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NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il)
Reynolds number: 1,000,000
Max Cl/Cd: 93.58 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca001034a08cli02-il-1000000.txt
Download as CSV file: xf-naca001034a08cli02-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5151   0.08454   0.08297  -0.0388   1.0000   0.0076
  -9.250  -0.5209   0.07915   0.07760  -0.0422   1.0000   0.0076
  -9.000  -0.5366   0.07293   0.07142  -0.0473   1.0000   0.0074
  -8.750  -0.4733   0.05542   0.05397  -0.0523   0.9984   0.0084
  -8.500  -0.4919   0.04899   0.04743  -0.0577   0.9955   0.0081
  -8.250  -0.4981   0.04337   0.04167  -0.0600   0.9916   0.0082
  -8.000  -0.4939   0.03818   0.03632  -0.0614   0.9883   0.0085
  -7.750  -0.4791   0.03430   0.03226  -0.0625   0.9863   0.0088
  -7.500  -0.4664   0.02973   0.02746  -0.0635   0.9846   0.0089
  -7.250  -0.4523   0.02528   0.02277  -0.0643   0.9831   0.0090
  -7.000  -0.4422   0.02161   0.01885  -0.0632   0.9784   0.0090
  -6.750  -0.4282   0.01815   0.01511  -0.0625   0.9746   0.0090
  -6.500  -0.4121   0.01493   0.01158  -0.0617   0.9715   0.0090
  -6.250  -0.3964   0.01225   0.00860  -0.0604   0.9678   0.0091
  -6.000  -0.4112   0.01780   0.01323  -0.0572   0.9692   0.0070
  -5.750  -0.3900   0.01579   0.01096  -0.0556   0.9649   0.0074
  -5.500  -0.3648   0.01464   0.00965  -0.0550   0.9615   0.0080
  -5.250  -0.3389   0.01360   0.00849  -0.0546   0.9587   0.0084
  -5.000  -0.3132   0.01270   0.00749  -0.0542   0.9560   0.0086
  -4.500  -0.2680   0.01079   0.00538  -0.0522   0.9477   0.0096
  -4.250  -0.2461   0.00980   0.00429  -0.0510   0.9441   0.0102
  -4.000  -0.2219   0.00927   0.00369  -0.0503   0.9404   0.0115
  -3.750  -0.1967   0.00894   0.00332  -0.0498   0.9362   0.0131
  -3.500  -0.1709   0.00863   0.00295  -0.0495   0.9323   0.0144
  -3.250  -0.1448   0.00831   0.00254  -0.0491   0.9289   0.0167
  -3.000  -0.1192   0.00800   0.00219  -0.0487   0.9244   0.0232
  -2.750  -0.0968   0.00722   0.00184  -0.0479   0.9195   0.1474
  -2.500  -0.0768   0.00620   0.00156  -0.0469   0.9151   0.3671
  -2.250  -0.0549   0.00557   0.00143  -0.0461   0.9097   0.5101
  -2.000  -0.0320   0.00510   0.00132  -0.0452   0.9046   0.6243
  -1.750  -0.0078   0.00483   0.00128  -0.0445   0.8997   0.7030
  -1.500   0.0165   0.00463   0.00126  -0.0437   0.8939   0.7639
  -1.250   0.0431   0.00454   0.00121  -0.0434   0.8891   0.7908
  -1.000   0.0700   0.00448   0.00118  -0.0432   0.8836   0.8076
  -0.750   0.0970   0.00442   0.00114  -0.0431   0.8780   0.8237
  -0.500   0.1241   0.00437   0.00111  -0.0429   0.8727   0.8418
  -0.250   0.1508   0.00431   0.00110  -0.0427   0.8662   0.8603
   0.000   0.1778   0.00428   0.00109  -0.0425   0.8603   0.8776
   0.250   0.2046   0.00425   0.00111  -0.0422   0.8530   0.8944
   0.500   0.2316   0.00425   0.00112  -0.0420   0.8461   0.9103
   0.750   0.2586   0.00425   0.00115  -0.0418   0.8374   0.9248
   1.000   0.2859   0.00428   0.00118  -0.0417   0.8282   0.9372
   1.250   0.3137   0.00432   0.00122  -0.0416   0.8171   0.9477
   1.500   0.3414   0.00438   0.00126  -0.0416   0.8049   0.9573
   1.750   0.3704   0.00445   0.00131  -0.0418   0.7928   0.9651
   2.000   0.4007   0.00453   0.00137  -0.0424   0.7790   0.9713
   2.250   0.4324   0.00467   0.00145  -0.0434   0.7497   0.9763
   2.500   0.4604   0.00492   0.00153  -0.0434   0.7021   0.9825
   2.750   0.4938   0.00533   0.00165  -0.0450   0.6272   0.9847
   3.000   0.5249   0.00592   0.00183  -0.0462   0.5288   0.9876
   3.250   0.5538   0.00664   0.00210  -0.0470   0.4144   0.9911
   3.500   0.5792   0.00774   0.00249  -0.0474   0.2498   0.9946
   3.750   0.6052   0.00922   0.00308  -0.0482   0.0484   0.9968
   4.000   0.6383   0.00971   0.00346  -0.0497   0.0205   0.9987
   4.250   0.6685   0.01024   0.00407  -0.0504   0.0147   1.0000
   4.500   0.6891   0.01046   0.00433  -0.0491   0.0137   1.0000
   4.750   0.7088   0.01079   0.00469  -0.0476   0.0123   1.0000
   5.000   0.7281   0.01114   0.00508  -0.0460   0.0108   1.0000
   5.250   0.7395   0.01221   0.00627  -0.0427   0.0089   1.0000
   5.500   0.7572   0.01272   0.00683  -0.0408   0.0085   1.0000
   5.750   0.7756   0.01320   0.00736  -0.0390   0.0081   1.0000
   6.000   0.7935   0.01377   0.00801  -0.0371   0.0077   1.0000
   6.250   0.8118   0.01438   0.00867  -0.0353   0.0071   1.0000
   6.500   0.8307   0.01498   0.00932  -0.0336   0.0065   1.0000
   6.750   0.8496   0.01565   0.01004  -0.0321   0.0060   1.0000
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