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NACA 65-410 (naca65410-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 65-410 (naca65410-il)
Reynolds number: 100,000
Max Cl/Cd: 52.87 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca65410-il-100000.txt
Download as CSV file: xf-naca65410-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65-410                                     
  
 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  -0.4325   0.09438   0.08948  -0.0411   1.0000   0.0951
  -8.750  -0.4521   0.09135   0.08659  -0.0450   1.0000   0.0970
  -8.500  -0.4757   0.08831   0.08369  -0.0476   1.0000   0.0974
  -8.250  -0.4500   0.08435   0.07971  -0.0427   1.0000   0.1023
  -8.000  -0.4565   0.08178   0.07720  -0.0417   1.0000   0.1056
  -7.750  -0.4750   0.07907   0.07465  -0.0417   1.0000   0.1069
  -7.500  -0.4956   0.07619   0.07182  -0.0421   1.0000   0.1089
  -7.250  -0.5228   0.07395   0.06954  -0.0424   1.0000   0.1110
  -7.000  -0.5532   0.07331   0.06852  -0.0427   1.0000   0.1122
  -6.750  -0.5299   0.06794   0.06362  -0.0380   1.0000   0.1173
  -6.500  -0.5370   0.06553   0.06112  -0.0373   1.0000   0.1236
  -6.250  -0.5423   0.06209   0.05760  -0.0369   1.0000   0.1293
  -6.000  -0.5451   0.06010   0.05523  -0.0375   1.0000   0.1414
  -5.750  -0.5358   0.05667   0.05208  -0.0345   1.0000   0.1465
  -5.500  -0.5308   0.05403   0.04937  -0.0338   1.0000   0.1611
  -5.250  -0.5251   0.05159   0.04672  -0.0340   1.0000   0.1855
  -5.000  -0.5164   0.04923   0.04450  -0.0317   1.0000   0.2043
  -4.750  -0.5077   0.04695   0.04223  -0.0304   1.0000   0.2325
  -4.500  -0.4979   0.04499   0.04030  -0.0286   1.0000   0.2655
  -4.000  -0.3799   0.03101   0.02297  -0.0394   0.9977   0.0812
  -3.750  -0.3410   0.02860   0.02009  -0.0416   0.9942   0.0803
  -3.500  -0.3040   0.02641   0.01749  -0.0431   0.9900   0.0771
  -3.250  -0.2660   0.02479   0.01555  -0.0447   0.9859   0.0766
  -3.000  -0.2289   0.02384   0.01439  -0.0464   0.9817   0.0817
  -2.750  -0.1963   0.02275   0.01318  -0.0473   0.9767   0.0850
  -2.500  -0.1613   0.02170   0.01228  -0.0490   0.9724   0.0911
  -2.250  -0.1268   0.02102   0.01166  -0.0507   0.9678   0.1050
  -2.000  -0.0948   0.02039   0.01103  -0.0520   0.9620   0.1263
  -1.750  -0.0817   0.01809   0.01165  -0.0479   0.9582   0.7664
  -1.500  -0.0823   0.01859   0.01225  -0.0397   0.9503   0.8555
  -1.250  -0.0756   0.01889   0.01252  -0.0333   0.9433   0.9160
  -1.000   0.0472   0.01945   0.01269  -0.0490   0.9489   1.0000
  -0.750   0.0783   0.01954   0.01263  -0.0513   0.9427   1.0000
  -0.500   0.0882   0.01955   0.01255  -0.0497   0.9329   1.0000
  -0.250   0.1221   0.01972   0.01260  -0.0522   0.9276   1.0000
   0.000   0.1283   0.01980   0.01260  -0.0499   0.9177   1.0000
   0.250   0.1672   0.02006   0.01274  -0.0530   0.9132   1.0000
   0.500   0.1834   0.02031   0.01292  -0.0523   0.9046   1.0000
   0.750   0.2221   0.02061   0.01315  -0.0552   0.9000   1.0000
   1.000   0.2450   0.02098   0.01346  -0.0556   0.8926   1.0000
   1.250   0.2803   0.02131   0.01376  -0.0578   0.8871   1.0000
   1.500   0.3107   0.02172   0.01414  -0.0592   0.8812   1.0000
   1.750   0.3391   0.02211   0.01453  -0.0602   0.8743   1.0000
   2.000   0.3817   0.02240   0.01485  -0.0633   0.8703   1.0000
   2.250   0.3989   0.02295   0.01540  -0.0625   0.8611   1.0000
   2.500   0.4410   0.02319   0.01570  -0.0654   0.8566   1.0000
   2.750   0.4605   0.02372   0.01630  -0.0647   0.8470   1.0000
   3.000   0.5058   0.02381   0.01651  -0.0679   0.8421   1.0000
   3.250   0.5253   0.02435   0.01711  -0.0671   0.8317   1.0000
   3.500   0.5760   0.02421   0.01717  -0.0708   0.8273   1.0000
   3.750   0.5963   0.02467   0.01775  -0.0699   0.8158   1.0000
   4.000   0.6260   0.02487   0.01811  -0.0703   0.8053   1.0000
   4.250   0.7334   0.01847   0.01209  -0.0734   0.7656   1.0000
   4.500   0.7730   0.01617   0.00986  -0.0710   0.7260   1.0000
   4.750   0.7952   0.01504   0.00875  -0.0671   0.6645   1.0000
   5.000   0.7889   0.01596   0.00789  -0.0583   0.3266   1.0000
   5.250   0.7812   0.01933   0.00961  -0.0534   0.1183   1.0000
   5.500   0.7951   0.02079   0.01096  -0.0512   0.0955   1.0000
   5.750   0.8111   0.02216   0.01233  -0.0492   0.0856   1.0000
   6.000   0.8297   0.02376   0.01381  -0.0479   0.0776   1.0000
   6.250   0.8548   0.02520   0.01525  -0.0473   0.0712   1.0000
   6.500   0.8882   0.02773   0.01761  -0.0481   0.0673   1.0000
   6.750   0.9222   0.03008   0.02014  -0.0486   0.0656   1.0000
   7.000   0.9503   0.03192   0.02230  -0.0482   0.0627   1.0000
   7.250   0.9781   0.03439   0.02511  -0.0478   0.0614   1.0000
   7.500   1.0042   0.03754   0.02866  -0.0471   0.0623   1.0000
   7.750   1.0272   0.04128   0.03279  -0.0461   0.0643   1.0000
   8.000   1.0521   0.04627   0.03800  -0.0458   0.0673   1.0000
   8.250   1.0649   0.05342   0.04700  -0.0396   0.1107   1.0000
  10.750   0.9840   0.10665   0.10241  -0.0301   0.1474   1.0000
  11.000   0.9353   0.11247   0.10825  -0.0354   0.1480   1.0000
  11.250   0.8915   0.12227   0.11796  -0.0449   0.1467   1.0000
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