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NACA 66 (p51htip-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 66 (p51htip-il)
Reynolds number: 500,000
Max Cl/Cd: 72.93 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-p51htip-il-500000.txt
Download as CSV file: xf-p51htip-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4820   0.08633   0.08415  -0.0541   0.9777   0.0226
 -10.500  -0.4817   0.07801   0.07582  -0.0632   0.9643   0.0229
 -10.250  -0.5021   0.06870   0.06638  -0.0720   0.9440   0.0226
 -10.000  -0.5248   0.06409   0.06164  -0.0729   0.9281   0.0227
  -9.750  -0.5488   0.06028   0.05768  -0.0716   0.9153   0.0227
  -9.500  -0.5676   0.05740   0.05466  -0.0688   0.9047   0.0227
  -9.250  -0.5811   0.05479   0.05190  -0.0658   0.8964   0.0231
  -9.000  -0.5894   0.05163   0.04855  -0.0633   0.8900   0.0234
  -8.750  -0.5918   0.04846   0.04514  -0.0609   0.8844   0.0249
  -8.500  -0.5878   0.04750   0.04372  -0.0574   0.8787   0.0265
  -8.250  -0.5861   0.04498   0.04088  -0.0547   0.8744   0.0266
  -8.000  -0.5797   0.04222   0.03785  -0.0527   0.8704   0.0266
  -7.000  -0.5445   0.02219   0.01609  -0.0437   0.8569   0.0214
  -6.750  -0.5209   0.02069   0.01443  -0.0432   0.8539   0.0218
  -6.500  -0.4962   0.01953   0.01316  -0.0429   0.8512   0.0224
  -6.250  -0.4713   0.01868   0.01221  -0.0427   0.8488   0.0234
  -6.000  -0.4459   0.01788   0.01129  -0.0424   0.8466   0.0246
  -5.750  -0.4202   0.01706   0.01035  -0.0420   0.8446   0.0255
  -5.500  -0.3941   0.01646   0.00965  -0.0418   0.8426   0.0263
  -5.250  -0.3691   0.01508   0.00820  -0.0415   0.8404   0.0274
  -5.000  -0.3460   0.01413   0.00724  -0.0410   0.8381   0.0287
  -4.750  -0.3214   0.01371   0.00683  -0.0407   0.8359   0.0308
  -4.500  -0.2968   0.01330   0.00638  -0.0403   0.8339   0.0327
  -4.250  -0.2724   0.01290   0.00593  -0.0398   0.8319   0.0342
  -4.000  -0.2492   0.01240   0.00536  -0.0391   0.8300   0.0357
  -3.750  -0.2266   0.01187   0.00481  -0.0383   0.8283   0.0391
  -3.500  -0.2011   0.01159   0.00453  -0.0382   0.8264   0.0425
  -3.250  -0.1752   0.01137   0.00428  -0.0380   0.8245   0.0452
  -3.000  -0.1504   0.01102   0.00394  -0.0376   0.8226   0.0537
  -2.750  -0.1291   0.01032   0.00363  -0.0368   0.8207   0.1436
  -2.500  -0.1231   0.00836   0.00314  -0.0339   0.8184   0.5201
  -2.250  -0.1065   0.00774   0.00321  -0.0317   0.8166   0.7140
  -2.000  -0.0803   0.00778   0.00328  -0.0313   0.8152   0.7493
  -1.750  -0.0540   0.00790   0.00343  -0.0308   0.8139   0.7754
  -1.500  -0.0282   0.00808   0.00367  -0.0302   0.8124   0.7997
  -1.250  -0.0019   0.00825   0.00387  -0.0297   0.8106   0.8151
  -1.000   0.0240   0.00843   0.00409  -0.0291   0.8087   0.8292
  -0.750   0.0503   0.00861   0.00427  -0.0286   0.8070   0.8406
  -0.500   0.0774   0.00870   0.00438  -0.0284   0.8054   0.8462
  -0.250   0.1050   0.00875   0.00442  -0.0284   0.8037   0.8509
   0.000   0.1330   0.00878   0.00441  -0.0286   0.8021   0.8554
   0.250   0.1613   0.00877   0.00440  -0.0288   0.8005   0.8579
   0.500   0.1895   0.00882   0.00444  -0.0290   0.7989   0.8602
   0.750   0.2171   0.00885   0.00450  -0.0292   0.7963   0.8627
   1.000   0.2450   0.00886   0.00454  -0.0295   0.7935   0.8654
   1.250   0.2731   0.00885   0.00453  -0.0297   0.7907   0.8685
   1.500   0.3016   0.00882   0.00449  -0.0300   0.7881   0.8714
   1.750   0.3301   0.00876   0.00445  -0.0302   0.7855   0.8735
   2.000   0.3575   0.00875   0.00448  -0.0302   0.7817   0.8759
   2.250   0.3849   0.00858   0.00433  -0.0300   0.7747   0.8786
   2.500   0.4126   0.00833   0.00407  -0.0297   0.7654   0.8817
   2.750   0.4409   0.00809   0.00379  -0.0295   0.7558   0.8851
   3.000   0.4673   0.00781   0.00350  -0.0289   0.7405   0.8879
   3.250   0.4923   0.00760   0.00332  -0.0281   0.7209   0.8907
   3.500   0.5182   0.00751   0.00327  -0.0277   0.7032   0.8940
   3.750   0.5433   0.00745   0.00320  -0.0271   0.6742   0.8979
   4.000   0.5576   0.00784   0.00311  -0.0244   0.5518   0.9026
   4.250   0.5549   0.00930   0.00373  -0.0191   0.3678   0.9092
   4.500   0.5515   0.01086   0.00438  -0.0141   0.1735   0.9174
   4.750   0.5544   0.01202   0.00498  -0.0099   0.0551   0.9249
   5.000   0.5724   0.01241   0.00535  -0.0083   0.0441   0.9314
   5.250   0.5874   0.01284   0.00581  -0.0059   0.0386   0.9383
   5.500   0.6042   0.01318   0.00621  -0.0040   0.0362   0.9462
   5.750   0.6197   0.01350   0.00659  -0.0018   0.0339   0.9552
   6.000   0.6390   0.01392   0.00705  -0.0006   0.0317   0.9640
   6.250   0.6578   0.01487   0.00804   0.0004   0.0292   0.9742
   6.500   0.6864   0.01566   0.00890  -0.0006   0.0279   0.9806
   6.750   0.7169   0.01641   0.00970  -0.0020   0.0268   0.9862
   7.000   0.7486   0.01720   0.01054  -0.0035   0.0254   0.9908
   7.250   0.7802   0.01794   0.01128  -0.0052   0.0238   0.9963
   7.500   0.8003   0.01879   0.01213  -0.0045   0.0229   1.0000
   8.000   0.8697   0.02230   0.01581  -0.0079   0.0214   1.0000
   8.250   0.8858   0.02308   0.01668  -0.0061   0.0210   1.0000
   8.500   0.9105   0.02446   0.01821  -0.0058   0.0206   1.0000
   8.750   0.9325   0.02571   0.01961  -0.0052   0.0199   1.0000
   9.000   0.9536   0.02714   0.02122  -0.0045   0.0192   1.0000
   9.250   0.9742   0.02928   0.02358  -0.0037   0.0190   1.0000
   9.500   0.9906   0.03205   0.02665  -0.0023   0.0190   1.0000
   9.750   0.9984   0.03617   0.03120   0.0003   0.0197   1.0000
  10.000   0.9978   0.04080   0.03620   0.0034   0.0207   1.0000
  13.500   0.7323   0.12068   0.11840   0.0015   0.0233   1.0000
  13.750   0.7273   0.12725   0.12495  -0.0019   0.0232   1.0000
  14.000   0.7310   0.13048   0.12819  -0.0034   0.0227   1.0000
  14.250   0.7331   0.13422   0.13193  -0.0049   0.0224   1.0000
  15.000   0.5769   0.14458   0.14256  -0.0134   0.0228   1.0000
  15.250   0.5815   0.14699   0.14497  -0.0146   0.0224   1.0000
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