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NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il)
Reynolds number: 100,000
Max Cl/Cd: 47.27 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca001034a08cli02-il-100000.txt
Download as CSV file: xf-naca001034a08cli02-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0010-34 a=0.8 c(li)=0.2                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5485   0.09963   0.09490  -0.0444   1.0000   0.0881
  -9.250  -0.5696   0.09625   0.09154  -0.0461   1.0000   0.0882
  -9.000  -0.5928   0.09369   0.08897  -0.0455   1.0000   0.0883
  -8.750  -0.5208   0.08955   0.08483  -0.0362   1.0000   0.1088
  -8.500  -0.5362   0.08567   0.08105  -0.0384   1.0000   0.1115
  -8.250  -0.5584   0.08231   0.07782  -0.0387   1.0000   0.1122
  -8.000  -0.5817   0.07904   0.07455  -0.0387   1.0000   0.1135
  -7.750  -0.6077   0.07642   0.07181  -0.0376   1.0000   0.1145
  -7.500  -0.5926   0.07282   0.06833  -0.0346   1.0000   0.1241
  -7.250  -0.6218   0.07060   0.06589  -0.0333   1.0000   0.1281
  -4.750  -0.5289   0.03298   0.02498  -0.0144   1.0000   0.0697
  -4.500  -0.5035   0.03027   0.02161  -0.0124   1.0000   0.0589
  -4.250  -0.4787   0.02768   0.01863  -0.0112   1.0000   0.0549
  -4.000  -0.4538   0.02596   0.01659  -0.0102   1.0000   0.0564
  -3.750  -0.4280   0.02444   0.01481  -0.0093   1.0000   0.0585
  -3.500  -0.4015   0.02287   0.01303  -0.0085   1.0000   0.0589
  -3.250  -0.3764   0.02162   0.01169  -0.0075   1.0000   0.0608
  -3.000  -0.3534   0.02021   0.01035  -0.0066   1.0000   0.0652
  -2.750  -0.3308   0.01930   0.00944  -0.0058   1.0000   0.0778
  -2.500  -0.1662   0.01697   0.01038  -0.0230   1.0000   0.9948
  -2.250  -0.1449   0.01665   0.00983  -0.0237   1.0000   1.0000
  -2.000  -0.1510   0.01630   0.00938  -0.0191   1.0000   1.0000
  -1.750  -0.1538   0.01603   0.00900  -0.0149   1.0000   1.0000
  -1.500  -0.1511   0.01587   0.00870  -0.0114   1.0000   1.0000
  -1.250  -0.1435   0.01583   0.00850  -0.0087   1.0000   1.0000
  -1.000  -0.1318   0.01587   0.00836  -0.0066   1.0000   1.0000
  -0.750  -0.1171   0.01599   0.00834  -0.0050   1.0000   1.0000
  -0.500  -0.1006   0.01617   0.00838  -0.0038   1.0000   1.0000
  -0.250  -0.0829   0.01640   0.00849  -0.0029   1.0000   1.0000
   0.000  -0.0645   0.01666   0.00866  -0.0021   1.0000   1.0000
   0.250  -0.0456   0.01697   0.00886  -0.0014   1.0000   1.0000
   0.500  -0.0192   0.01737   0.00918  -0.0023   0.9979   1.0000
   0.750   0.0253   0.01794   0.00969  -0.0067   0.9899   1.0000
   1.000   0.0724   0.01859   0.01029  -0.0116   0.9826   1.0000
   1.250   0.1121   0.01901   0.01070  -0.0149   0.9725   1.0000
   1.500   0.1523   0.01945   0.01115  -0.0183   0.9628   1.0000
   1.750   0.1975   0.01992   0.01166  -0.0225   0.9544   1.0000
   2.000   0.2370   0.02026   0.01207  -0.0255   0.9439   1.0000
   2.250   0.2743   0.02055   0.01244  -0.0280   0.9325   1.0000
   2.500   0.3128   0.02081   0.01280  -0.0306   0.9213   1.0000
   2.750   0.3534   0.02101   0.01312  -0.0335   0.9102   1.0000
   3.000   0.4039   0.02106   0.01340  -0.0380   0.9014   1.0000
   3.250   0.4432   0.02105   0.01358  -0.0403   0.8886   1.0000
   3.500   0.4850   0.02090   0.01366  -0.0428   0.8756   1.0000
   3.750   0.5300   0.02058   0.01366  -0.0456   0.8624   1.0000
   4.000   0.5742   0.02010   0.01351  -0.0480   0.8490   1.0000
   4.250   0.6493   0.01521   0.00897  -0.0480   0.7779   1.0000
   4.500   0.6745   0.01427   0.00728  -0.0426   0.5549   1.0000
   4.750   0.6546   0.01807   0.00821  -0.0338   0.1168   1.0000
   5.000   0.6647   0.01980   0.00968  -0.0303   0.0814   1.0000
   5.250   0.6779   0.02109   0.01098  -0.0275   0.0681   1.0000
   5.500   0.6920   0.02260   0.01241  -0.0250   0.0605   1.0000
   5.750   0.7146   0.02441   0.01423  -0.0235   0.0571   1.0000
   6.000   0.7436   0.02636   0.01627  -0.0231   0.0542   1.0000
   6.250   0.7703   0.02842   0.01835  -0.0228   0.0488   1.0000
   6.500   0.8007   0.03147   0.02157  -0.0228   0.0479   1.0000
   6.750   0.8270   0.03377   0.02438  -0.0213   0.0496   1.0000
   7.000   0.8487   0.03725   0.02858  -0.0187   0.0543   1.0000
  10.500   0.6112   0.10338   0.09890   0.0002   0.1624   1.0000
  10.750   0.6036   0.10747   0.10296  -0.0008   0.1540   1.0000
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