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AG45c -03f (ag45c03-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: AG45c -03f (ag45c03-il)
Reynolds number: 50,000
Max Cl/Cd: 34.89 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ag45c03-il-50000-n5.txt
Download as CSV file: xf-ag45c03-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG45c -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  -0.4566   0.10796   0.10173   0.0100   1.0000   0.1020
  -7.750  -0.4640   0.10481   0.09866   0.0072   1.0000   0.1029
  -7.500  -0.4673   0.10113   0.09503   0.0049   1.0000   0.1031
  -7.250  -0.4498   0.09257   0.08637   0.0047   1.0000   0.0603
  -7.000  -0.4463   0.08830   0.08210   0.0041   1.0000   0.0578
  -6.750  -0.4463   0.08386   0.07771   0.0024   1.0000   0.0556
  -6.500  -0.5382   0.08937   0.08295   0.0041   1.0000   0.0478
  -6.250  -0.5295   0.08493   0.07854   0.0014   1.0000   0.0465
  -6.000  -0.5196   0.08014   0.07376  -0.0027   1.0000   0.0456
  -5.750  -0.5079   0.07510   0.06870  -0.0072   1.0000   0.0448
  -5.500  -0.4944   0.06991   0.06346  -0.0117   1.0000   0.0443
  -5.250  -0.4789   0.06463   0.05803  -0.0161   1.0000   0.0439
  -5.000  -0.4614   0.05934   0.05257  -0.0202   1.0000   0.0435
  -4.750  -0.4418   0.05411   0.04710  -0.0237   1.0000   0.0430
  -4.500  -0.4202   0.04893   0.04159  -0.0267   1.0000   0.0422
  -4.250  -0.3966   0.04397   0.03618  -0.0291   1.0000   0.0414
  -4.000  -0.3716   0.03956   0.03127  -0.0306   1.0000   0.0410
  -3.750  -0.3455   0.03576   0.02693  -0.0316   1.0000   0.0413
  -3.500  -0.3187   0.03249   0.02315  -0.0320   1.0000   0.0421
  -3.250  -0.2914   0.02988   0.02006  -0.0321   1.0000   0.0453
  -3.000  -0.2628   0.02756   0.01711  -0.0319   1.0000   0.0493
  -2.750  -0.2364   0.02534   0.01472  -0.0316   1.0000   0.0527
  -2.500  -0.2093   0.02363   0.01278  -0.0310   1.0000   0.0582
  -2.250  -0.1826   0.02218   0.01122  -0.0305   1.0000   0.0687
  -2.000  -0.1557   0.02078   0.00972  -0.0299   1.0000   0.0821
  -1.750  -0.1286   0.01951   0.00847  -0.0296   1.0000   0.1099
  -1.500  -0.1019   0.01812   0.00743  -0.0297   1.0000   0.1799
  -1.250  -0.0775   0.01649   0.00675  -0.0297   1.0000   0.3524
  -1.000  -0.0650   0.01464   0.00655  -0.0254   1.0000   0.7102
  -0.750  -0.0234   0.01402   0.00590  -0.0269   1.0000   1.0000
  -0.500   0.0015   0.01403   0.00558  -0.0267   1.0000   1.0000
  -0.250   0.0255   0.01408   0.00536  -0.0266   1.0000   1.0000
   0.000   0.0525   0.01420   0.00526  -0.0272   0.9928   1.0000
   0.250   0.0991   0.01436   0.00512  -0.0314   0.9526   1.0000
   0.500   0.1434   0.01452   0.00499  -0.0347   0.9147   1.0000
   0.750   0.1833   0.01469   0.00492  -0.0369   0.8790   1.0000
   1.000   0.2180   0.01489   0.00488  -0.0379   0.8468   1.0000
   1.250   0.2481   0.01512   0.00487  -0.0378   0.8181   1.0000
   1.500   0.2754   0.01540   0.00493  -0.0372   0.7924   1.0000
   1.750   0.3016   0.01570   0.00503  -0.0363   0.7694   1.0000
   2.000   0.3273   0.01603   0.00520  -0.0355   0.7473   1.0000
   2.250   0.3529   0.01639   0.00540  -0.0346   0.7271   1.0000
   2.500   0.3786   0.01677   0.00566  -0.0338   0.7071   1.0000
   2.750   0.4044   0.01715   0.00597  -0.0332   0.6860   1.0000
   3.000   0.4301   0.01749   0.00627  -0.0326   0.6655   1.0000
   3.250   0.4559   0.01780   0.00660  -0.0320   0.6444   1.0000
   3.500   0.4815   0.01808   0.00686  -0.0313   0.6242   1.0000
   3.750   0.5072   0.01836   0.00713  -0.0306   0.6035   1.0000
   4.000   0.5327   0.01863   0.00739  -0.0298   0.5826   1.0000
   4.250   0.5583   0.01890   0.00767  -0.0291   0.5613   1.0000
   4.500   0.5837   0.01918   0.00801  -0.0283   0.5397   1.0000
   4.750   0.6091   0.01949   0.00834  -0.0276   0.5169   1.0000
   5.000   0.6343   0.01981   0.00864  -0.0268   0.4947   1.0000
   5.250   0.6599   0.02017   0.00906  -0.0262   0.4701   1.0000
   5.500   0.6852   0.02056   0.00955  -0.0255   0.4452   1.0000
   5.750   0.7104   0.02099   0.01000  -0.0249   0.4200   1.0000
   6.000   0.7353   0.02145   0.01050  -0.0242   0.3944   1.0000
   6.250   0.7600   0.02195   0.01103  -0.0236   0.3682   1.0000
   6.500   0.7846   0.02253   0.01171  -0.0230   0.3413   1.0000
   6.750   0.8088   0.02318   0.01242  -0.0224   0.3141   1.0000
   7.000   0.8327   0.02392   0.01322  -0.0219   0.2873   1.0000
   7.250   0.8563   0.02475   0.01412  -0.0214   0.2612   1.0000
   7.500   0.8793   0.02568   0.01510  -0.0209   0.2357   1.0000
   7.750   0.9018   0.02671   0.01623  -0.0204   0.2122   1.0000
   8.000   0.9237   0.02784   0.01742  -0.0198   0.1896   1.0000
   8.250   0.9452   0.02911   0.01882  -0.0194   0.1674   1.0000
   8.500   0.9657   0.03049   0.02024  -0.0188   0.1485   1.0000
   8.750   0.9858   0.03204   0.02196  -0.0183   0.1294   1.0000
   9.000   1.0050   0.03380   0.02388  -0.0177   0.1136   1.0000
   9.250   1.0230   0.03560   0.02589  -0.0171   0.0988   1.0000
   9.500   1.0405   0.03781   0.02831  -0.0164   0.0878   1.0000
   9.750   1.0561   0.03998   0.03066  -0.0158   0.0772   1.0000
  10.000   1.0714   0.04230   0.03307  -0.0151   0.0700   1.0000
  10.250   1.0839   0.04550   0.03676  -0.0144   0.0634   1.0000
  10.500   1.0956   0.04771   0.03896  -0.0139   0.0576   1.0000
  10.750   1.1014   0.05180   0.04362  -0.0134   0.0542   1.0000
  11.000   1.1024   0.05611   0.04841  -0.0132   0.0519   1.0000
  11.250   1.0994   0.06023   0.05286  -0.0134   0.0498   1.0000
  11.500   1.0940   0.06393   0.05675  -0.0136   0.0480   1.0000
  11.750   1.0925   0.06700   0.05981  -0.0138   0.0459   1.0000
  12.000   1.0768   0.07243   0.06543  -0.0164   0.0456   1.0000
  12.250   1.0591   0.07884   0.07204  -0.0206   0.0457   1.0000
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