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NACA 65-410 (naca65410-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 65-410 (naca65410-il)
Reynolds number: 200,000
Max Cl/Cd: 75.24 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca65410-il-200000.txt
Download as CSV file: xf-naca65410-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4290   0.08762   0.08411  -0.0438   1.0000   0.0406
  -8.750  -0.4359   0.08361   0.08017  -0.0464   1.0000   0.0416
  -8.500  -0.4481   0.07943   0.07608  -0.0494   1.0000   0.0421
  -8.250  -0.4655   0.07627   0.07300  -0.0495   1.0000   0.0419
  -8.000  -0.4854   0.07386   0.07063  -0.0479   1.0000   0.0418
  -7.750  -0.5043   0.07167   0.06845  -0.0455   1.0000   0.0419
  -7.500  -0.5240   0.06955   0.06628  -0.0434   1.0000   0.0423
  -7.250  -0.5384   0.06756   0.06411  -0.0422   0.9996   0.0429
  -7.000  -0.5209   0.06024   0.05635  -0.0496   0.9935   0.0440
  -6.750  -0.5029   0.05504   0.05137  -0.0515   0.9901   0.0462
  -6.500  -0.4769   0.05161   0.04784  -0.0551   0.9856   0.0500
  -6.000  -0.4239   0.04239   0.03784  -0.0627   0.9743   0.0596
  -5.750  -0.3914   0.03944   0.03471  -0.0659   0.9710   0.0655
  -5.500  -0.3657   0.03601   0.03090  -0.0678   0.9647   0.0738
  -5.250  -0.3341   0.03347   0.02798  -0.0703   0.9600   0.0865
  -4.750  -0.2595   0.02536   0.01865  -0.0727   0.9537   0.0595
  -4.500  -0.2257   0.02204   0.01468  -0.0723   0.9489   0.0454
  -4.250  -0.1897   0.02020   0.01266  -0.0740   0.9457   0.0469
  -4.000  -0.1509   0.01878   0.01112  -0.0761   0.9435   0.0493
  -3.750  -0.1111   0.01743   0.00966  -0.0783   0.9419   0.0508
  -3.500  -0.0851   0.01661   0.00879  -0.0780   0.9347   0.0532
  -3.250  -0.0496   0.01567   0.00781  -0.0796   0.9312   0.0579
  -3.000  -0.0127   0.01467   0.00686  -0.0817   0.9285   0.0640
  -2.750   0.0150   0.01412   0.00627  -0.0819   0.9217   0.0728
  -2.250   0.0712   0.01117   0.00569  -0.0830   0.9137   0.7036
  -2.000   0.0910   0.01138   0.00599  -0.0805   0.9057   0.7593
  -1.750   0.1144   0.01159   0.00627  -0.0782   0.9009   0.8009
  -1.500   0.1314   0.01188   0.00657  -0.0748   0.8942   0.8316
  -1.250   0.1501   0.01200   0.00670  -0.0718   0.8881   0.8516
  -1.000   0.1768   0.01197   0.00662  -0.0708   0.8844   0.8653
  -0.750   0.1988   0.01201   0.00661  -0.0698   0.8761   0.8750
  -0.500   0.2263   0.01192   0.00646  -0.0694   0.8718   0.8818
  -0.250   0.2507   0.01192   0.00643  -0.0688   0.8652   0.8909
   0.000   0.2757   0.01186   0.00635  -0.0681   0.8595   0.8991
   0.250   0.3047   0.01176   0.00621  -0.0681   0.8558   0.9073
   0.500   0.3253   0.01182   0.00627  -0.0669   0.8477   0.9181
   0.750   0.3523   0.01171   0.00615  -0.0664   0.8433   0.9270
   1.000   0.3765   0.01170   0.00616  -0.0658   0.8370   0.9375
   1.250   0.4043   0.01165   0.00613  -0.0658   0.8314   0.9482
   1.500   0.4377   0.01155   0.00603  -0.0669   0.8277   0.9580
   1.750   0.4720   0.01160   0.00614  -0.0686   0.8209   0.9673
   2.000   0.5123   0.01155   0.00614  -0.0713   0.8162   0.9751
   2.250   0.5534   0.01151   0.00615  -0.0742   0.8117   0.9829
   2.500   0.5950   0.01151   0.00622  -0.0774   0.8040   0.9903
   2.750   0.6370   0.01135   0.00614  -0.0803   0.7964   0.9984
   3.000   0.6577   0.01111   0.00590  -0.0787   0.7823   1.0000
   3.250   0.6746   0.01083   0.00561  -0.0761   0.7630   1.0000
   3.500   0.6965   0.01045   0.00516  -0.0742   0.7372   1.0000
   3.750   0.7194   0.01022   0.00488  -0.0727   0.7070   1.0000
   4.000   0.7437   0.01015   0.00482  -0.0717   0.6767   1.0000
   4.250   0.7667   0.01019   0.00476  -0.0704   0.6298   1.0000
   4.500   0.7744   0.01108   0.00473  -0.0662   0.4344   1.0000
   4.750   0.7618   0.01457   0.00621  -0.0606   0.0953   1.0000
   5.000   0.7787   0.01582   0.00726  -0.0590   0.0652   1.0000
   5.250   0.7972   0.01684   0.00829  -0.0577   0.0548   1.0000
   5.500   0.8170   0.01777   0.00928  -0.0565   0.0505   1.0000
   5.750   0.8365   0.01880   0.01033  -0.0553   0.0468   1.0000
   6.000   0.8557   0.02014   0.01164  -0.0540   0.0440   1.0000
   6.250   0.8784   0.02185   0.01337  -0.0533   0.0413   1.0000
   6.500   0.9046   0.02311   0.01474  -0.0530   0.0395   1.0000
   6.750   0.9331   0.02479   0.01654  -0.0530   0.0384   1.0000
   7.000   0.9628   0.02685   0.01878  -0.0531   0.0379   1.0000
   7.250   0.9913   0.02925   0.02143  -0.0529   0.0378   1.0000
   7.500   1.0159   0.03134   0.02377  -0.0523   0.0364   1.0000
   7.750   1.0395   0.03467   0.02753  -0.0512   0.0374   1.0000
   8.000   1.0587   0.03957   0.03284  -0.0499   0.0406   1.0000
  10.000   1.0890   0.07863   0.07447  -0.0335   0.0539   1.0000
  10.250   1.0631   0.07925   0.07541  -0.0290   0.0533   1.0000
  10.500   1.0350   0.08163   0.07799  -0.0258   0.0530   1.0000
  10.750   1.0088   0.08534   0.08187  -0.0248   0.0527   1.0000
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