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NACA 0010-66 (naca001066-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 0010-66 (naca001066-il)
Reynolds number: 200,000
Max Cl/Cd: 34.4 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca001066-il-200000-n5.txt
Download as CSV file: xf-naca001066-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0010-66                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.8772   0.06435   0.06055  -0.0444   1.0000   0.0182
 -11.500  -0.9193   0.05911   0.05511  -0.0398   1.0000   0.0179
 -11.250  -0.9572   0.05514   0.05091  -0.0330   1.0000   0.0179
 -11.000  -0.9914   0.05209   0.04763  -0.0249   1.0000   0.0179
 -10.750  -1.0213   0.04948   0.04478  -0.0164   1.0000   0.0181
 -10.500  -1.0439   0.04614   0.04109  -0.0091   1.0000   0.0185
 -10.250  -1.0610   0.04275   0.03727  -0.0023   1.0000   0.0190
 -10.000  -1.0713   0.03958   0.03359   0.0038   1.0000   0.0197
  -9.750  -1.0714   0.03700   0.03057   0.0083   0.9996   0.0204
  -9.500  -1.0568   0.03568   0.02914   0.0099   0.9983   0.0211
  -9.250  -1.0398   0.03488   0.02825   0.0112   0.9971   0.0219
  -9.000  -1.0229   0.03397   0.02714   0.0127   0.9961   0.0231
  -8.750  -1.0064   0.03263   0.02549   0.0143   0.9951   0.0247
  -8.500  -0.9891   0.03118   0.02366   0.0160   0.9943   0.0262
  -8.250  -0.9724   0.02969   0.02185   0.0179   0.9934   0.0274
  -8.000  -0.9543   0.02869   0.02079   0.0193   0.9924   0.0288
  -7.750  -0.9337   0.02806   0.02008   0.0203   0.9912   0.0304
  -7.500  -0.9119   0.02724   0.01906   0.0212   0.9901   0.0321
  -7.250  -0.8896   0.02639   0.01799   0.0220   0.9892   0.0338
  -7.000  -0.8667   0.02580   0.01717   0.0229   0.9884   0.0352
  -6.750  -0.8441   0.02454   0.01583   0.0235   0.9879   0.0371
  -6.500  -0.8208   0.02387   0.01511   0.0241   0.9872   0.0387
  -6.250  -0.7969   0.02334   0.01451   0.0246   0.9866   0.0406
  -6.000  -0.7725   0.02276   0.01381   0.0251   0.9860   0.0423
  -5.750  -0.7476   0.02217   0.01312   0.0255   0.9855   0.0437
  -5.500  -0.7255   0.02165   0.01249   0.0265   0.9843   0.0449
  -5.250  -0.7037   0.02102   0.01182   0.0276   0.9831   0.0467
  -5.000  -0.6822   0.02046   0.01124   0.0287   0.9821   0.0488
  -4.750  -0.6599   0.02004   0.01078   0.0296   0.9811   0.0506
  -4.500  -0.6372   0.01966   0.01036   0.0305   0.9802   0.0527
  -4.250  -0.6140   0.01934   0.00997   0.0313   0.9793   0.0552
  -4.000  -0.5902   0.01903   0.00961   0.0320   0.9784   0.0581
  -3.750  -0.5655   0.01870   0.00931   0.0325   0.9775   0.0637
  -3.500  -0.5400   0.01843   0.00907   0.0327   0.9766   0.0735
  -3.250  -0.5152   0.01815   0.00888   0.0331   0.9759   0.0905
  -3.000  -0.4903   0.01792   0.00872   0.0335   0.9753   0.1132
  -2.750  -0.4711   0.01761   0.00852   0.0351   0.9740   0.1378
  -2.500  -0.4507   0.01732   0.00837   0.0364   0.9727   0.1694
  -2.250  -0.4294   0.01699   0.00824   0.0375   0.9711   0.2144
  -2.000  -0.4083   0.01663   0.00813   0.0386   0.9698   0.2752
  -1.750  -0.3070   0.01637   0.01057   0.0236   0.9789   0.8921
  -1.500  -0.2810   0.01697   0.01111   0.0245   0.9783   0.9173
  -1.250  -0.2466   0.01750   0.01156   0.0232   0.9781   0.9301
  -1.000  -0.2131   0.01794   0.01195   0.0221   0.9778   0.9403
  -0.750  -0.1774   0.01844   0.01240   0.0205   0.9778   0.9507
  -0.500  -0.1067   0.01947   0.01340   0.0115   0.9817   0.9665
  -0.250  -0.0488   0.02000   0.01392   0.0048   0.9843   0.9773
   0.000   0.0000   0.02013   0.01405   0.0000   0.9832   0.9832
   0.250   0.0486   0.02000   0.01392  -0.0048   0.9773   0.9844
   0.500   0.1069   0.01946   0.01340  -0.0115   0.9664   0.9816
   0.750   0.1775   0.01844   0.01240  -0.0205   0.9507   0.9778
   1.000   0.2132   0.01794   0.01194  -0.0221   0.9403   0.9778
   1.250   0.2466   0.01749   0.01156  -0.0233   0.9301   0.9781
   1.500   0.2810   0.01696   0.01110  -0.0245   0.9172   0.9783
   1.750   0.3067   0.01637   0.01057  -0.0235   0.8917   0.9790
   2.000   0.4082   0.01663   0.00813  -0.0386   0.2749   0.9698
   2.250   0.4294   0.01699   0.00823  -0.0375   0.2140   0.9712
   2.500   0.4506   0.01732   0.00837  -0.0364   0.1692   0.9727
   2.750   0.4710   0.01761   0.00852  -0.0351   0.1377   0.9740
   3.000   0.4902   0.01791   0.00871  -0.0335   0.1132   0.9753
   3.250   0.5152   0.01815   0.00888  -0.0331   0.0904   0.9759
   3.500   0.5400   0.01843   0.00907  -0.0327   0.0734   0.9766
   3.750   0.5655   0.01869   0.00931  -0.0325   0.0638   0.9775
   4.000   0.5902   0.01902   0.00960  -0.0320   0.0581   0.9785
   4.250   0.6139   0.01933   0.00997  -0.0313   0.0552   0.9793
   4.500   0.6371   0.01966   0.01035  -0.0305   0.0527   0.9802
   4.750   0.6599   0.02003   0.01077  -0.0296   0.0506   0.9812
   5.000   0.6821   0.02046   0.01123  -0.0287   0.0488   0.9821
   5.250   0.7036   0.02101   0.01181  -0.0276   0.0467   0.9831
   5.500   0.7254   0.02165   0.01249  -0.0265   0.0449   0.9843
   5.750   0.7476   0.02217   0.01311  -0.0255   0.0437   0.9855
   6.000   0.7725   0.02276   0.01380  -0.0251   0.0423   0.9860
   6.250   0.7970   0.02333   0.01450  -0.0246   0.0406   0.9866
   6.500   0.8208   0.02386   0.01510  -0.0241   0.0386   0.9872
   6.750   0.8441   0.02454   0.01583  -0.0235   0.0371   0.9879
   7.000   0.8668   0.02580   0.01717  -0.0229   0.0353   0.9884
   7.250   0.8897   0.02639   0.01798  -0.0221   0.0338   0.9892
   7.500   0.9121   0.02723   0.01905  -0.0212   0.0321   0.9901
   7.750   0.9339   0.02805   0.02007  -0.0203   0.0304   0.9912
   8.000   0.9544   0.02867   0.02077  -0.0193   0.0288   0.9925
   8.250   0.9725   0.02967   0.02183  -0.0179   0.0274   0.9934
   8.500   0.9891   0.03117   0.02365  -0.0161   0.0262   0.9943
   8.750   1.0065   0.03264   0.02550  -0.0144   0.0247   0.9951
   9.000   1.0230   0.03397   0.02714  -0.0127   0.0231   0.9961
   9.250   1.0400   0.03486   0.02822  -0.0112   0.0219   0.9972
   9.500   1.0569   0.03569   0.02915  -0.0099   0.0211   0.9984
   9.750   1.0716   0.03698   0.03056  -0.0083   0.0204   0.9997
  10.000   1.0714   0.03956   0.03357  -0.0039   0.0197   1.0000
  10.250   1.0610   0.04275   0.03726   0.0023   0.0190   1.0000
  10.500   1.0441   0.04613   0.04107   0.0091   0.0185   1.0000
  10.750   1.0218   0.04944   0.04474   0.0164   0.0180   1.0000
  11.000   0.9915   0.05210   0.04765   0.0249   0.0179   1.0000
  11.250   0.9576   0.05513   0.05090   0.0329   0.0178   1.0000
  11.500   0.9198   0.05909   0.05508   0.0397   0.0179   1.0000
  11.750   0.8769   0.06441   0.06061   0.0444   0.0182   1.0000
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