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NACA 66 (p51htip-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 66 (p51htip-il)
Reynolds number: 50,000
Max Cl/Cd: 22.7 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-p51htip-il-50000-n5.txt
Download as CSV file: xf-p51htip-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66                                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.3658   0.11240   0.10564  -0.0456   1.0000   0.0670
 -11.500  -0.3690   0.10829   0.10156  -0.0471   1.0000   0.0650
 -11.250  -0.4890   0.10755   0.10038  -0.0496   1.0000   0.0590
 -11.000  -0.4817   0.10395   0.09680  -0.0493   1.0000   0.0578
 -10.750  -0.4819   0.09951   0.09241  -0.0509   1.0000   0.0567
 -10.500  -0.4852   0.09475   0.08770  -0.0532   1.0000   0.0556
 -10.250  -0.4930   0.08941   0.08242  -0.0564   1.0000   0.0546
 -10.000  -0.5068   0.08437   0.07744  -0.0590   1.0000   0.0537
  -9.750  -0.5262   0.08031   0.07343  -0.0598   1.0000   0.0528
  -9.500  -0.5521   0.07754   0.07070  -0.0579   1.0000   0.0520
  -9.250  -0.5832   0.07589   0.06910  -0.0535   1.0000   0.0515
  -9.000  -0.6147   0.07461   0.06785  -0.0479   1.0000   0.0511
  -8.750  -0.6411   0.07270   0.06589  -0.0432   1.0000   0.0506
  -8.500  -0.6652   0.07042   0.06350  -0.0386   1.0000   0.0499
  -8.250  -0.6848   0.06788   0.06078  -0.0343   1.0000   0.0494
  -8.000  -0.6999   0.06517   0.05783  -0.0302   1.0000   0.0490
  -7.750  -0.6989   0.06173   0.05408  -0.0290   0.9963   0.0491
  -7.500  -0.6900   0.05856   0.05063  -0.0287   0.9917   0.0502
  -7.250  -0.6801   0.05546   0.04719  -0.0282   0.9872   0.0512
  -7.000  -0.6689   0.05238   0.04371  -0.0274   0.9835   0.0522
  -6.750  -0.6577   0.04945   0.04036  -0.0261   0.9796   0.0526
  -6.500  -0.6420   0.04652   0.03695  -0.0251   0.9760   0.0528
  -6.250  -0.6218   0.04378   0.03372  -0.0247   0.9730   0.0532
  -6.000  -0.6037   0.04159   0.03110  -0.0235   0.9696   0.0546
  -5.500  -0.5595   0.03795   0.02642  -0.0218   0.9640   0.0590
  -5.250  -0.5323   0.03599   0.02423  -0.0219   0.9621   0.0604
  -5.000  -0.5029   0.03439   0.02251  -0.0223   0.9605   0.0627
  -4.750  -0.4756   0.03330   0.02129  -0.0223   0.9584   0.0673
  -4.500  -0.4489   0.03241   0.02011  -0.0218   0.9560   0.0717
  -4.250  -0.4219   0.03138   0.01906  -0.0215   0.9539   0.0753
  -4.000  -0.3985   0.03062   0.01819  -0.0209   0.9516   0.0810
  -3.750  -0.3762   0.02991   0.01738  -0.0202   0.9492   0.0894
  -3.500  -0.3529   0.02923   0.01656  -0.0198   0.9468   0.0996
  -3.000  -0.3224   0.02726   0.01512  -0.0166   0.9407   0.1699
  -2.750  -0.3255   0.02538   0.01628  -0.0085   0.9385   0.7291
  -2.500  -0.1456   0.02987   0.01998  -0.0260   0.9493   0.9463
  -2.250  -0.1035   0.02976   0.01955  -0.0298   0.9477   0.9551
  -2.000  -0.0648   0.02969   0.01923  -0.0331   0.9461   0.9627
  -1.750  -0.0347   0.02961   0.01897  -0.0347   0.9434   0.9707
  -1.500  -0.0015   0.02951   0.01869  -0.0370   0.9406   0.9771
  -1.250   0.0303   0.02949   0.01853  -0.0391   0.9379   0.9836
  -1.000   0.0658   0.02945   0.01837  -0.0419   0.9354   0.9888
  -0.750   0.1010   0.02951   0.01832  -0.0446   0.9331   0.9940
  -0.500   0.1340   0.02954   0.01828  -0.0469   0.9304   0.9991
  -0.250   0.1467   0.02966   0.01836  -0.0453   0.9255   1.0000
   0.000   0.1649   0.02981   0.01848  -0.0446   0.9211   1.0000
   0.250   0.1892   0.03002   0.01866  -0.0451   0.9176   1.0000
   0.500   0.1942   0.03018   0.01881  -0.0419   0.9115   1.0000
   0.750   0.2120   0.03039   0.01902  -0.0411   0.9066   1.0000
   1.000   0.2369   0.03065   0.01929  -0.0415   0.9028   1.0000
   1.250   0.2394   0.03083   0.01949  -0.0378   0.8955   1.0000
   1.500   0.2604   0.03109   0.01978  -0.0375   0.8905   1.0000
   1.750   0.2715   0.03133   0.02006  -0.0354   0.8841   1.0000
   2.000   0.2866   0.03158   0.02036  -0.0339   0.8776   1.0000
   2.250   0.3078   0.03187   0.02073  -0.0334   0.8720   1.0000
   2.500   0.3152   0.03210   0.02102  -0.0306   0.8637   1.0000
   2.750   0.3427   0.03243   0.02145  -0.0312   0.8583   1.0000
   3.000   0.3461   0.03264   0.02173  -0.0275   0.8486   1.0000
   3.250   0.3665   0.03294   0.02216  -0.0267   0.8413   1.0000
   3.500   0.3814   0.03319   0.02251  -0.0250   0.8322   1.0000
   3.750   0.3940   0.03345   0.02288  -0.0228   0.8225   1.0000
   4.000   0.4247   0.03372   0.02333  -0.0235   0.8149   1.0000
   4.250   0.4349   0.03394   0.02367  -0.0208   0.8031   1.0000
   4.500   0.4518   0.03415   0.02407  -0.0192   0.7918   1.0000
   4.750   0.4772   0.03429   0.02443  -0.0187   0.7809   1.0000
   5.000   0.5127   0.03424   0.02469  -0.0196   0.7702   1.0000
   5.250   0.5597   0.03240   0.02327  -0.0196   0.7401   1.0000
   5.500   0.5764   0.02853   0.01952  -0.0117   0.6643   1.0000
   5.750   0.5654   0.02830   0.01931  -0.0049   0.6089   1.0000
   6.000   0.6043   0.02662   0.01518   0.0005   0.1976   1.0000
   6.500   0.6040   0.02982   0.01745   0.0076   0.1043   1.0000
   6.750   0.6138   0.03108   0.01860   0.0098   0.0905   1.0000
   7.000   0.6273   0.03224   0.01982   0.0117   0.0833   1.0000
   7.250   0.6442   0.03341   0.02100   0.0132   0.0765   1.0000
   7.500   0.6683   0.03450   0.02223   0.0139   0.0697   1.0000
   7.750   0.7096   0.03576   0.02360   0.0128   0.0642   1.0000
   8.000   0.7760   0.03800   0.02607   0.0081   0.0590   1.0000
   8.500   0.8444   0.04237   0.03096   0.0062   0.0527   1.0000
   8.750   0.8716   0.04509   0.03391   0.0060   0.0514   1.0000
   9.000   0.8940   0.04834   0.03736   0.0062   0.0503   1.0000
   9.250   0.9036   0.05080   0.04031   0.0085   0.0494   1.0000
   9.500   0.9087   0.05339   0.04337   0.0110   0.0484   1.0000
   9.750   0.9102   0.05616   0.04660   0.0137   0.0474   1.0000
  10.000   0.9083   0.05908   0.04988   0.0165   0.0467   1.0000
  10.250   0.9034   0.06208   0.05320   0.0193   0.0466   1.0000
  10.500   0.8935   0.06506   0.05646   0.0223   0.0466   1.0000
  10.750   0.8810   0.06819   0.05982   0.0250   0.0466   1.0000
  11.000   0.8662   0.07159   0.06344   0.0271   0.0468   1.0000
  11.250   0.8493   0.07529   0.06734   0.0286   0.0469   1.0000
  11.500   0.8307   0.07936   0.07160   0.0292   0.0472   1.0000
  11.750   0.8093   0.08408   0.07647   0.0289   0.0474   1.0000
  12.000   0.7883   0.08933   0.08184   0.0276   0.0477   1.0000
  12.250   0.7688   0.09509   0.08769   0.0252   0.0482   1.0000
  12.500   0.7502   0.10160   0.09424   0.0219   0.0486   1.0000
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