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NACA 0010-66 (naca001066-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 0010-66 (naca001066-il)
Reynolds number: 50,000
Max Cl/Cd: 21.89 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca001066-il-50000-n5.txt
Download as CSV file: xf-naca001066-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.6690   0.10438   0.09692  -0.0297   1.0000   0.0648
 -10.500  -0.6861   0.09802   0.09062  -0.0325   1.0000   0.0641
 -10.250  -0.7083   0.09210   0.08471  -0.0338   1.0000   0.0634
 -10.000  -0.7349   0.08702   0.07963  -0.0328   1.0000   0.0626
  -9.750  -0.7644   0.08283   0.07540  -0.0295   1.0000   0.0619
  -9.500  -0.7944   0.07931   0.07182  -0.0245   1.0000   0.0613
  -9.250  -0.8164   0.07563   0.06802  -0.0199   1.0000   0.0613
  -9.000  -0.8340   0.07202   0.06425  -0.0153   1.0000   0.0615
  -8.750  -0.8487   0.06845   0.06047  -0.0107   1.0000   0.0617
  -8.500  -0.8605   0.06486   0.05662  -0.0060   1.0000   0.0620
  -8.250  -0.8689   0.06135   0.05281  -0.0013   1.0000   0.0625
  -8.000  -0.8737   0.05808   0.04921   0.0031   1.0000   0.0635
  -7.750  -0.8758   0.05503   0.04577   0.0074   1.0000   0.0655
  -7.500  -0.8766   0.05189   0.04212   0.0119   1.0000   0.0676
  -7.250  -0.8741   0.04875   0.03837   0.0162   1.0000   0.0693
  -7.000  -0.8662   0.04580   0.03489   0.0198   1.0000   0.0704
  -6.750  -0.8521   0.04346   0.03236   0.0219   1.0000   0.0721
  -6.500  -0.8369   0.04183   0.03057   0.0239   1.0000   0.0755
  -6.250  -0.8206   0.03998   0.02830   0.0261   1.0000   0.0794
  -6.000  -0.8005   0.03789   0.02570   0.0278   1.0000   0.0820
  -5.750  -0.7769   0.03596   0.02338   0.0288   1.0000   0.0843
  -5.500  -0.7521   0.03441   0.02173   0.0293   1.0000   0.0873
  -5.250  -0.7271   0.03322   0.02035   0.0298   1.0000   0.0927
  -5.000  -0.6994   0.03203   0.01888   0.0300   1.0000   0.0994
  -4.750  -0.6687   0.03090   0.01771   0.0294   1.0000   0.1057
  -4.500  -0.6305   0.02986   0.01647   0.0276   1.0000   0.1145
  -4.250  -0.5958   0.02897   0.01546   0.0262   1.0000   0.1279
  -4.000  -0.5661   0.02810   0.01470   0.0256   1.0000   0.1501
  -3.750  -0.5382   0.02718   0.01395   0.0254   1.0000   0.1844
  -3.500  -0.3862   0.02607   0.01616   0.0032   1.0000   0.8559
  -3.250  -0.3591   0.02731   0.01703   0.0046   1.0000   0.9363
  -3.000  -0.2080   0.02817   0.01700  -0.0209   1.0000   1.0000
  -2.750  -0.1912   0.02798   0.01663  -0.0192   1.0000   1.0000
  -2.500  -0.1742   0.02781   0.01629  -0.0174   1.0000   1.0000
  -2.250  -0.1571   0.02767   0.01600  -0.0157   1.0000   1.0000
  -2.000  -0.1399   0.02754   0.01573  -0.0139   1.0000   1.0000
  -1.750  -0.1226   0.02744   0.01551  -0.0122   1.0000   1.0000
  -1.500  -0.1053   0.02734   0.01532  -0.0104   1.0000   1.0000
  -1.250  -0.0878   0.02727   0.01516  -0.0087   1.0000   1.0000
  -1.000  -0.0703   0.02720   0.01503  -0.0069   1.0000   1.0000
  -0.750  -0.0528   0.02716   0.01493  -0.0052   1.0000   1.0000
  -0.500  -0.0352   0.02712   0.01486  -0.0035   1.0000   1.0000
  -0.250  -0.0176   0.02710   0.01482  -0.0017   1.0000   1.0000
   0.000   0.0000   0.02710   0.01480   0.0000   1.0000   1.0000
   0.250   0.0176   0.02710   0.01482   0.0017   1.0000   1.0000
   0.500   0.0352   0.02712   0.01486   0.0035   1.0000   1.0000
   0.750   0.0528   0.02715   0.01493   0.0052   1.0000   1.0000
   1.000   0.0703   0.02720   0.01503   0.0069   1.0000   1.0000
   1.250   0.0878   0.02726   0.01515   0.0087   1.0000   1.0000
   1.500   0.1053   0.02734   0.01532   0.0104   1.0000   1.0000
   1.750   0.1227   0.02743   0.01550   0.0122   1.0000   1.0000
   2.000   0.1400   0.02753   0.01572   0.0139   1.0000   1.0000
   2.250   0.1572   0.02766   0.01599   0.0157   1.0000   1.0000
   2.500   0.1742   0.02780   0.01628   0.0174   1.0000   1.0000
   2.750   0.1912   0.02797   0.01661   0.0192   1.0000   1.0000
   3.000   0.2080   0.02815   0.01699   0.0209   1.0000   1.0000
   3.250   0.3592   0.02730   0.01702  -0.0046   0.9363   1.0000
   3.500   0.3862   0.02606   0.01615  -0.0032   0.8561   1.0000
   3.750   0.5382   0.02718   0.01394  -0.0254   0.1844   1.0000
   4.000   0.5661   0.02809   0.01470  -0.0256   0.1501   1.0000
   4.250   0.5958   0.02896   0.01546  -0.0262   0.1278   1.0000
   4.500   0.6305   0.02985   0.01646  -0.0276   0.1144   1.0000
   4.750   0.6686   0.03090   0.01770  -0.0294   0.1057   1.0000
   5.000   0.6993   0.03202   0.01888  -0.0299   0.0994   1.0000
   5.250   0.7271   0.03321   0.02034  -0.0298   0.0927   1.0000
   5.500   0.7520   0.03441   0.02172  -0.0293   0.0873   1.0000
   5.750   0.7768   0.03595   0.02337  -0.0288   0.0843   1.0000
   6.000   0.8005   0.03788   0.02569  -0.0278   0.0820   1.0000
   6.250   0.8205   0.03998   0.02829  -0.0260   0.0794   1.0000
   6.500   0.8369   0.04183   0.03056  -0.0239   0.0755   1.0000
   6.750   0.8520   0.04345   0.03236  -0.0219   0.0721   1.0000
   7.000   0.8661   0.04579   0.03488  -0.0198   0.0704   1.0000
   7.250   0.8741   0.04874   0.03836  -0.0162   0.0693   1.0000
   7.500   0.8766   0.05188   0.04211  -0.0119   0.0676   1.0000
   7.750   0.8758   0.05502   0.04576  -0.0074   0.0655   1.0000
   8.000   0.8737   0.05807   0.04920  -0.0031   0.0635   1.0000
   8.250   0.8690   0.06134   0.05280   0.0013   0.0625   1.0000
   8.500   0.8606   0.06485   0.05661   0.0060   0.0620   1.0000
   8.750   0.8488   0.06844   0.06046   0.0107   0.0617   1.0000
   9.000   0.8341   0.07202   0.06425   0.0153   0.0615   1.0000
   9.250   0.8166   0.07563   0.06801   0.0199   0.0613   1.0000
   9.500   0.7946   0.07931   0.07182   0.0244   0.0613   1.0000
   9.750   0.7647   0.08283   0.07540   0.0295   0.0619   1.0000
  10.000   0.7352   0.08702   0.07962   0.0328   0.0626   1.0000
  10.250   0.7087   0.09209   0.08471   0.0337   0.0634   1.0000
  10.500   0.6865   0.09801   0.09060   0.0325   0.0641   1.0000
  10.750   0.6695   0.10437   0.09690   0.0296   0.0648   1.0000
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