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AG46c -03f (ag46c03-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: AG46c -03f (ag46c03-il)
Reynolds number: 100,000
Max Cl/Cd: 44.24 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ag46c03-il-100000-n5.txt
Download as CSV file: xf-ag46c03-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.5841   0.10581   0.10104   0.0248   1.0000   0.0399
  -7.250  -0.5805   0.10198   0.09724   0.0225   1.0000   0.0405
  -7.000  -0.5769   0.09808   0.09339   0.0200   1.0000   0.0409
  -6.750  -0.5731   0.09409   0.08945   0.0173   1.0000   0.0410
  -6.250  -0.5588   0.08319   0.07858   0.0061   1.0000   0.0307
  -6.000  -0.5494   0.07857   0.07397   0.0030   1.0000   0.0292
  -5.750  -0.5367   0.07335   0.06873  -0.0021   1.0000   0.0284
  -5.500  -0.5216   0.06790   0.06322  -0.0074   1.0000   0.0280
  -5.250  -0.5042   0.06232   0.05754  -0.0124   1.0000   0.0276
  -5.000  -0.4847   0.05652   0.05157  -0.0169   1.0000   0.0268
  -4.750  -0.4623   0.04955   0.04431  -0.0215   1.0000   0.0248
  -4.250  -0.4107   0.03773   0.03141  -0.0261   1.0000   0.0219
  -4.000  -0.3867   0.03354   0.02677  -0.0271   1.0000   0.0217
  -3.750  -0.3612   0.02987   0.02258  -0.0276   1.0000   0.0217
  -3.500  -0.3347   0.02678   0.01895  -0.0277   1.0000   0.0218
  -3.250  -0.3076   0.02426   0.01592  -0.0275   1.0000   0.0222
  -3.000  -0.2811   0.02156   0.01285  -0.0274   1.0000   0.0231
  -2.750  -0.2547   0.02019   0.01135  -0.0273   1.0000   0.0262
  -2.500  -0.2276   0.01885   0.00980  -0.0269   1.0000   0.0296
  -2.250  -0.2005   0.01745   0.00820  -0.0263   1.0000   0.0319
  -2.000  -0.1743   0.01612   0.00687  -0.0260   1.0000   0.0366
  -1.750  -0.1477   0.01522   0.00592  -0.0256   1.0000   0.0460
  -1.500  -0.1211   0.01433   0.00504  -0.0253   1.0000   0.0628
  -1.250  -0.0946   0.01343   0.00437  -0.0251   1.0000   0.1075
  -1.000  -0.0688   0.01251   0.00396  -0.0250   1.0000   0.2175
  -0.750  -0.0447   0.01126   0.00371  -0.0248   1.0000   0.4622
  -0.500  -0.0291   0.00994   0.00366  -0.0208   1.0000   0.8401
  -0.250   0.0110   0.00970   0.00334  -0.0230   1.0000   1.0000
   0.000   0.0415   0.00973   0.00318  -0.0237   0.9885   1.0000
   0.250   0.0833   0.00980   0.00304  -0.0267   0.9436   1.0000
   0.500   0.1227   0.00989   0.00289  -0.0288   0.8958   1.0000
   0.750   0.1563   0.01000   0.00278  -0.0296   0.8514   1.0000
   1.250   0.2111   0.01034   0.00266  -0.0284   0.7859   1.0000
   1.500   0.2373   0.01054   0.00267  -0.0276   0.7610   1.0000
   1.750   0.2635   0.01075   0.00272  -0.0270   0.7388   1.0000
   2.000   0.2898   0.01098   0.00279  -0.0263   0.7187   1.0000
   2.250   0.3160   0.01121   0.00292  -0.0257   0.6989   1.0000
   2.500   0.3426   0.01140   0.00305  -0.0253   0.6768   1.0000
   2.750   0.3692   0.01156   0.00315  -0.0248   0.6537   1.0000
   3.000   0.3957   0.01170   0.00325  -0.0244   0.6285   1.0000
   3.250   0.4221   0.01185   0.00334  -0.0238   0.6016   1.0000
   3.500   0.4483   0.01202   0.00346  -0.0233   0.5724   1.0000
   3.750   0.4744   0.01222   0.00356  -0.0227   0.5408   1.0000
   4.000   0.5005   0.01245   0.00371  -0.0222   0.5066   1.0000
   4.250   0.5264   0.01274   0.00387  -0.0216   0.4710   1.0000
   4.500   0.5524   0.01307   0.00414  -0.0212   0.4335   1.0000
   4.750   0.5783   0.01344   0.00440  -0.0208   0.3952   1.0000
   5.000   0.6040   0.01386   0.00471  -0.0204   0.3571   1.0000
   5.250   0.6297   0.01433   0.00507  -0.0201   0.3193   1.0000
   5.500   0.6554   0.01483   0.00552  -0.0198   0.2819   1.0000
   5.750   0.6809   0.01539   0.00599  -0.0196   0.2475   1.0000
   6.000   0.7064   0.01598   0.00652  -0.0193   0.2159   1.0000
   6.250   0.7317   0.01662   0.00712  -0.0191   0.1887   1.0000
   6.500   0.7568   0.01731   0.00776  -0.0189   0.1649   1.0000
   6.750   0.7819   0.01802   0.00853  -0.0186   0.1444   1.0000
   7.000   0.8065   0.01881   0.00930  -0.0184   0.1260   1.0000
   7.250   0.8312   0.01962   0.01018  -0.0181   0.1104   1.0000
   7.500   0.8556   0.02046   0.01110  -0.0178   0.0949   1.0000
   7.750   0.8795   0.02146   0.01217  -0.0174   0.0829   1.0000
   8.000   0.9030   0.02248   0.01333  -0.0171   0.0710   1.0000
   8.250   0.9257   0.02368   0.01458  -0.0167   0.0616   1.0000
   8.500   0.9488   0.02485   0.01596  -0.0162   0.0529   1.0000
   8.750   0.9706   0.02629   0.01757  -0.0157   0.0458   1.0000
   9.000   0.9918   0.02783   0.01926  -0.0152   0.0407   1.0000
   9.250   1.0120   0.02968   0.02135  -0.0146   0.0358   1.0000
   9.500   1.0321   0.03148   0.02341  -0.0140   0.0318   1.0000
   9.750   1.0497   0.03367   0.02581  -0.0135   0.0293   1.0000
  10.000   1.0654   0.03662   0.02914  -0.0127   0.0272   1.0000
  10.250   1.0801   0.03933   0.03234  -0.0121   0.0245   1.0000
  10.500   1.0919   0.04222   0.03562  -0.0117   0.0227   1.0000
  10.750   1.0998   0.04554   0.03929  -0.0112   0.0217   1.0000
  11.000   1.1035   0.04909   0.04316  -0.0110   0.0210   1.0000
  11.250   1.1015   0.05307   0.04744  -0.0110   0.0205   1.0000
  11.500   1.0918   0.05745   0.05211  -0.0115   0.0202   1.0000
  11.750   1.0761   0.06249   0.05742  -0.0137   0.0202   1.0000
  12.000   1.0566   0.06941   0.06460  -0.0193   0.0204   1.0000
  12.250   1.0199   0.08225   0.07777  -0.0307   0.0213   1.0000
  12.500   0.9549   0.10588   0.10142  -0.0471   0.0242   1.0000
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