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NACA 66 (p51hroot-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 66 (p51hroot-il)
Reynolds number: 50,000
Max Cl/Cd: 19.47 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-p51hroot-il-50000-n5.txt
Download as CSV file: xf-p51hroot-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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.4693   0.11027   0.10310  -0.0658   1.0000   0.0605
 -12.500  -0.4819   0.10573   0.09863  -0.0667   1.0000   0.0601
 -12.250  -0.4990   0.10156   0.09453  -0.0669   1.0000   0.0597
 -12.000  -0.5214   0.09754   0.09057  -0.0667   1.0000   0.0591
 -11.750  -0.5469   0.09382   0.08689  -0.0661   1.0000   0.0584
 -11.500  -0.5779   0.08999   0.08307  -0.0652   1.0000   0.0579
 -11.250  -0.6062   0.08573   0.07877  -0.0651   0.9981   0.0572
 -11.000  -0.6292   0.08033   0.07320  -0.0675   0.9918   0.0568
 -10.750  -0.6510   0.07585   0.06851  -0.0683   0.9855   0.0565
 -10.500  -0.6705   0.07234   0.06477  -0.0675   0.9791   0.0561
 -10.250  -0.6883   0.06928   0.06145  -0.0657   0.9731   0.0561
 -10.000  -0.7045   0.06683   0.05877  -0.0624   0.9668   0.0561
  -9.750  -0.7133   0.06394   0.05557  -0.0600   0.9618   0.0561
  -9.500  -0.7194   0.06128   0.05260  -0.0573   0.9572   0.0561
  -9.250  -0.7249   0.05888   0.04989  -0.0540   0.9522   0.0562
  -9.000  -0.7226   0.05626   0.04688  -0.0518   0.9483   0.0566
  -8.750  -0.7156   0.05385   0.04408  -0.0500   0.9450   0.0573
  -8.500  -0.7160   0.05213   0.04204  -0.0463   0.9408   0.0582
  -8.250  -0.7104   0.05027   0.03975  -0.0435   0.9376   0.0596
  -8.000  -0.6987   0.04843   0.03745  -0.0415   0.9349   0.0608
  -7.750  -0.6778   0.04633   0.03506  -0.0411   0.9331   0.0620
  -7.500  -0.6500   0.04443   0.03298  -0.0417   0.9315   0.0633
  -7.250  -0.6292   0.04306   0.03146  -0.0408   0.9292   0.0651
  -7.000  -0.6089   0.04195   0.03018  -0.0398   0.9267   0.0679
  -6.750  -0.5807   0.04088   0.02885  -0.0398   0.9248   0.0713
  -6.500  -0.5387   0.03967   0.02757  -0.0420   0.9240   0.0746
  -6.250  -0.5022   0.03883   0.02667  -0.0434   0.9230   0.0791
  -6.000  -0.4757   0.03824   0.02589  -0.0432   0.9214   0.0852
  -5.750  -0.4562   0.03750   0.02519  -0.0422   0.9197   0.0903
  -5.500  -0.4384   0.03686   0.02446  -0.0409   0.9177   0.0966
  -5.250  -0.4241   0.03618   0.02377  -0.0392   0.9155   0.1054
  -5.000  -0.4258   0.03573   0.02329  -0.0345   0.9119   0.1146
  -4.500  -0.4240   0.03405   0.02210  -0.0266   0.9066   0.1668
  -4.250  -0.3920   0.03365   0.02471  -0.0232   0.9063   0.6163
  -4.000  -0.4048   0.03350   0.02441  -0.0165   0.9026   0.6801
  -3.750  -0.3978   0.03479   0.02555  -0.0108   0.9002   0.7447
  -3.500  -0.2614   0.04074   0.03099  -0.0206   0.9030   0.8382
  -3.250  -0.2350   0.04086   0.03087  -0.0208   0.9014   0.8507
  -3.000  -0.1972   0.04096   0.03070  -0.0233   0.9002   0.8600
  -2.750  -0.1844   0.04095   0.03056  -0.0212   0.8971   0.8697
  -2.500  -0.1703   0.04094   0.03041  -0.0195   0.8941   0.8795
  -2.250  -0.1432   0.04092   0.03022  -0.0203   0.8919   0.8864
  -2.000  -0.1196   0.04091   0.03007  -0.0205   0.8894   0.8939
  -1.750  -0.0957   0.04091   0.02994  -0.0208   0.8869   0.9005
  -1.500  -0.0615   0.04093   0.02982  -0.0231   0.8850   0.9055
  -1.250  -0.0567   0.04096   0.02978  -0.0198   0.8814   0.9133
  -1.000  -0.0339   0.04095   0.02969  -0.0201   0.8780   0.9179
  -0.750  -0.0109   0.04098   0.02965  -0.0203   0.8748   0.9229
  -0.500   0.0069   0.04106   0.02965  -0.0195   0.8716   0.9284
  -0.250   0.0385   0.04116   0.02969  -0.0213   0.8690   0.9320
   0.000   0.0587   0.04124   0.02973  -0.0212   0.8652   0.9364
   0.250   0.0713   0.04133   0.02980  -0.0195   0.8605   0.9418
   0.500   0.0914   0.04145   0.02990  -0.0192   0.8565   0.9457
   0.750   0.1229   0.04160   0.03004  -0.0210   0.8533   0.9482
   1.000   0.1431   0.04176   0.03020  -0.0209   0.8488   0.9518
   1.250   0.1555   0.04191   0.03036  -0.0192   0.8431   0.9562
   1.500   0.1779   0.04210   0.03056  -0.0193   0.8387   0.9593
   1.750   0.2138   0.04234   0.03084  -0.0218   0.8353   0.9614
   2.000   0.2245   0.04253   0.03108  -0.0201   0.8281   0.9657
   2.250   0.2487   0.04276   0.03136  -0.0206   0.8227   0.9690
   2.500   0.2797   0.04305   0.03170  -0.0220   0.8187   0.9717
   2.750   0.2938   0.04328   0.03202  -0.0210   0.8103   0.9755
   3.000   0.3244   0.04354   0.03238  -0.0226   0.8048   0.9785
   3.250   0.3467   0.04384   0.03278  -0.0227   0.7981   0.9821
   3.500   0.3690   0.04411   0.03316  -0.0229   0.7904   0.9852
   3.750   0.4076   0.04433   0.03352  -0.0254   0.7856   0.9872
   4.000   0.4207   0.04465   0.03397  -0.0243   0.7749   0.9918
   4.250   0.4600   0.04482   0.03433  -0.0269   0.7695   0.9943
   4.750   0.4997   0.04527   0.03508  -0.0261   0.7500   1.0000
   5.000   0.5123   0.04531   0.03525  -0.0239   0.7397   1.0000
   5.250   0.5166   0.04539   0.03546  -0.0205   0.7278   1.0000
   5.500   0.5402   0.04520   0.03546  -0.0197   0.7189   1.0000
   5.750   0.5510   0.04506   0.03546  -0.0170   0.7069   1.0000
   6.000   0.5544   0.04494   0.03548  -0.0133   0.6933   1.0000
   6.250   0.5607   0.04471   0.03540  -0.0098   0.6796   1.0000
   6.500   0.5694   0.04423   0.03509  -0.0065   0.6648   1.0000
   6.750   0.5791   0.04351   0.03453  -0.0029   0.6483   1.0000
   7.000   0.5888   0.04177   0.03294   0.0017   0.6218   1.0000
   7.250   0.5976   0.03900   0.03024   0.0078   0.5786   1.0000
   7.500   0.6022   0.03665   0.02786   0.0142   0.5123   1.0000
   7.750   0.6483   0.03330   0.02326   0.0177   0.3069   1.0000
   8.000   0.6348   0.03475   0.02394   0.0227   0.2130   1.0000
   8.250   0.6261   0.03654   0.02510   0.0265   0.1448   1.0000
   8.500   0.6247   0.03827   0.02641   0.0292   0.1095   1.0000
   8.750   0.6288   0.03981   0.02776   0.0313   0.0934   1.0000
   9.000   0.6372   0.04114   0.02907   0.0329   0.0832   1.0000
   9.250   0.6472   0.04246   0.03037   0.0344   0.0767   1.0000
   9.500   0.6601   0.04367   0.03163   0.0356   0.0718   1.0000
   9.750   0.6749   0.04491   0.03281   0.0368   0.0681   1.0000
  10.000   0.6984   0.04577   0.03387   0.0375   0.0650   1.0000
  10.250   0.7303   0.04652   0.03475   0.0378   0.0619   1.0000
  10.500   0.7715   0.04730   0.03557   0.0372   0.0595   1.0000
  10.750   0.8214   0.04867   0.03712   0.0358   0.0575   1.0000
  11.000   0.8542   0.05056   0.03934   0.0353   0.0555   1.0000
  11.250   0.8773   0.05266   0.04169   0.0354   0.0536   1.0000
  11.500   0.8970   0.05487   0.04414   0.0357   0.0523   1.0000
  11.750   0.9129   0.05741   0.04691   0.0363   0.0515   1.0000
  12.000   0.9241   0.06011   0.04985   0.0371   0.0510   1.0000
  12.250   0.9331   0.06292   0.05284   0.0379   0.0503   1.0000
  12.500   0.9283   0.06592   0.05612   0.0397   0.0498   1.0000
  12.750   0.9192   0.06908   0.05959   0.0414   0.0497   1.0000
  13.000   0.9046   0.07251   0.06333   0.0431   0.0494   1.0000
  13.250   0.8885   0.07631   0.06741   0.0442   0.0492   1.0000
  13.500   0.8720   0.08034   0.07168   0.0448   0.0492   1.0000
  13.750   0.8512   0.08497   0.07654   0.0448   0.0492   1.0000
  14.000   0.8301   0.08998   0.08176   0.0440   0.0493   1.0000
  14.250   0.8057   0.09580   0.08776   0.0424   0.0494   1.0000
  14.500   0.7844   0.10193   0.09404   0.0399   0.0497   1.0000
  14.750   0.7611   0.10910   0.10133   0.0363   0.0499   1.0000
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