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NACA6409 9% (n6409-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA6409 9% (n6409-il)
Reynolds number: 200,000
Max Cl/Cd: 87.06 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n6409-il-200000.txt
Download as CSV file: xf-n6409-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA6409 9%                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.1538   0.09258   0.08945  -0.0538   0.9758   0.0433
  -8.250  -0.1400   0.08827   0.08513  -0.0581   0.9729   0.0454
  -8.000  -0.2612   0.10137   0.09814  -0.0427   0.9867   0.0407
  -7.750  -0.2410   0.09775   0.09450  -0.0473   0.9834   0.0424
  -7.500  -0.2266   0.09436   0.09111  -0.0512   0.9766   0.0441
  -7.250  -0.2094   0.09102   0.08777  -0.0591   0.9706   0.0465
  -7.000  -0.1838   0.08679   0.08351  -0.0758   0.9587   0.0476
  -6.750  -0.1741   0.08144   0.07818  -0.0777   0.9512   0.0483
  -6.500  -0.1564   0.07801   0.07475  -0.0753   0.9483   0.0496
  -6.250  -0.1298   0.07446   0.07117  -0.0790   0.9453   0.0516
  -6.000  -0.1113   0.07124   0.06793  -0.0831   0.9374   0.0548
  -5.500  -0.0440   0.06062   0.05715  -0.1038   0.9270   0.0611
  -5.250  -0.0262   0.05817   0.05469  -0.1041   0.9197   0.0631
  -5.000   0.0138   0.05397   0.05038  -0.1120   0.9167   0.0681
  -4.750   0.0565   0.04741   0.04355  -0.1239   0.9102   0.0735
  -4.500   0.0811   0.04531   0.04146  -0.1244   0.9053   0.0760
  -4.250   0.1329   0.03985   0.03560  -0.1346   0.9026   0.0873
  -4.000   0.1811   0.02831   0.02313  -0.1429   0.9005   0.0571
  -3.750   0.2038   0.02449   0.01881  -0.1431   0.8919   0.0547
  -3.500   0.2419   0.02164   0.01536  -0.1454   0.8886   0.0567
  -3.250   0.2816   0.01944   0.01262  -0.1475   0.8862   0.0581
  -3.000   0.3069   0.01794   0.01080  -0.1469   0.8781   0.0603
  -2.750   0.3422   0.01697   0.00977  -0.1482   0.8737   0.0663
  -2.500   0.3804   0.01583   0.00840  -0.1498   0.8706   0.0734
  -2.250   0.4042   0.01530   0.00789  -0.1487   0.8609   0.0820
  -2.000   0.4404   0.01457   0.00710  -0.1500   0.8565   0.0968
  -1.750   0.4655   0.01417   0.00669  -0.1493   0.8468   0.1120
  -1.500   0.5003   0.01360   0.00612  -0.1504   0.8414   0.1325
  -1.250   0.5251   0.01332   0.00589  -0.1495   0.8310   0.1520
  -1.000   0.5548   0.01298   0.00554  -0.1496   0.8227   0.1775
  -0.750   0.5842   0.01265   0.00526  -0.1497   0.8136   0.2080
  -0.500   0.6103   0.01239   0.00511  -0.1492   0.8029   0.2415
  -0.250   0.6388   0.01211   0.00492  -0.1492   0.7935   0.2863
   0.000   0.6665   0.01176   0.00474  -0.1490   0.7833   0.3500
   0.250   0.6996   0.01030   0.00467  -0.1498   0.7722   1.0000
   0.500   0.7269   0.01036   0.00454  -0.1495   0.7607   1.0000
   0.750   0.7548   0.01043   0.00444  -0.1492   0.7498   1.0000
   1.000   0.7823   0.01051   0.00436  -0.1489   0.7384   1.0000
   1.250   0.8077   0.01064   0.00438  -0.1483   0.7258   1.0000
   1.500   0.8336   0.01078   0.00442  -0.1478   0.7138   1.0000
   1.750   0.8599   0.01093   0.00446  -0.1473   0.7023   1.0000
   2.000   0.8869   0.01109   0.00450  -0.1470   0.6916   1.0000
   2.250   0.9124   0.01127   0.00460  -0.1465   0.6803   1.0000
   2.500   0.9376   0.01146   0.00474  -0.1459   0.6692   1.0000
   2.750   0.9638   0.01167   0.00487  -0.1455   0.6594   1.0000
   3.000   0.9901   0.01188   0.00502  -0.1452   0.6498   1.0000
   3.250   1.0148   0.01211   0.00523  -0.1446   0.6398   1.0000
   3.500   1.0414   0.01235   0.00540  -0.1443   0.6314   1.0000
   3.750   1.0664   0.01259   0.00563  -0.1438   0.6223   1.0000
   4.000   1.0920   0.01285   0.00589  -0.1434   0.6141   1.0000
   4.250   1.1178   0.01310   0.00612  -0.1430   0.6060   1.0000
   4.500   1.1427   0.01338   0.00642  -0.1425   0.5980   1.0000
   4.750   1.1689   0.01364   0.00669  -0.1421   0.5905   1.0000
   5.000   1.1932   0.01393   0.00703  -0.1415   0.5827   1.0000
   5.250   1.2194   0.01421   0.00731  -0.1413   0.5754   1.0000
   5.500   1.2432   0.01451   0.00769  -0.1406   0.5676   1.0000
   5.750   1.2693   0.01480   0.00800  -0.1402   0.5603   1.0000
   6.000   1.2920   0.01508   0.00838  -0.1393   0.5513   1.0000
   6.250   1.3141   0.01528   0.00859  -0.1381   0.5391   1.0000
   6.500   1.3321   0.01538   0.00869  -0.1360   0.5215   1.0000
   6.750   1.3492   0.01550   0.00882  -0.1338   0.5031   1.0000
   7.000   1.3668   0.01570   0.00901  -0.1317   0.4859   1.0000
   7.250   1.3839   0.01595   0.00926  -0.1296   0.4688   1.0000
   7.500   1.3994   0.01620   0.00959  -0.1273   0.4508   1.0000
   7.750   1.4137   0.01649   0.00995  -0.1247   0.4305   1.0000
   8.000   1.4259   0.01684   0.01032  -0.1218   0.4072   1.0000
   8.250   1.4336   0.01729   0.01074  -0.1181   0.3743   1.0000
   8.500   1.4307   0.01809   0.01132  -0.1126   0.3236   1.0000
   8.750   1.4176   0.01967   0.01244  -0.1060   0.2503   1.0000
   9.000   1.3971   0.02213   0.01428  -0.0992   0.1621   1.0000
   9.250   1.3785   0.02486   0.01650  -0.0933   0.0965   1.0000
   9.500   1.3681   0.02728   0.01871  -0.0887   0.0685   1.0000
   9.750   1.3637   0.02941   0.02083  -0.0852   0.0574   1.0000
  10.000   1.3571   0.03182   0.02325  -0.0817   0.0513   1.0000
  10.250   1.3582   0.03378   0.02535  -0.0792   0.0475   1.0000
  10.500   1.3586   0.03588   0.02753  -0.0770   0.0445   1.0000
  10.750   1.3548   0.03846   0.03014  -0.0747   0.0421   1.0000
  11.000   1.3528   0.04102   0.03278  -0.0726   0.0400   1.0000
  11.250   1.3576   0.04304   0.03491  -0.0710   0.0380   1.0000
  11.500   1.3620   0.04516   0.03712  -0.0695   0.0366   1.0000
  11.750   1.3672   0.04728   0.03930  -0.0681   0.0352   1.0000
  12.000   1.3739   0.04935   0.04142  -0.0667   0.0340   1.0000
  12.250   1.3870   0.05124   0.04328  -0.0651   0.0326   1.0000
  12.500   1.4057   0.05291   0.04506  -0.0638   0.0314   1.0000
  12.750   1.4168   0.05475   0.04707  -0.0628   0.0304   1.0000
  13.000   1.4293   0.05669   0.04918  -0.0617   0.0293   1.0000
  13.250   1.4449   0.05873   0.05139  -0.0607   0.0286   1.0000
  13.500   1.4592   0.06103   0.05389  -0.0597   0.0279   1.0000
  13.750   1.4711   0.06365   0.05672  -0.0588   0.0275   1.0000
  14.000   1.4789   0.06648   0.05973  -0.0579   0.0269   1.0000
  14.250   1.4821   0.06949   0.06290  -0.0572   0.0263   1.0000
  14.500   1.4881   0.07282   0.06635  -0.0566   0.0255   1.0000
  14.750   1.4897   0.07801   0.07180  -0.0561   0.0250   1.0000
  15.000   1.4809   0.08266   0.07671  -0.0557   0.0249   1.0000
  15.250   1.4693   0.08728   0.08160  -0.0555   0.0250   1.0000
  15.500   1.4556   0.09202   0.08659  -0.0558   0.0250   1.0000
  15.750   1.4410   0.09684   0.09165  -0.0565   0.0251   1.0000
  16.000   1.4250   0.10204   0.09709  -0.0577   0.0252   1.0000
  16.250   1.4071   0.10765   0.10294  -0.0596   0.0254   1.0000
  16.500   1.3827   0.11467   0.11027  -0.0626   0.0258   1.0000
  16.750   1.3286   0.12794   0.12406  -0.0702   0.0271   1.0000
  17.000   1.2909   0.13989   0.13631  -0.0775   0.0279   1.0000
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