Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 0010 (naca0010-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 0010 (naca0010-il)
Reynolds number: 500,000
Max Cl/Cd: 55.2 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca0010-il-500000.txt
Download as CSV file: xf-naca0010-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0010                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -15.500  -0.5410   0.15664   0.15441   0.0166   1.0000   0.0244
 -15.250  -0.9687   0.10921   0.10680   0.0116   1.0000   0.0144
 -15.000  -0.9414   0.11142   0.10906   0.0131   1.0000   0.0150
 -14.750  -0.9092   0.11490   0.11260   0.0151   1.0000   0.0157
 -14.500  -0.8712   0.11994   0.11766   0.0177   1.0000   0.0166
 -13.750  -1.1591   0.04725   0.04339  -0.0277   1.0000   0.0135
 -13.500  -1.1772   0.04217   0.03806  -0.0290   1.0000   0.0136
 -13.250  -1.1889   0.03845   0.03414  -0.0288   1.0000   0.0139
 -13.000  -1.1924   0.03596   0.03150  -0.0276   1.0000   0.0142
 -12.750  -1.1898   0.03429   0.02972  -0.0261   1.0000   0.0145
 -12.500  -1.1837   0.03304   0.02840  -0.0244   1.0000   0.0148
 -12.250  -1.1760   0.03195   0.02721  -0.0224   1.0000   0.0153
 -12.000  -1.1647   0.03087   0.02602  -0.0209   1.0000   0.0158
 -11.750  -1.1519   0.02971   0.02471  -0.0195   1.0000   0.0165
 -11.500  -1.1372   0.02863   0.02346  -0.0182   1.0000   0.0171
 -11.250  -1.1201   0.02777   0.02243  -0.0171   1.0000   0.0177
 -11.000  -1.1119   0.02534   0.01983  -0.0152   1.0000   0.0186
 -10.750  -1.0929   0.02460   0.01905  -0.0143   1.0000   0.0194
 -10.500  -1.0725   0.02400   0.01839  -0.0135   1.0000   0.0204
 -10.250  -1.0520   0.02330   0.01760  -0.0126   1.0000   0.0215
 -10.000  -1.0302   0.02277   0.01693  -0.0119   1.0000   0.0227
  -9.750  -1.0116   0.02152   0.01553  -0.0108   1.0000   0.0240
  -9.500  -0.9918   0.02057   0.01457  -0.0099   1.0000   0.0255
  -9.250  -0.9692   0.02008   0.01404  -0.0093   1.0000   0.0270
  -9.000  -0.9464   0.01954   0.01342  -0.0086   1.0000   0.0286
  -8.750  -0.9222   0.01927   0.01306  -0.0080   1.0000   0.0299
  -8.500  -0.9043   0.01773   0.01142  -0.0067   1.0000   0.0321
  -8.250  -0.8817   0.01716   0.01085  -0.0060   1.0000   0.0339
  -8.000  -0.8585   0.01668   0.01031  -0.0053   1.0000   0.0357
  -7.750  -0.8348   0.01626   0.00983  -0.0046   1.0000   0.0374
  -7.500  -0.8104   0.01600   0.00950  -0.0040   1.0000   0.0384
  -7.250  -0.7922   0.01472   0.00816  -0.0025   1.0000   0.0409
  -7.000  -0.7700   0.01420   0.00763  -0.0015   1.0000   0.0429
  -6.750  -0.7472   0.01377   0.00717  -0.0006   1.0000   0.0448
  -6.500  -0.7244   0.01338   0.00674   0.0003   1.0000   0.0466
  -6.250  -0.7012   0.01304   0.00635   0.0013   1.0000   0.0479
  -6.000  -0.6798   0.01246   0.00572   0.0024   1.0000   0.0498
  -5.750  -0.6580   0.01195   0.00521   0.0036   1.0000   0.0530
  -5.500  -0.6353   0.01159   0.00485   0.0046   1.0000   0.0560
  -5.250  -0.6122   0.01130   0.00451   0.0055   1.0000   0.0591
  -5.000  -0.5901   0.01084   0.00410   0.0066   1.0000   0.0677
  -4.750  -0.5678   0.01039   0.00376   0.0076   1.0000   0.0877
  -4.500  -0.5459   0.00989   0.00346   0.0086   1.0000   0.1251
  -4.250  -0.5233   0.00948   0.00323   0.0094   1.0000   0.1629
  -4.000  -0.5002   0.00914   0.00305   0.0101   1.0000   0.2012
  -3.750  -0.4769   0.00881   0.00289   0.0108   1.0000   0.2422
  -3.500  -0.4532   0.00851   0.00277   0.0114   1.0000   0.2842
  -3.250  -0.4209   0.00820   0.00265   0.0102   0.9982   0.3324
  -3.000  -0.3827   0.00789   0.00254   0.0077   0.9950   0.3835
  -2.750  -0.3457   0.00757   0.00242   0.0056   0.9911   0.4361
  -2.500  -0.3083   0.00724   0.00234   0.0034   0.9870   0.4958
  -2.250  -0.2703   0.00695   0.00226   0.0011   0.9832   0.5508
  -2.000  -0.2342   0.00667   0.00218  -0.0006   0.9775   0.6005
  -1.750  -0.1959   0.00642   0.00210  -0.0028   0.9734   0.6461
  -1.500  -0.1642   0.00620   0.00203  -0.0034   0.9644   0.6875
  -1.250  -0.1334   0.00599   0.00198  -0.0037   0.9548   0.7284
  -1.000  -0.1036   0.00583   0.00193  -0.0038   0.9437   0.7622
  -0.750  -0.0762   0.00569   0.00189  -0.0032   0.9299   0.7927
  -0.500  -0.0504   0.00559   0.00187  -0.0023   0.9129   0.8214
  -0.250  -0.0251   0.00552   0.00185  -0.0012   0.8936   0.8479
   0.000   0.0000   0.00550   0.00184   0.0000   0.8721   0.8722
   0.250   0.0251   0.00552   0.00185   0.0012   0.8479   0.8935
   0.500   0.0504   0.00559   0.00187   0.0023   0.8213   0.9129
   0.750   0.0762   0.00569   0.00189   0.0032   0.7926   0.9298
   1.000   0.1036   0.00583   0.00193   0.0038   0.7622   0.9437
   1.250   0.1334   0.00599   0.00198   0.0037   0.7285   0.9548
   1.500   0.1642   0.00620   0.00203   0.0034   0.6876   0.9644
   1.750   0.1959   0.00642   0.00210   0.0028   0.6461   0.9734
   2.000   0.2342   0.00667   0.00217   0.0006   0.6005   0.9775
   2.250   0.2703   0.00695   0.00226  -0.0011   0.5507   0.9832
   2.500   0.3083   0.00724   0.00234  -0.0034   0.4957   0.9870
   2.750   0.3457   0.00757   0.00242  -0.0056   0.4362   0.9911
   3.000   0.3827   0.00788   0.00253  -0.0077   0.3835   0.9950
   3.250   0.4209   0.00820   0.00265  -0.0102   0.3325   0.9982
   3.500   0.4532   0.00851   0.00277  -0.0114   0.2843   1.0000
   3.750   0.4768   0.00881   0.00289  -0.0108   0.2422   1.0000
   4.000   0.5002   0.00914   0.00305  -0.0101   0.2013   1.0000
   4.250   0.5233   0.00948   0.00323  -0.0094   0.1629   1.0000
   4.500   0.5458   0.00989   0.00346  -0.0086   0.1252   1.0000
   4.750   0.5678   0.01039   0.00376  -0.0076   0.0877   1.0000
   5.000   0.5901   0.01084   0.00410  -0.0066   0.0677   1.0000
   5.250   0.6122   0.01130   0.00451  -0.0055   0.0591   1.0000
   5.500   0.6353   0.01159   0.00484  -0.0046   0.0560   1.0000
   5.750   0.6580   0.01195   0.00521  -0.0036   0.0530   1.0000
   6.000   0.6798   0.01246   0.00572  -0.0024   0.0498   1.0000
   6.250   0.7012   0.01304   0.00635  -0.0013   0.0479   1.0000
   6.500   0.7244   0.01338   0.00674  -0.0003   0.0466   1.0000
   6.750   0.7472   0.01377   0.00717   0.0006   0.0448   1.0000
   7.000   0.7700   0.01420   0.00763   0.0015   0.0429   1.0000
   7.250   0.7922   0.01472   0.00816   0.0025   0.0409   1.0000
   7.500   0.8104   0.01600   0.00950   0.0040   0.0384   1.0000
   7.750   0.8348   0.01627   0.00984   0.0046   0.0374   1.0000
   8.000   0.8585   0.01667   0.01031   0.0053   0.0357   1.0000
   8.250   0.8817   0.01716   0.01084   0.0060   0.0339   1.0000
   8.500   0.9043   0.01772   0.01142   0.0067   0.0321   1.0000
   8.750   0.9223   0.01926   0.01305   0.0080   0.0299   1.0000
   9.000   0.9465   0.01954   0.01341   0.0085   0.0286   1.0000
   9.250   0.9693   0.02008   0.01404   0.0092   0.0270   1.0000
   9.500   0.9918   0.02058   0.01457   0.0099   0.0255   1.0000
   9.750   1.0116   0.02152   0.01553   0.0108   0.0240   1.0000
  10.000   1.0302   0.02277   0.01693   0.0119   0.0227   1.0000
  10.250   1.0521   0.02330   0.01760   0.0126   0.0215   1.0000
  10.500   1.0726   0.02400   0.01840   0.0135   0.0204   1.0000
  10.750   1.0930   0.02460   0.01905   0.0143   0.0194   1.0000
  11.000   1.1120   0.02534   0.01983   0.0152   0.0186   1.0000
  11.250   1.1203   0.02776   0.02243   0.0170   0.0176   1.0000
  11.500   1.1374   0.02861   0.02344   0.0182   0.0171   1.0000
  11.750   1.1521   0.02971   0.02470   0.0195   0.0165   1.0000
  12.000   1.1650   0.03086   0.02601   0.0208   0.0158   1.0000
  12.250   1.1764   0.03193   0.02719   0.0223   0.0153   1.0000
  12.500   1.1841   0.03303   0.02838   0.0243   0.0148   1.0000
  12.750   1.1901   0.03430   0.02974   0.0261   0.0145   1.0000
  13.000   1.1928   0.03597   0.03151   0.0276   0.0142   1.0000
  13.250   1.1893   0.03846   0.03415   0.0287   0.0139   1.0000
  13.500   1.1776   0.04220   0.03809   0.0289   0.0136   1.0000
  13.750   1.1598   0.04726   0.04339   0.0276   0.0135   1.0000
  14.000   1.1392   0.05348   0.04987   0.0244   0.0134   1.0000
  14.250   1.1185   0.06054   0.05716   0.0198   0.0134   1.0000
  14.500   1.0985   0.06815   0.06497   0.0145   0.0134   1.0000
  14.750   1.0794   0.07607   0.07306   0.0090   0.0134   1.0000
  15.000   1.0587   0.08458   0.08172   0.0034   0.0135   1.0000
  15.250   1.0360   0.09378   0.09107  -0.0024   0.0136   1.0000
<< Back to NACA 0010 (naca0010-il)

Polar data table (+)

Polar graphs


<< Back to NACA 0010 (naca0010-il)