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AG46c -03f (ag46c03-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: AG46c -03f (ag46c03-il)
Reynolds number: 50,000
Max Cl/Cd: 33.28 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ag46c03-il-50000-n5.txt
Download as CSV file: xf-ag46c03-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.5934   0.11852   0.11179   0.0269   1.0000   0.0949
  -7.750  -0.6004   0.11635   0.10973   0.0215   1.0000   0.0972
  -7.500  -0.6048   0.11355   0.10708   0.0160   1.0000   0.0978
  -7.250  -0.5877   0.10750   0.10098   0.0195   1.0000   0.0994
  -7.000  -0.5794   0.10336   0.09687   0.0190   1.0000   0.1010
  -6.750  -0.5737   0.09950   0.09306   0.0174   1.0000   0.1022
  -6.250  -0.5548   0.08681   0.08031   0.0031   1.0000   0.0556
  -6.000  -0.5448   0.08229   0.07581   0.0019   1.0000   0.0514
  -5.750  -0.5280   0.07444   0.06777  -0.0094   1.0000   0.0439
  -5.500  -0.5160   0.07018   0.06351  -0.0105   1.0000   0.0427
  -5.250  -0.5011   0.06544   0.05869  -0.0133   1.0000   0.0416
  -5.000  -0.4839   0.06045   0.05356  -0.0166   1.0000   0.0405
  -4.750  -0.4644   0.05541   0.04830  -0.0198   1.0000   0.0399
  -4.500  -0.4428   0.05054   0.04313  -0.0227   1.0000   0.0402
  -4.250  -0.4193   0.04590   0.03808  -0.0251   1.0000   0.0412
  -4.000  -0.3942   0.04155   0.03322  -0.0268   1.0000   0.0421
  -3.750  -0.3683   0.03765   0.02879  -0.0278   1.0000   0.0426
  -3.500  -0.3415   0.03412   0.02470  -0.0284   1.0000   0.0429
  -3.250  -0.3139   0.03098   0.02093  -0.0285   1.0000   0.0436
  -3.000  -0.2861   0.02822   0.01768  -0.0283   1.0000   0.0450
  -2.750  -0.2603   0.02630   0.01565  -0.0283   1.0000   0.0505
  -2.500  -0.2322   0.02442   0.01334  -0.0277   1.0000   0.0561
  -2.250  -0.2055   0.02256   0.01136  -0.0270   1.0000   0.0611
  -2.000  -0.1787   0.02123   0.00992  -0.0265   1.0000   0.0744
  -1.750  -0.1516   0.01991   0.00845  -0.0259   1.0000   0.0915
  -1.500  -0.1247   0.01861   0.00727  -0.0256   1.0000   0.1304
  -1.250  -0.0988   0.01698   0.00633  -0.0257   1.0000   0.2483
  -1.000  -0.0853   0.01457   0.00597  -0.0224   1.0000   0.6585
  -0.750  -0.0435   0.01378   0.00526  -0.0234   1.0000   1.0000
  -0.500  -0.0177   0.01375   0.00483  -0.0231   1.0000   1.0000
  -0.250   0.0079   0.01374   0.00454  -0.0228   1.0000   1.0000
   0.000   0.0331   0.01375   0.00432  -0.0225   1.0000   1.0000
   0.250   0.0579   0.01378   0.00418  -0.0223   1.0000   1.0000
   0.500   0.0822   0.01385   0.00409  -0.0220   1.0000   1.0000
   0.750   0.1055   0.01396   0.00411  -0.0217   1.0000   1.0000
   1.000   0.1284   0.01414   0.00421  -0.0217   0.9990   1.0000
   1.250   0.1761   0.01436   0.00431  -0.0261   0.9647   1.0000
   1.500   0.2214   0.01456   0.00441  -0.0298   0.9302   1.0000
   1.750   0.2630   0.01474   0.00451  -0.0324   0.8954   1.0000
   2.000   0.2997   0.01494   0.00463  -0.0337   0.8611   1.0000
   2.250   0.3315   0.01517   0.00476  -0.0338   0.8290   1.0000
   2.500   0.3590   0.01544   0.00492  -0.0331   0.7981   1.0000
   2.750   0.3847   0.01574   0.00512  -0.0319   0.7690   1.0000
   3.000   0.4095   0.01609   0.00536  -0.0306   0.7411   1.0000
   3.250   0.4339   0.01647   0.00565  -0.0293   0.7140   1.0000
   3.500   0.4585   0.01686   0.00605  -0.0281   0.6848   1.0000
   3.750   0.4829   0.01718   0.00638  -0.0270   0.6541   1.0000
   4.000   0.5074   0.01745   0.00666  -0.0260   0.6217   1.0000
   4.250   0.5317   0.01770   0.00691  -0.0248   0.5878   1.0000
   4.500   0.5559   0.01797   0.00721  -0.0236   0.5521   1.0000
   4.750   0.5800   0.01827   0.00746  -0.0223   0.5144   1.0000
   5.000   0.6041   0.01865   0.00778  -0.0213   0.4738   1.0000
   5.250   0.6282   0.01911   0.00816  -0.0203   0.4318   1.0000
   5.500   0.6522   0.01966   0.00862  -0.0194   0.3893   1.0000
   5.750   0.6766   0.02033   0.00927  -0.0188   0.3474   1.0000
   6.000   0.7010   0.02110   0.00997  -0.0183   0.3068   1.0000
   6.250   0.7254   0.02197   0.01080  -0.0179   0.2699   1.0000
   6.500   0.7493   0.02294   0.01172  -0.0174   0.2378   1.0000
   6.750   0.7729   0.02399   0.01280  -0.0170   0.2095   1.0000
   7.000   0.7965   0.02513   0.01399  -0.0166   0.1844   1.0000
   7.250   0.8197   0.02636   0.01529  -0.0160   0.1629   1.0000
   7.500   0.8426   0.02767   0.01668  -0.0155   0.1434   1.0000
   7.750   0.8649   0.02910   0.01813  -0.0150   0.1271   1.0000
   8.000   0.8874   0.03071   0.01991  -0.0144   0.1123   1.0000
   8.250   0.9091   0.03238   0.02184  -0.0139   0.0983   1.0000
   8.500   0.9308   0.03437   0.02404  -0.0133   0.0883   1.0000
   8.750   0.9510   0.03639   0.02640  -0.0128   0.0772   1.0000
   9.000   0.9705   0.03919   0.02957  -0.0121   0.0704   1.0000
   9.250   0.9885   0.04176   0.03242  -0.0116   0.0640   1.0000
   9.500   1.0028   0.04504   0.03619  -0.0113   0.0579   1.0000
   9.750   1.0149   0.04872   0.04035  -0.0110   0.0540   1.0000
  10.000   1.0256   0.05224   0.04415  -0.0107   0.0514   1.0000
  10.250   1.0300   0.05667   0.04891  -0.0108   0.0494   1.0000
  10.500   1.0228   0.06241   0.05523  -0.0118   0.0483   1.0000
  10.750   1.0096   0.06830   0.06150  -0.0137   0.0479   1.0000
  11.000   0.9916   0.07417   0.06758  -0.0164   0.0481   1.0000
  11.250   0.9730   0.08101   0.07453  -0.0215   0.0487   1.0000
  11.500   0.9557   0.08877   0.08233  -0.0274   0.0493   1.0000
  11.750   0.9401   0.09707   0.09064  -0.0332   0.0498   1.0000
  12.000   0.9266   0.10545   0.09900  -0.0384   0.0501   1.0000
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