.250  -0.3055   0.01751   0.01257  -0.0271   1.0000   0.0138
  -3.000  -0.2781   0.01527   0.00994  -0.0268   1.0000   0.0140
  -2.750  -0.2506   0.01415   0.00862  -0.0264   1.0000   0.0144
  -2.500  -0.2240   0.01195   0.00617  -0.0261   1.0000   0.0159
  -2.250  -0.1969   0.01082   0.00494  -0.0257   1.0000   0.0160
  -2.000  -0.1698   0.00990   0.00396  -0.0253   1.0000   0.0167
  -1.750  -0.1424   0.00925   0.00328  -0.0250   1.0000   0.0185
  -1.500  -0.1150   0.00880   0.00277  -0.0247   1.0000   0.0219
  -1.250  -0.0803   0.00807   0.00206  -0.0261   0.9851   0.0388
  -1.000  -0.0394   0.00743   0.00172  -0.0289   0.9284   0.1219
  -0.750  -0.0150   0.00721   0.00155  -0.0278   0.8399   0.2104
  -0.500   0.0092   0.00682   0.00141  -0.0272   0.7921   0.3557
  -0.250   0.0332   0.00601   0.00136  -0.0266   0.7665   0.6190
   0.000   0.0516   0.00533   0.00138  -0.0241   0.7489   0.8570
   0.250   0.0868   0.00521   0.00130  -0.0249   0.7335   1.0000
   0.500   0.1143   0.00532   0.00126  -0.0247   0.7203   1.0000
   0.750   0.1418   0.00544   0.00124  -0.0245   0.7083   1.0000
   1.000   0.1695   0.00554   0.00124  -0.0243   0.6959   1.0000
   1.250   0.1973   0.00559   0.00122  -0.0242   0.6825   1.0000
   1.500   0.2252   0.00563   0.00119  -0.0240   0.6681   1.0000
   1.750   0.2531   0.00567   0.00116  -0.0239   0.6518   1.0000
   2.000   0.2809   0.00571   0.00114  -0.0237   0.6327   1.0000
   2.250   0.3085   0.00580   0.00112  -0.0236   0.6115   1.0000
   2.500   0.3361   0.00589   0.00113  -0.0234   0.5867   1.0000
   2.750   0.3637   0.00602   0.00115  -0.0232   0.5601   1.0000
   3.000   0.3912   0.00617   0.00118  -0.0231   0.5314   1.0000
   3.250   0.4186   0.00635   0.00124  -0.0229   0.5010   1.0000
   3.500   0.4460   0.00654   0.00133  -0.0228   0.4695   1.0000
   3.750   0.4734   0.00676   0.00142  -0.0227   0.4355   1.0000
   4.000   0.5007   0.00701   0.00153  -0.0226   0.4021   1.0000
   4.250   0.5279   0.00727   0.00166  -0.0225   0.3662   1.0000
   4.500   0.5551   0.00755   0.00184  -0.0225   0.3325   1.0000
   4.750   0.5823   0.00785   0.00201  -0.0224   0.2957   1.0000
   5.000   0.6093   0.00818   0.00221  -0.0224   0.2620   1.0000
   5.250   0.6363   0.00853   0.00243  -0.0223   0.2278   1.0000
   5.500   0.6632   0.00890   0.00270  -0.0223   0.1966   1.0000
   5.750   0.6901   0.00927   0.00298  -0.0222   0.1699   1.0000
   6.000   0.7169   0.00964   0.00327  -0.0221   0.1461   1.0000
   6.250   0.7436   0.01005   0.00360  -0.0221   0.1268   1.0000
   6.500   0.7703   0.01040   0.00394  -0.0220   0.1100   1.0000
   6.750   0.7970   0.01079   0.00430  -0.0219   0.0951   1.0000
   7.000   0.8235   0.01120   0.00469  -0.0218   0.0814   1.0000
   7.250   0.8499   0.01163   0.00510  -0.0217   0.0689   1.0000
   7.500   0.8761   0.01210   0.00557  -0.0215   0.0576   1.0000
   7.750   0.9020   0.01264   0.00613  -0.0214   0.0475   1.0000
   8.000   0.9273   0.01336   0.00683  -0.0211   0.0383   1.0000
   8.250   0.9534   0.01381   0.00733  -0.0210   0.0321   1.0000
   8.500   0.9781   0.01465   0.00825  -0.0207   0.0266   1.0000
   8.750   1.0032   0.01532   0.00898  -0.0204   0.0226   1.0000
   9.000   1.0257   0.01669   0.01048  -0.0199   0.0191   1.0000
   9.250   1.0508   0.01727   0.01118  -0.0196   0.0169   1.0000
   9.500   1.0746   0.01813   0.01213  -0.0192   0.0150   1.0000
   9.750   1.0920   0.02062   0.01484  -0.0183   0.0131   1.0000
  10.000   1.1137   0.02197   0.01639  -0.0177   0.0124   1.0000
  10.250   1.1356   0.02317   0.01776  -0.0172   0.0116   1.0000
  10.500   1.1573   0.02424   0.01898  -0.0168   0.0105   1.0000
  10.750   1.1785   0.02525   0.02010  -0.0164   0.0097   1.0000
  11.000   1.1960   0.02702   0.02202  -0.0158   0.0091   1.0000
  11.250   1.2047   0.03053   0.02588  -0.0148   0.0085   1.0000
  11.750   1.2096   0.03850   0.03468  -0.0129   0.0080   1.0000
  12.000   1.2120   0.04152   0.03799  -0.0124   0.0079   1.0000
  12.250   1.2045   0.04501   0.04174  -0.0119   0.0078   1.0000
  12.500   1.1913   0.04968   0.04664  -0.0142   0.0078   1.0000
  12.750   1.1762   0.05606   0.05324  -0.0194   0.0078   1.0000
  13.000   1.1593   0.06370   0.06108  -0.0257   0.0078   1.0000
  13.250   1.1376   0.07303   0.07058  -0.0330   0.0079   1.0000
  13.500   1.1101   0.08393   0.08162  -0.0405   0.0081   1.0000
  13.750   0.9886   0.07568   0.07327  -0.0237   0.0084   1.0000
  14.000   0.9717   0.08311   0.08079  -0.0267   0.0085   1.0000
  14.250   0.9544   0.09067   0.08843  -0.0297   0.0087   1.0000
  14.500   0.9324   0.09933   0.09719  -0.0333   0.0088   1.0000
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