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NACA 65-209 (naca65209-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 65-209 (naca65209-il)
Reynolds number: 50,000
Max Cl/Cd: 24.86 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca65209-il-50000.txt
Download as CSV file: xf-naca65209-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65-209                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5160   0.11108   0.10406  -0.0045   1.0000   0.2735
  -9.250  -0.5085   0.10777   0.10078  -0.0039   1.0000   0.2927
  -9.000  -0.5166   0.10573   0.09884  -0.0041   1.0000   0.3110
  -8.750  -0.4985   0.10174   0.09483  -0.0023   1.0000   0.3370
  -8.500  -0.4871   0.09830   0.09142  -0.0008   1.0000   0.3635
  -8.250  -0.4775   0.09497   0.08807   0.0004   1.0000   0.3879
  -7.500  -0.4495   0.08576   0.07896   0.0048   1.0000   0.4694
  -5.750  -0.5404   0.04724   0.03950  -0.0332   1.0000   0.1686
  -5.500  -0.5222   0.04317   0.03454  -0.0327   1.0000   0.1424
  -5.250  -0.5030   0.03996   0.03059  -0.0313   1.0000   0.1293
  -5.000  -0.4839   0.03659   0.02702  -0.0301   1.0000   0.1244
  -4.750  -0.4631   0.03389   0.02381  -0.0287   1.0000   0.1199
  -4.500  -0.4423   0.03172   0.02131  -0.0274   1.0000   0.1223
  -4.250  -0.4203   0.02976   0.01899  -0.0260   1.0000   0.1247
  -4.000  -0.3969   0.02792   0.01683  -0.0246   1.0000   0.1253
  -3.750  -0.3729   0.02634   0.01499  -0.0230   1.0000   0.1278
  -3.500  -0.3502   0.02484   0.01351  -0.0213   1.0000   0.1347
  -3.250  -0.0886   0.02047   0.01131  -0.0408   1.0000   1.0000
  -3.000  -0.0803   0.02011   0.01079  -0.0390   1.0000   1.0000
  -2.750  -0.0743   0.01983   0.01038  -0.0367   1.0000   1.0000
  -2.500  -0.0710   0.01961   0.01006  -0.0340   1.0000   1.0000
  -2.250  -0.0711   0.01945   0.00982  -0.0307   1.0000   1.0000
  -2.000  -0.0741   0.01932   0.00963  -0.0270   1.0000   1.0000
  -1.750  -0.0792   0.01920   0.00946  -0.0230   1.0000   1.0000
  -1.500  -0.0855   0.01907   0.00927  -0.0187   1.0000   1.0000
  -1.250  -0.0922   0.01892   0.00906  -0.0145   1.0000   1.0000
  -1.000  -0.0981   0.01875   0.00882  -0.0103   1.0000   1.0000
  -0.750  -0.1010   0.01860   0.00854  -0.0066   1.0000   1.0000
  -0.500  -0.0971   0.01853   0.00835  -0.0039   1.0000   1.0000
  -0.250  -0.0860   0.01858   0.00824  -0.0025   1.0000   1.0000
   0.000  -0.0707   0.01871   0.00823  -0.0016   1.0000   1.0000
   0.250  -0.0531   0.01891   0.00829  -0.0012   1.0000   1.0000
   0.500  -0.0343   0.01916   0.00843  -0.0009   1.0000   1.0000
   0.750  -0.0149   0.01946   0.00861  -0.0007   1.0000   1.0000
   1.000   0.0049   0.01980   0.00887  -0.0005   1.0000   1.0000
   1.250   0.0249   0.02018   0.00918  -0.0005   1.0000   1.0000
   1.500   0.0450   0.02060   0.00956  -0.0004   1.0000   1.0000
   1.750   0.0650   0.02105   0.00999  -0.0004   1.0000   1.0000
   2.000   0.0850   0.02154   0.01047  -0.0004   1.0000   1.0000
   2.250   0.1049   0.02207   0.01101  -0.0004   1.0000   1.0000
   2.500   0.1247   0.02264   0.01161  -0.0005   1.0000   1.0000
   2.750   0.1442   0.02325   0.01226  -0.0005   1.0000   1.0000
   3.000   0.1636   0.02391   0.01301  -0.0006   1.0000   1.0000
   3.250   0.1827   0.02461   0.01379  -0.0008   1.0000   1.0000
   3.500   0.2016   0.02536   0.01464  -0.0009   1.0000   1.0000
   3.750   0.2200   0.02617   0.01556  -0.0011   1.0000   1.0000
   4.000   0.2695   0.02788   0.01755  -0.0073   0.9842   1.0000
   4.250   0.3174   0.02946   0.01948  -0.0129   0.9654   1.0000
   4.500   0.3704   0.03107   0.02150  -0.0191   0.9429   1.0000
   4.750   0.5846   0.02352   0.01221  -0.0175   0.1805   1.0000
   5.000   0.6028   0.02538   0.01381  -0.0158   0.1494   1.0000
   5.250   0.6346   0.02730   0.01569  -0.0154   0.1340   1.0000
   5.500   0.6733   0.02942   0.01786  -0.0157   0.1231   1.0000
   5.750   0.7067   0.03180   0.02037  -0.0158   0.1143   1.0000
   6.000   0.7380   0.03444   0.02336  -0.0154   0.1123   1.0000
   6.250   0.7660   0.03739   0.02675  -0.0146   0.1129   1.0000
   6.500   0.7910   0.04070   0.03057  -0.0136   0.1146   1.0000
   6.750   0.8114   0.04402   0.03439  -0.0124   0.1151   1.0000
   7.000   0.8288   0.04757   0.03842  -0.0111   0.1158   1.0000
   7.250   0.8448   0.05139   0.04284  -0.0096   0.1219   1.0000
   7.500   0.8606   0.05677   0.04856  -0.0088   0.1317   1.0000
   7.750   0.8577   0.06174   0.05458  -0.0075   0.1535   1.0000
   8.000   0.8565   0.06889   0.06234  -0.0088   0.1898   1.0000
   8.250   0.8208   0.07648   0.07032  -0.0128   0.2214   1.0000
   8.500   0.7233   0.09186   0.08546  -0.0329   0.3215   1.0000
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