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NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il)
Reynolds number: 100,000
Max Cl/Cd: 46.01 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca001034a08cli02-il-100000-n5.txt
Download as CSV file: xf-naca001034a08cli02-il-100000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3938   0.09266   0.08799  -0.0392   1.0000   0.0249
  -9.750  -0.3995   0.08817   0.08354  -0.0402   1.0000   0.0240
  -9.500  -0.5014   0.09468   0.08977  -0.0370   1.0000   0.0264
  -9.250  -0.5050   0.09009   0.08524  -0.0388   1.0000   0.0249
  -9.000  -0.5111   0.08510   0.08031  -0.0415   1.0000   0.0238
  -8.750  -0.5218   0.07965   0.07493  -0.0452   1.0000   0.0230
  -8.500  -0.5388   0.07548   0.07079  -0.0462   1.0000   0.0226
  -8.250  -0.5578   0.07206   0.06737  -0.0446   1.0000   0.0220
  -8.000  -0.5750   0.06809   0.06333  -0.0429   1.0000   0.0211
  -7.500  -0.5864   0.06215   0.05692  -0.0375   1.0000   0.0181
  -7.250  -0.5939   0.05843   0.05312  -0.0349   1.0000   0.0177
  -7.000  -0.5981   0.05507   0.04958  -0.0322   1.0000   0.0174
  -6.750  -0.5992   0.05174   0.04604  -0.0295   1.0000   0.0171
  -6.500  -0.5974   0.04846   0.04251  -0.0269   1.0000   0.0169
  -6.250  -0.5921   0.04538   0.03911  -0.0243   1.0000   0.0170
  -6.000  -0.5831   0.04267   0.03602  -0.0218   1.0000   0.0175
  -5.750  -0.5708   0.04071   0.03363  -0.0194   1.0000   0.0182
  -5.500  -0.5599   0.03748   0.02997  -0.0172   1.0000   0.0187
  -5.250  -0.5453   0.03447   0.02654  -0.0154   1.0000   0.0189
  -5.000  -0.5191   0.03164   0.02323  -0.0153   0.9979   0.0189
  -4.750  -0.4901   0.02880   0.01986  -0.0157   0.9957   0.0191
  -4.500  -0.4605   0.02634   0.01705  -0.0160   0.9936   0.0197
  -4.250  -0.4306   0.02438   0.01488  -0.0165   0.9912   0.0207
  -4.000  -0.4001   0.02311   0.01347  -0.0173   0.9887   0.0242
  -3.750  -0.3688   0.02185   0.01207  -0.0180   0.9865   0.0272
  -3.500  -0.3405   0.02072   0.01078  -0.0182   0.9831   0.0293
  -3.250  -0.3110   0.01959   0.00952  -0.0189   0.9799   0.0352
  -3.000  -0.2784   0.01882   0.00854  -0.0201   0.9772   0.0477
  -2.750  -0.2544   0.01673   0.00764  -0.0204   0.9740   0.2796
  -2.500  -0.2381   0.01497   0.00793  -0.0174   0.9715   0.7297
  -2.250  -0.2083   0.01524   0.00856  -0.0147   0.9703   0.8997
  -2.000  -0.1652   0.01542   0.00844  -0.0178   0.9683   0.9269
  -1.750  -0.1183   0.01558   0.00830  -0.0220   0.9667   0.9469
  -1.500  -0.0760   0.01567   0.00818  -0.0254   0.9633   0.9646
  -1.250  -0.0296   0.01575   0.00807  -0.0298   0.9606   0.9779
  -1.000   0.0195   0.01581   0.00794  -0.0348   0.9584   0.9885
  -0.750   0.0695   0.01584   0.00783  -0.0401   0.9563   0.9980
  -0.500   0.1026   0.01581   0.00772  -0.0420   0.9502   1.0000
  -0.250   0.1347   0.01578   0.00760  -0.0435   0.9438   1.0000
   0.000   0.1661   0.01576   0.00753  -0.0448   0.9372   1.0000
   0.250   0.1987   0.01573   0.00747  -0.0463   0.9306   1.0000
   0.500   0.2297   0.01571   0.00743  -0.0474   0.9234   1.0000
   0.750   0.2636   0.01566   0.00739  -0.0490   0.9168   1.0000
   1.000   0.2911   0.01564   0.00738  -0.0493   0.9081   1.0000
   1.250   0.3266   0.01555   0.00735  -0.0510   0.9021   1.0000
   1.500   0.3514   0.01553   0.00737  -0.0506   0.8921   1.0000
   1.750   0.3820   0.01546   0.00737  -0.0512   0.8842   1.0000
   2.000   0.4121   0.01537   0.00737  -0.0517   0.8757   1.0000
   2.250   0.4370   0.01534   0.00746  -0.0512   0.8650   1.0000
   2.500   0.4637   0.01527   0.00751  -0.0509   0.8546   1.0000
   2.750   0.4920   0.01517   0.00754  -0.0508   0.8441   1.0000
   3.000   0.5202   0.01505   0.00757  -0.0507   0.8326   1.0000
   3.250   0.5458   0.01495   0.00768  -0.0499   0.8185   1.0000
   3.500   0.5706   0.01486   0.00776  -0.0490   0.8023   1.0000
   3.750   0.5969   0.01475   0.00785  -0.0483   0.7851   1.0000
   4.000   0.6252   0.01435   0.00759  -0.0472   0.7479   1.0000
   4.250   0.6510   0.01415   0.00654  -0.0440   0.5520   1.0000
   4.500   0.6583   0.01539   0.00685  -0.0398   0.3773   1.0000
   4.750   0.6580   0.01771   0.00772  -0.0353   0.1240   1.0000
   5.000   0.6680   0.01942   0.00885  -0.0324   0.0493   1.0000
   5.250   0.6828   0.02060   0.01009  -0.0300   0.0389   1.0000
   5.500   0.7000   0.02148   0.01116  -0.0280   0.0315   1.0000
   5.750   0.7124   0.02289   0.01265  -0.0254   0.0268   1.0000
   6.000   0.7279   0.02432   0.01419  -0.0230   0.0251   1.0000
   6.250   0.7476   0.02588   0.01589  -0.0214   0.0233   1.0000
   6.500   0.7693   0.02733   0.01748  -0.0203   0.0200   1.0000
   6.750   0.7917   0.02914   0.01953  -0.0194   0.0180   1.0000
   7.000   0.8153   0.03159   0.02218  -0.0186   0.0171   1.0000
   7.250   0.8370   0.03460   0.02549  -0.0175   0.0165   1.0000
   7.500   0.8546   0.03800   0.02928  -0.0159   0.0161   1.0000
   7.750   0.8679   0.04145   0.03316  -0.0137   0.0160   1.0000
   8.250   0.8828   0.04752   0.04009  -0.0080   0.0152   1.0000
   8.500   0.8881   0.05010   0.04311  -0.0050   0.0146   1.0000
   8.750   0.8893   0.05313   0.04653  -0.0019   0.0141   1.0000
   9.000   0.8865   0.05641   0.05014   0.0012   0.0139   1.0000
   9.250   0.8796   0.05978   0.05380   0.0044   0.0138   1.0000
   9.500   0.8678   0.06299   0.05725   0.0077   0.0138   1.0000
   9.750   0.8533   0.06632   0.06077   0.0106   0.0139   1.0000
  10.000   0.8373   0.06995   0.06458   0.0124   0.0140   1.0000
  10.250   0.8204   0.07404   0.06883   0.0130   0.0141   1.0000
  10.500   0.8029   0.07872   0.07364   0.0123   0.0142   1.0000
  10.750   0.7855   0.08416   0.07920   0.0100   0.0143   1.0000
  11.000   0.7693   0.09053   0.08566   0.0062   0.0144   1.0000
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