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NACA 64-209 (naca64209-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 64-209 (naca64209-il)
Reynolds number: 50,000
Max Cl/Cd: 31.5 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca64209-il-50000.txt
Download as CSV file: xf-naca64209-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-209                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5191   0.10901   0.10199   0.0026   1.0000   0.2931
  -9.000  -0.5123   0.10587   0.09888   0.0032   1.0000   0.3133
  -8.750  -0.5228   0.10413   0.09724   0.0029   1.0000   0.3311
  -8.500  -0.5017   0.09987   0.09296   0.0048   1.0000   0.3578
  -8.250  -0.4859   0.09596   0.08905   0.0060   1.0000   0.3815
  -7.750  -0.4712   0.08991   0.08307   0.0079   1.0000   0.4272
  -7.500  -0.4620   0.08647   0.07967   0.0088   1.0000   0.4484
  -7.250  -0.4684   0.08490   0.07819   0.0105   1.0000   0.4730
  -7.000  -0.4396   0.07980   0.07305   0.0107   1.0000   0.4938
  -6.750  -0.4344   0.07662   0.06988   0.0111   1.0000   0.5068
  -6.500  -0.5033   0.04815   0.04220  -0.0265   1.0000   0.2367
  -6.250  -0.5537   0.05081   0.04305  -0.0372   1.0000   0.1608
  -6.000  -0.5362   0.04603   0.03779  -0.0373   1.0000   0.1459
  -5.750  -0.5181   0.04175   0.03314  -0.0368   1.0000   0.1372
  -5.500  -0.4977   0.03827   0.02901  -0.0360   1.0000   0.1297
  -5.250  -0.4768   0.03506   0.02535  -0.0351   1.0000   0.1271
  -5.000  -0.4550   0.03260   0.02232  -0.0340   1.0000   0.1313
  -4.750  -0.4343   0.03025   0.01987  -0.0329   1.0000   0.1418
  -4.500  -0.4105   0.02827   0.01739  -0.0316   1.0000   0.1461
  -4.250  -0.3882   0.02637   0.01549  -0.0304   1.0000   0.1545
  -4.000  -0.3645   0.02496   0.01383  -0.0289   1.0000   0.1585
  -3.750  -0.3414   0.02379   0.01252  -0.0272   1.0000   0.1617
  -3.500  -0.3206   0.02269   0.01147  -0.0255   1.0000   0.1667
  -3.250  -0.3000   0.02184   0.01053  -0.0239   1.0000   0.1739
  -3.000  -0.2808   0.02093   0.00966  -0.0225   1.0000   0.1850
  -2.750  -0.2610   0.01995   0.00878  -0.0215   1.0000   0.2061
  -2.500  -0.2497   0.01737   0.00843  -0.0191   1.0000   0.5522
  -2.250  -0.2547   0.01745   0.00920  -0.0092   1.0000   0.7659
  -2.000  -0.0472   0.01850   0.00915  -0.0294   1.0000   1.0000
  -1.750  -0.0529   0.01832   0.00896  -0.0256   1.0000   1.0000
  -1.500  -0.0637   0.01817   0.00879  -0.0210   1.0000   1.0000
  -1.250  -0.0775   0.01799   0.00860  -0.0161   1.0000   1.0000
  -1.000  -0.0903   0.01778   0.00836  -0.0114   1.0000   1.0000
  -0.750  -0.0952   0.01764   0.00812  -0.0078   1.0000   1.0000
  -0.500  -0.0866   0.01765   0.00797  -0.0063   1.0000   1.0000
  -0.250  -0.0714   0.01778   0.00792  -0.0058   1.0000   1.0000
   0.000  -0.0533   0.01800   0.00797  -0.0057   1.0000   1.0000
   0.250  -0.0341   0.01828   0.00811  -0.0057   1.0000   1.0000
   0.500  -0.0143   0.01862   0.00832  -0.0058   1.0000   1.0000
   0.750   0.0056   0.01900   0.00860  -0.0060   1.0000   1.0000
   1.000   0.0256   0.01943   0.00893  -0.0061   1.0000   1.0000
   1.250   0.0456   0.01990   0.00933  -0.0063   1.0000   1.0000
   1.500   0.0655   0.02041   0.00979  -0.0065   1.0000   1.0000
   1.750   0.0853   0.02096   0.01031  -0.0066   1.0000   1.0000
   2.000   0.1050   0.02155   0.01089  -0.0068   1.0000   1.0000
   2.250   0.1245   0.02218   0.01152  -0.0071   1.0000   1.0000
   2.500   0.1438   0.02286   0.01221  -0.0073   1.0000   1.0000
   2.750   0.1798   0.02393   0.01336  -0.0108   0.9916   1.0000
   3.000   0.2223   0.02518   0.01475  -0.0154   0.9794   1.0000
   3.250   0.2641   0.02640   0.01612  -0.0197   0.9665   1.0000
   3.500   0.3049   0.02760   0.01749  -0.0237   0.9527   1.0000
   3.750   0.3442   0.02874   0.01886  -0.0273   0.9374   1.0000
   4.000   0.3844   0.02985   0.02026  -0.0308   0.9196   1.0000
   4.250   0.4380   0.03097   0.02177  -0.0360   0.8978   1.0000
   4.500   0.4899   0.03150   0.02277  -0.0396   0.8648   1.0000
   4.750   0.6269   0.01990   0.01065  -0.0236   0.3379   1.0000
   5.000   0.6291   0.02366   0.01273  -0.0201   0.1954   1.0000
   5.250   0.6493   0.02580   0.01458  -0.0187   0.1589   1.0000
   5.500   0.6806   0.02785   0.01656  -0.0180   0.1404   1.0000
   5.750   0.7125   0.03000   0.01865  -0.0178   0.1251   1.0000
   6.000   0.7457   0.03273   0.02147  -0.0177   0.1190   1.0000
   6.250   0.7749   0.03543   0.02461  -0.0170   0.1165   1.0000
   6.500   0.8003   0.03822   0.02785  -0.0162   0.1128   1.0000
   6.750   0.8247   0.04156   0.03126  -0.0158   0.1084   1.0000
   7.000   0.8437   0.04481   0.03534  -0.0142   0.1109   1.0000
   7.250   0.8595   0.04899   0.04020  -0.0128   0.1157   1.0000
   7.500   0.8770   0.05371   0.04520  -0.0122   0.1201   1.0000
   7.750   0.8815   0.05852   0.05089  -0.0109   0.1312   1.0000
   8.000   0.8837   0.06426   0.05721  -0.0106   0.1453   1.0000
   8.250   0.8713   0.07107   0.06459  -0.0120   0.1674   1.0000
   8.500   0.7822   0.06783   0.06192  -0.0079   0.1659   1.0000
   8.750   0.7523   0.07454   0.06868  -0.0093   0.1743   1.0000
   9.000   0.7040   0.08280   0.07691  -0.0150   0.1807   1.0000
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