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NACA 0010-65 (naca001065-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 0010-65 (naca001065-il)
Reynolds number: 500,000
Max Cl/Cd: 43.08 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca001065-il-500000.txt
Download as CSV file: xf-naca001065-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0010-65                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.7770   0.06475   0.06220  -0.0531   1.0000   0.0193
 -11.500  -0.8229   0.05753   0.05480  -0.0525   1.0000   0.0188
 -11.250  -0.8745   0.05153   0.04856  -0.0469   1.0000   0.0185
 -11.000  -0.9228   0.04749   0.04429  -0.0377   1.0000   0.0183
 -10.750  -0.9612   0.04428   0.04084  -0.0283   1.0000   0.0183
 -10.500  -0.9866   0.04099   0.03725  -0.0207   1.0000   0.0185
 -10.250  -1.0045   0.03793   0.03387  -0.0139   1.0000   0.0188
 -10.000  -1.0159   0.03504   0.03062  -0.0078   1.0000   0.0193
  -9.750  -1.0197   0.03268   0.02792  -0.0027   1.0000   0.0198
  -9.500  -1.0161   0.03119   0.02612   0.0014   1.0000   0.0203
  -9.250  -1.0171   0.02831   0.02285   0.0060   1.0000   0.0209
  -9.000  -1.0070   0.02693   0.02139   0.0087   1.0000   0.0216
  -8.750  -0.9932   0.02646   0.02088   0.0110   1.0000   0.0222
  -8.500  -0.9784   0.02604   0.02042   0.0131   1.0000   0.0230
  -8.250  -0.9636   0.02537   0.01963   0.0153   1.0000   0.0240
  -8.000  -0.9442   0.02445   0.01851   0.0166   0.9995   0.0251
  -7.750  -0.9164   0.02387   0.01773   0.0163   0.9981   0.0260
  -7.500  -0.8942   0.02126   0.01487   0.0168   0.9972   0.0275
  -7.250  -0.8659   0.02069   0.01428   0.0161   0.9958   0.0288
  -7.000  -0.8369   0.02020   0.01373   0.0154   0.9947   0.0304
  -6.750  -0.8086   0.01955   0.01296   0.0150   0.9936   0.0318
  -6.500  -0.7814   0.01900   0.01230   0.0149   0.9917   0.0328
  -6.250  -0.7550   0.01781   0.01098   0.0149   0.9904   0.0342
  -6.000  -0.7286   0.01690   0.01005   0.0148   0.9890   0.0360
  -5.750  -0.6999   0.01639   0.00951   0.0143   0.9875   0.0374
  -5.500  -0.6700   0.01593   0.00900   0.0136   0.9861   0.0390
  -5.250  -0.6392   0.01553   0.00856   0.0126   0.9849   0.0406
  -5.000  -0.6080   0.01515   0.00813   0.0116   0.9839   0.0417
  -4.750  -0.5833   0.01456   0.00748   0.0121   0.9819   0.0430
  -4.500  -0.5601   0.01398   0.00690   0.0128   0.9789   0.0454
  -4.250  -0.5320   0.01366   0.00658   0.0125   0.9767   0.0478
  -4.000  -0.5024   0.01337   0.00626   0.0119   0.9749   0.0502
  -3.750  -0.4711   0.01312   0.00599   0.0110   0.9735   0.0527
  -3.500  -0.4398   0.01275   0.00567   0.0100   0.9723   0.0605
  -3.250  -0.4081   0.01241   0.00543   0.0089   0.9713   0.0811
  -3.000  -0.3886   0.01203   0.00524   0.0104   0.9673   0.1193
  -2.750  -0.3639   0.01162   0.00508   0.0107   0.9642   0.1742
  -2.500  -0.3373   0.01110   0.00491   0.0105   0.9620   0.2594
  -2.250  -0.3152   0.01002   0.00466   0.0110   0.9600   0.4611
  -2.000  -0.3002   0.00866   0.00451   0.0135   0.9581   0.7421
  -1.750  -0.2702   0.00852   0.00473   0.0135   0.9572   0.8398
  -1.500  -0.2518   0.00864   0.00494   0.0160   0.9522   0.8778
  -1.250  -0.2234   0.00882   0.00515   0.0162   0.9496   0.9025
  -1.000  -0.1917   0.00908   0.00542   0.0158   0.9479   0.9185
  -0.750  -0.1584   0.00936   0.00569   0.0150   0.9465   0.9303
  -0.500  -0.1178   0.00976   0.00609   0.0126   0.9461   0.9378
  -0.250  -0.0771   0.01012   0.00644   0.0101   0.9457   0.9449
   0.000  -0.0002   0.01037   0.00669   0.0000   0.9462   0.9462
   0.250   0.0773   0.01012   0.00644  -0.0102   0.9449   0.9457
   0.500   0.1178   0.00976   0.00609  -0.0126   0.9377   0.9461
   0.750   0.1583   0.00936   0.00569  -0.0150   0.9304   0.9465
   1.000   0.1917   0.00908   0.00542  -0.0158   0.9183   0.9479
   1.250   0.2234   0.00882   0.00515  -0.0162   0.9025   0.9496
   1.500   0.2518   0.00863   0.00494  -0.0160   0.8778   0.9522
   1.750   0.2702   0.00852   0.00473  -0.0135   0.8400   0.9572
   2.000   0.3003   0.00865   0.00451  -0.0136   0.7432   0.9581
   2.250   0.3152   0.01002   0.00466  -0.0110   0.4610   0.9601
   2.500   0.3373   0.01110   0.00491  -0.0105   0.2596   0.9620
   2.750   0.3638   0.01162   0.00508  -0.0107   0.1748   0.9642
   3.000   0.3885   0.01203   0.00523  -0.0104   0.1195   0.9673
   3.250   0.4080   0.01241   0.00543  -0.0089   0.0809   0.9713
   3.500   0.4398   0.01275   0.00567  -0.0100   0.0605   0.9723
   3.750   0.4711   0.01312   0.00599  -0.0110   0.0527   0.9735
   4.000   0.5024   0.01337   0.00626  -0.0119   0.0502   0.9750
   4.250   0.5320   0.01366   0.00658  -0.0125   0.0478   0.9767
   4.500   0.5600   0.01398   0.00690  -0.0128   0.0454   0.9789
   4.750   0.5831   0.01456   0.00749  -0.0121   0.0430   0.9819
   5.000   0.6080   0.01515   0.00813  -0.0116   0.0417   0.9840
   5.250   0.6392   0.01552   0.00856  -0.0126   0.0406   0.9849
   5.500   0.6700   0.01592   0.00900  -0.0136   0.0390   0.9861
   5.750   0.6999   0.01639   0.00950  -0.0143   0.0374   0.9875
   6.000   0.7285   0.01691   0.01006  -0.0148   0.0360   0.9890
   6.250   0.7551   0.01780   0.01097  -0.0149   0.0342   0.9904
   6.500   0.7814   0.01901   0.01231  -0.0149   0.0328   0.9918
   6.750   0.8086   0.01955   0.01296  -0.0150   0.0318   0.9936
   7.000   0.8370   0.02020   0.01373  -0.0154   0.0304   0.9947
   7.250   0.8659   0.02069   0.01428  -0.0161   0.0288   0.9958
   7.500   0.8942   0.02125   0.01486  -0.0168   0.0275   0.9972
   7.750   0.9164   0.02389   0.01774  -0.0164   0.0260   0.9981
   8.000   0.9443   0.02445   0.01851  -0.0167   0.0251   0.9996
   8.250   0.9635   0.02537   0.01963  -0.0153   0.0240   1.0000
   8.500   0.9783   0.02606   0.02043  -0.0131   0.0230   1.0000
   8.750   0.9931   0.02647   0.02089  -0.0110   0.0222   1.0000
   9.000   1.0070   0.02693   0.02139  -0.0087   0.0216   1.0000
   9.250   1.0171   0.02830   0.02284  -0.0060   0.0209   1.0000
   9.500   1.0161   0.03120   0.02613  -0.0014   0.0203   1.0000
   9.750   1.0197   0.03268   0.02792   0.0027   0.0198   1.0000
  10.000   1.0159   0.03504   0.03062   0.0078   0.0193   1.0000
  10.250   1.0045   0.03792   0.03386   0.0139   0.0188   1.0000
  10.500   0.9867   0.04099   0.03725   0.0207   0.0185   1.0000
  10.750   0.9620   0.04420   0.04075   0.0282   0.0182   1.0000
  11.000   0.9220   0.04757   0.04437   0.0378   0.0183   1.0000
  11.250   0.8741   0.05160   0.04862   0.0469   0.0185   1.0000
  11.500   0.8222   0.05766   0.05493   0.0525   0.0188   1.0000
  11.750   0.7763   0.06496   0.06241   0.0530   0.0193   1.0000
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