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AG38 (ag38-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: AG38 (ag38-il)
Reynolds number: 100,000
Max Cl/Cd: 49.13 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ag38-il-100000.txt
Download as CSV file: xf-ag38-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG38                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5099   0.09665   0.09175  -0.0039   1.0000   0.0796
  -8.750  -0.5135   0.09346   0.08864  -0.0085   1.0000   0.0826
  -8.500  -0.5138   0.08940   0.08454  -0.0226   1.0000   0.0842
  -8.250  -0.5045   0.08473   0.07998  -0.0151   1.0000   0.0872
  -8.000  -0.4946   0.08146   0.07673  -0.0146   1.0000   0.0916
  -7.750  -0.4862   0.07708   0.07211  -0.0296   1.0000   0.0983
  -7.500  -0.4773   0.07203   0.06722  -0.0264   1.0000   0.1005
  -7.250  -0.4656   0.06898   0.06421  -0.0244   1.0000   0.1048
  -7.000  -0.4514   0.06410   0.05909  -0.0321   1.0000   0.1140
  -6.750  -0.4391   0.06103   0.05613  -0.0293   1.0000   0.1184
  -6.500  -0.4228   0.05690   0.05179  -0.0329   1.0000   0.1293
  -6.250  -0.4053   0.05363   0.04832  -0.0349   1.0000   0.1426
  -6.000  -0.3906   0.05064   0.04546  -0.0330   1.0000   0.1498
  -5.750  -0.3727   0.04759   0.04230  -0.0336   1.0000   0.1653
  -5.500  -0.3544   0.04456   0.03913  -0.0344   1.0000   0.1871
  -5.250  -0.3370   0.04224   0.03677  -0.0338   1.0000   0.2154
  -4.750  -0.2525   0.02891   0.02111  -0.0386   1.0000   0.0827
  -4.500  -0.2235   0.02579   0.01720  -0.0376   1.0000   0.0713
  -4.250  -0.1977   0.02353   0.01466  -0.0368   1.0000   0.0694
  -4.000  -0.1714   0.02166   0.01247  -0.0359   1.0000   0.0696
  -3.750  -0.1458   0.01983   0.01052  -0.0354   1.0000   0.0743
  -3.500  -0.1198   0.01851   0.00912  -0.0346   1.0000   0.0780
  -3.250  -0.0934   0.01742   0.00790  -0.0337   1.0000   0.0834
  -3.000  -0.0678   0.01632   0.00690  -0.0331   1.0000   0.0967
  -2.750  -0.0417   0.01520   0.00595  -0.0326   1.0000   0.1175
  -2.500  -0.0130   0.01120   0.00515  -0.0313   1.0000   1.0000
  -2.250   0.0117   0.01127   0.00484  -0.0306   1.0000   1.0000
  -2.000   0.0362   0.01136   0.00467  -0.0301   1.0000   1.0000
  -1.750   0.0605   0.01148   0.00460  -0.0296   1.0000   1.0000
  -1.500   0.0846   0.01163   0.00460  -0.0292   1.0000   1.0000
  -1.250   0.1085   0.01181   0.00467  -0.0288   1.0000   1.0000
  -1.000   0.1320   0.01205   0.00479  -0.0285   1.0000   1.0000
  -0.750   0.1550   0.01234   0.00502  -0.0282   1.0000   1.0000
  -0.500   0.1772   0.01271   0.00535  -0.0281   1.0000   1.0000
  -0.250   0.2103   0.01313   0.00572  -0.0303   0.9954   1.0000
   0.000   0.2724   0.01325   0.00582  -0.0376   0.9762   1.0000
   0.250   0.3343   0.01319   0.00578  -0.0446   0.9570   1.0000
   0.500   0.3881   0.01297   0.00562  -0.0494   0.9328   1.0000
   0.750   0.4330   0.01270   0.00539  -0.0521   0.9041   1.0000
   1.000   0.4704   0.01244   0.00516  -0.0530   0.8708   1.0000
   1.250   0.5036   0.01227   0.00494  -0.0529   0.8364   1.0000
   1.500   0.5325   0.01231   0.00487  -0.0520   0.8010   1.0000
   1.750   0.5579   0.01252   0.00498  -0.0507   0.7636   1.0000
   2.000   0.5827   0.01278   0.00515  -0.0494   0.7288   1.0000
   2.250   0.6072   0.01306   0.00534  -0.0482   0.6928   1.0000
   2.500   0.6317   0.01333   0.00551  -0.0469   0.6576   1.0000
   2.750   0.6561   0.01367   0.00571  -0.0458   0.6224   1.0000
   3.000   0.6803   0.01412   0.00604  -0.0446   0.5869   1.0000
   3.250   0.7045   0.01460   0.00641  -0.0436   0.5498   1.0000
   3.500   0.7285   0.01506   0.00675  -0.0426   0.5120   1.0000
   3.750   0.7523   0.01544   0.00708  -0.0416   0.4698   1.0000
   4.000   0.7757   0.01579   0.00738  -0.0407   0.4230   1.0000
   4.250   0.7986   0.01627   0.00771  -0.0397   0.3719   1.0000
   4.500   0.8209   0.01698   0.00819  -0.0388   0.3185   1.0000
   4.750   0.8425   0.01790   0.00884  -0.0379   0.2657   1.0000
   5.000   0.8636   0.01902   0.00973  -0.0370   0.2148   1.0000
   5.250   0.8844   0.02034   0.01079  -0.0360   0.1722   1.0000
   5.500   0.9054   0.02184   0.01204  -0.0351   0.1425   1.0000
   5.750   0.9280   0.02320   0.01343  -0.0342   0.1209   1.0000
   6.000   0.9509   0.02479   0.01500  -0.0335   0.1069   1.0000
   6.250   0.9739   0.02639   0.01669  -0.0327   0.0955   1.0000
   6.500   0.9977   0.02858   0.01881  -0.0322   0.0883   1.0000
   6.750   1.0212   0.03042   0.02101  -0.0313   0.0820   1.0000
   7.000   1.0432   0.03292   0.02347  -0.0309   0.0760   1.0000
   7.250   1.0637   0.03535   0.02650  -0.0296   0.0729   1.0000
   7.500   1.0820   0.03838   0.03006  -0.0282   0.0705   1.0000
   7.750   1.1001   0.04099   0.03291  -0.0272   0.0673   1.0000
   8.000   1.1141   0.04531   0.03734  -0.0266   0.0642   1.0000
   8.250   1.1215   0.04901   0.04166  -0.0246   0.0634   1.0000
   8.500   1.1255   0.05361   0.04679  -0.0228   0.0634   1.0000
   8.750   1.1258   0.05879   0.05239  -0.0212   0.0636   1.0000
   9.000   1.1254   0.06444   0.05836  -0.0199   0.0642   1.0000
   9.250   0.9949   0.05961   0.05460  -0.0069   0.0677   1.0000
   9.500   0.9484   0.06586   0.06108  -0.0060   0.0693   1.0000
   9.750   0.9037   0.07381   0.06918  -0.0089   0.0710   1.0000
  10.000   0.8654   0.08333   0.07874  -0.0136   0.0737   1.0000
  10.250   0.8447   0.09116   0.08657  -0.0165   0.0752   1.0000
  10.500   0.8318   0.09799   0.09340  -0.0183   0.0761   1.0000
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