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AG04 (ag04-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: AG04 (ag04-il)
Reynolds number: 50,000
Max Cl/Cd: 32 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ag04-il-50000.txt
Download as CSV file: xf-ag04-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG04                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.5714   0.11486   0.10829   0.0200   1.0000   0.1872
  -8.250  -0.5585   0.10997   0.10337   0.0208   1.0000   0.1952
  -8.000  -0.5711   0.10880   0.10238   0.0167   1.0000   0.2019
  -7.750  -0.5520   0.10328   0.09680   0.0187   1.0000   0.2122
  -7.500  -0.5501   0.09977   0.09337   0.0174   1.0000   0.2197
  -7.250  -0.5586   0.09807   0.09178   0.0125   1.0000   0.2299
  -7.000  -0.5422   0.09312   0.08685   0.0152   1.0000   0.2415
  -6.750  -0.5331   0.08914   0.08291   0.0149   1.0000   0.2527
  -6.500  -0.5258   0.08545   0.07928   0.0138   1.0000   0.2659
  -6.250  -0.5188   0.08194   0.07582   0.0122   1.0000   0.2821
  -6.000  -0.5137   0.07854   0.07248   0.0091   1.0000   0.3007
  -5.750  -0.4996   0.07463   0.06860   0.0120   1.0000   0.3213
  -5.500  -0.4906   0.07139   0.06542   0.0129   1.0000   0.3518
  -5.250  -0.4822   0.06810   0.06219   0.0143   1.0000   0.3855
  -5.000  -0.4046   0.04724   0.03970  -0.0336   1.0000   0.1317
  -4.750  -0.3800   0.04242   0.03459  -0.0351   1.0000   0.1276
  -4.500  -0.3490   0.03688   0.02803  -0.0377   1.0000   0.1186
  -4.250  -0.3212   0.03288   0.02346  -0.0381   1.0000   0.1181
  -4.000  -0.2951   0.02996   0.02030  -0.0379   1.0000   0.1275
  -3.750  -0.2672   0.02718   0.01710  -0.0377   1.0000   0.1397
  -3.500  -0.2391   0.02486   0.01428  -0.0372   1.0000   0.1614
  -3.250  -0.2124   0.02271   0.01214  -0.0364   1.0000   0.1924
  -3.000  -0.1861   0.02095   0.01042  -0.0355   1.0000   0.2448
  -2.750  -0.1609   0.01936   0.00915  -0.0345   1.0000   0.3187
  -2.500  -0.1363   0.01769   0.00803  -0.0332   1.0000   0.4343
  -2.250  -0.1217   0.01538   0.00715  -0.0289   1.0000   0.6613
  -2.000  -0.0747   0.01413   0.00581  -0.0308   1.0000   1.0000
  -1.750  -0.0489   0.01410   0.00531  -0.0306   1.0000   1.0000
  -1.500  -0.0239   0.01409   0.00494  -0.0302   1.0000   1.0000
  -1.250   0.0006   0.01411   0.00467  -0.0298   1.0000   1.0000
  -1.000   0.0249   0.01414   0.00443  -0.0293   1.0000   1.0000
  -0.750   0.0489   0.01420   0.00429  -0.0288   1.0000   1.0000
  -0.500   0.0727   0.01428   0.00422  -0.0283   1.0000   1.0000
  -0.250   0.0962   0.01439   0.00420  -0.0278   1.0000   1.0000
   0.000   0.1195   0.01453   0.00423  -0.0274   1.0000   1.0000
   0.250   0.1424   0.01471   0.00433  -0.0270   1.0000   1.0000
   0.500   0.1649   0.01494   0.00451  -0.0266   1.0000   1.0000
   0.750   0.1872   0.01523   0.00477  -0.0264   1.0000   1.0000
   1.000   0.2092   0.01558   0.00512  -0.0263   1.0000   1.0000
   1.250   0.2305   0.01603   0.00557  -0.0264   1.0000   1.0000
   1.500   0.2510   0.01659   0.00615  -0.0266   1.0000   1.0000
   1.750   0.2707   0.01728   0.00688  -0.0272   1.0000   1.0000
   2.000   0.2893   0.01814   0.00780  -0.0280   1.0000   1.0000
   2.250   0.3729   0.01899   0.00892  -0.0403   0.9623   1.0000
   2.500   0.4605   0.01922   0.00948  -0.0513   0.9167   1.0000
   2.750   0.5197   0.01912   0.00968  -0.0551   0.8700   1.0000
   3.000   0.5542   0.01911   0.00980  -0.0539   0.8219   1.0000
   3.250   0.5799   0.01918   0.00989  -0.0507   0.7756   1.0000
   3.500   0.6010   0.01943   0.01011  -0.0472   0.7275   1.0000
   3.750   0.6220   0.01977   0.01043  -0.0437   0.6798   1.0000
   4.000   0.6433   0.02024   0.01081  -0.0407   0.6311   1.0000
   4.250   0.6651   0.02080   0.01125  -0.0381   0.5830   1.0000
   4.500   0.6873   0.02148   0.01180  -0.0357   0.5357   1.0000
   4.750   0.7098   0.02226   0.01248  -0.0337   0.4886   1.0000
   5.000   0.7325   0.02313   0.01328  -0.0318   0.4438   1.0000
   5.250   0.7554   0.02413   0.01413  -0.0301   0.4005   1.0000
   5.500   0.7781   0.02526   0.01515  -0.0286   0.3577   1.0000
   5.750   0.8008   0.02653   0.01632  -0.0272   0.3164   1.0000
   6.000   0.8231   0.02792   0.01765  -0.0258   0.2763   1.0000
   6.250   0.8455   0.02967   0.01951  -0.0246   0.2396   1.0000
   6.500   0.8681   0.03158   0.02143  -0.0234   0.2085   1.0000
   6.750   0.8899   0.03356   0.02339  -0.0223   0.1802   1.0000
   7.000   0.9113   0.03668   0.02702  -0.0212   0.1608   1.0000
   7.250   0.9320   0.03910   0.02954  -0.0202   0.1416   1.0000
   7.500   0.9494   0.04308   0.03412  -0.0192   0.1306   1.0000
   7.750   0.9653   0.04742   0.03886  -0.0184   0.1232   1.0000
   8.000   0.9817   0.05066   0.04220  -0.0176   0.1121   1.0000
   8.250   0.9857   0.05658   0.04892  -0.0173   0.1105   1.0000
   8.500   0.9861   0.06287   0.05574  -0.0176   0.1107   1.0000
   8.750   0.9843   0.06922   0.06243  -0.0183   0.1115   1.0000
   9.000   0.9829   0.07548   0.06889  -0.0191   0.1124   1.0000
   9.250   0.9335   0.08642   0.08021  -0.0278   0.1228   1.0000
   9.500   0.9219   0.09368   0.08748  -0.0318   0.1273   1.0000
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