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NACA 0010-66 (naca001066-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 0010-66 (naca001066-il)
Reynolds number: 500,000
Max Cl/Cd: 42.87 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca001066-il-500000.txt
Download as CSV file: xf-naca001066-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.6438   0.14346   0.14104  -0.0139   1.0000   0.0259
 -13.250  -0.9148   0.06624   0.06364  -0.0512   1.0000   0.0162
 -13.000  -0.9452   0.06056   0.05778  -0.0515   1.0000   0.0161
 -12.750  -0.9734   0.05646   0.05351  -0.0489   1.0000   0.0160
 -12.500  -1.0033   0.05289   0.04975  -0.0443   1.0000   0.0160
 -12.250  -1.0333   0.04976   0.04643  -0.0383   1.0000   0.0160
 -12.000  -1.0654   0.04685   0.04331  -0.0308   1.0000   0.0161
 -11.750  -1.0959   0.04446   0.04070  -0.0224   1.0000   0.0161
 -11.500  -1.1254   0.04250   0.03855  -0.0132   1.0000   0.0162
 -11.250  -1.1426   0.04036   0.03623  -0.0062   1.0000   0.0164
 -11.000  -1.1419   0.03948   0.03530  -0.0019   1.0000   0.0167
 -10.750  -1.1335   0.03931   0.03512   0.0012   1.0000   0.0171
 -10.500  -1.1263   0.03886   0.03462   0.0045   1.0000   0.0174
 -10.250  -1.1188   0.03826   0.03396   0.0078   1.0000   0.0179
 -10.000  -1.1167   0.03679   0.03231   0.0120   1.0000   0.0184
  -9.750  -1.1162   0.03480   0.03004   0.0166   1.0000   0.0190
  -9.500  -1.1140   0.03273   0.02764   0.0212   1.0000   0.0196
  -9.250  -1.1067   0.03127   0.02588   0.0249   1.0000   0.0201
  -9.000  -1.1006   0.02923   0.02349   0.0288   1.0000   0.0207
  -8.750  -1.0811   0.02744   0.02156   0.0296   0.9989   0.0216
  -8.500  -1.0598   0.02700   0.02108   0.0304   0.9980   0.0224
  -8.250  -1.0386   0.02656   0.02056   0.0313   0.9971   0.0234
  -8.000  -1.0176   0.02588   0.01974   0.0324   0.9964   0.0245
  -7.750  -0.9943   0.02529   0.01895   0.0331   0.9955   0.0256
  -7.500  -0.9711   0.02348   0.01686   0.0337   0.9948   0.0268
  -7.250  -0.9452   0.02255   0.01590   0.0336   0.9934   0.0281
  -7.000  -0.9231   0.02211   0.01541   0.0345   0.9921   0.0293
  -6.750  -0.9009   0.02169   0.01493   0.0354   0.9912   0.0308
  -6.500  -0.8780   0.02121   0.01433   0.0363   0.9904   0.0320
  -6.250  -0.8546   0.02088   0.01391   0.0371   0.9896   0.0329
  -6.000  -0.8314   0.01939   0.01231   0.0378   0.9892   0.0347
  -5.750  -0.8080   0.01889   0.01180   0.0384   0.9885   0.0363
  -5.500  -0.7822   0.01851   0.01138   0.0386   0.9875   0.0378
  -5.250  -0.7552   0.01813   0.01094   0.0386   0.9866   0.0393
  -5.000  -0.7288   0.01786   0.01063   0.0387   0.9859   0.0407
  -4.750  -0.7026   0.01767   0.01038   0.0388   0.9853   0.0417
  -4.500  -0.6787   0.01695   0.00961   0.0395   0.9848   0.0437
  -4.250  -0.6526   0.01668   0.00933   0.0397   0.9843   0.0459
  -4.000  -0.6326   0.01634   0.00899   0.0412   0.9826   0.0480
  -3.750  -0.6121   0.01604   0.00866   0.0426   0.9812   0.0500
  -3.500  -0.5884   0.01583   0.00841   0.0434   0.9796   0.0519
  -3.250  -0.5657   0.01550   0.00810   0.0444   0.9786   0.0571
  -3.000  -0.5419   0.01533   0.00794   0.0451   0.9777   0.0637
  -2.750  -0.5186   0.01500   0.00779   0.0459   0.9769   0.0910
  -2.500  -0.4950   0.01472   0.00770   0.0465   0.9761   0.1338
  -2.250  -0.4695   0.01445   0.00767   0.0466   0.9751   0.1837
  -2.000  -0.4436   0.01415   0.00769   0.0467   0.9742   0.2581
  -1.750  -0.4202   0.01377   0.00772   0.0472   0.9735   0.3566
  -1.500  -0.4044   0.01294   0.00773   0.0494   0.9727   0.5508
  -1.250  -0.3734   0.01240   0.00870   0.0496   0.9735   0.9170
  -1.000  -0.3385   0.01313   0.00940   0.0484   0.9733   0.9355
  -0.750  -0.2957   0.01400   0.01024   0.0454   0.9736   0.9472
  -0.500  -0.2020   0.01548   0.01169   0.0312   0.9751   0.9551
  -0.250  -0.1393   0.01591   0.01208   0.0238   0.9700   0.9599
   0.000  -0.0051   0.01630   0.01246   0.0011   0.9637   0.9634
   0.250   0.1382   0.01592   0.01209  -0.0236   0.9600   0.9701
   0.500   0.2021   0.01548   0.01169  -0.0313   0.9551   0.9751
   0.750   0.2955   0.01400   0.01024  -0.0454   0.9473   0.9737
   1.000   0.3384   0.01313   0.00940  -0.0484   0.9355   0.9733
   1.250   0.3733   0.01240   0.00870  -0.0496   0.9170   0.9735
   1.500   0.4044   0.01293   0.00772  -0.0494   0.5517   0.9727
   1.750   0.4201   0.01376   0.00772  -0.0472   0.3569   0.9735
   2.000   0.4435   0.01415   0.00769  -0.0466   0.2578   0.9742
   2.250   0.4694   0.01445   0.00767  -0.0466   0.1837   0.9751
   2.500   0.4949   0.01471   0.00770  -0.0465   0.1341   0.9761
   2.750   0.5185   0.01500   0.00778  -0.0458   0.0910   0.9769
   3.000   0.5418   0.01533   0.00794  -0.0450   0.0637   0.9777
   3.250   0.5656   0.01549   0.00809  -0.0444   0.0571   0.9786
   3.500   0.5883   0.01583   0.00841  -0.0434   0.0519   0.9796
   3.750   0.6120   0.01604   0.00866  -0.0426   0.0500   0.9812
   4.000   0.6324   0.01634   0.00899  -0.0412   0.0480   0.9826
   4.250   0.6526   0.01667   0.00933  -0.0397   0.0459   0.9844
   4.500   0.6786   0.01695   0.00961  -0.0395   0.0437   0.9848
   4.750   0.7025   0.01766   0.01038  -0.0388   0.0417   0.9853
   5.000   0.7288   0.01785   0.01061  -0.0387   0.0407   0.9859
   5.250   0.7554   0.01812   0.01093  -0.0386   0.0393   0.9866
   5.500   0.7823   0.01850   0.01137  -0.0386   0.0378   0.9876
   5.750   0.8079   0.01889   0.01179  -0.0384   0.0363   0.9885
   6.000   0.8313   0.01939   0.01230  -0.0378   0.0347   0.9892
   6.250   0.8545   0.02088   0.01391  -0.0370   0.0329   0.9896
   6.500   0.8779   0.02121   0.01433  -0.0363   0.0320   0.9904
   6.750   0.9008   0.02168   0.01492  -0.0354   0.0308   0.9912
   7.000   0.9230   0.02211   0.01541  -0.0345   0.0294   0.9921
   7.250   0.9449   0.02253   0.01588  -0.0335   0.0281   0.9933
   7.500   0.9707   0.02346   0.01684  -0.0336   0.0268   0.9948
   7.750   0.9939   0.02528   0.01895  -0.0330   0.0256   0.9955
   8.000   1.0175   0.02586   0.01972  -0.0324   0.0245   0.9964
   8.250   1.0386   0.02656   0.02056  -0.0313   0.0234   0.9971
   8.500   1.0597   0.02700   0.02108  -0.0304   0.0224   0.9980
   8.750   1.0809   0.02745   0.02157  -0.0296   0.0216   0.9989
   9.000   1.1010   0.02911   0.02336  -0.0289   0.0207   1.0000
   9.250   1.1066   0.03127   0.02587  -0.0249   0.0201   1.0000
   9.500   1.1140   0.03272   0.02762  -0.0212   0.0196   1.0000
   9.750   1.1164   0.03476   0.02999  -0.0167   0.0190   1.0000
  10.000   1.1172   0.03672   0.03222  -0.0121   0.0184   1.0000
  10.250   1.1194   0.03818   0.03388  -0.0079   0.0179   1.0000
  10.500   1.1270   0.03877   0.03452  -0.0046   0.0174   1.0000
  10.750   1.1339   0.03927   0.03508  -0.0012   0.0171   1.0000
  11.000   1.1421   0.03947   0.03529   0.0019   0.0167   1.0000
  11.250   1.1427   0.04036   0.03623   0.0062   0.0164   1.0000
  11.500   1.1260   0.04248   0.03853   0.0131   0.0162   1.0000
  11.750   1.0959   0.04448   0.04073   0.0224   0.0161   1.0000
  12.000   1.0654   0.04687   0.04332   0.0308   0.0161   1.0000
  12.250   1.0335   0.04976   0.04643   0.0383   0.0160   1.0000
  12.500   1.0028   0.05294   0.04981   0.0443   0.0160   1.0000
  12.750   0.9729   0.05653   0.05358   0.0489   0.0160   1.0000
  13.000   0.9454   0.06056   0.05778   0.0515   0.0161   1.0000
  13.250   0.9146   0.06634   0.06375   0.0511   0.0162   1.0000
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