Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 64A410 (naca64a410-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 64A410 (naca64a410-il)
Reynolds number: 200,000
Max Cl/Cd: 71.27 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca64a410-il-200000-n5.txt
Download as CSV file: xf-naca64a410-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64A410                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4310   0.08885   0.08529  -0.0422   1.0000   0.0181
  -9.000  -0.4346   0.08478   0.08128  -0.0438   1.0000   0.0177
  -8.750  -0.4430   0.08090   0.07747  -0.0446   1.0000   0.0172
  -8.500  -0.4590   0.07771   0.07437  -0.0440   1.0000   0.0169
  -8.250  -0.4786   0.07441   0.07116  -0.0438   0.9985   0.0167
  -8.000  -0.4781   0.05505   0.05145  -0.0671   0.9864   0.0149
  -7.750  -0.4687   0.04632   0.04229  -0.0729   0.9792   0.0147
  -7.500  -0.4524   0.04008   0.03560  -0.0769   0.9745   0.0148
  -7.250  -0.4342   0.03590   0.03102  -0.0787   0.9688   0.0151
  -7.000  -0.4087   0.03245   0.02718  -0.0810   0.9655   0.0156
  -6.750  -0.3837   0.03011   0.02451  -0.0821   0.9614   0.0164
  -6.500  -0.3588   0.02787   0.02189  -0.0828   0.9564   0.0179
  -6.250  -0.3305   0.02494   0.01840  -0.0837   0.9529   0.0190
  -6.000  -0.3000   0.02264   0.01560  -0.0847   0.9502   0.0197
  -5.750  -0.2767   0.02092   0.01355  -0.0841   0.9442   0.0204
  -5.500  -0.2483   0.01969   0.01221  -0.0848   0.9403   0.0219
  -5.250  -0.2173   0.01888   0.01127  -0.0857   0.9373   0.0239
  -5.000  -0.1907   0.01785   0.01009  -0.0855   0.9325   0.0251
  -4.750  -0.1638   0.01692   0.00904  -0.0854   0.9274   0.0263
  -4.500  -0.1342   0.01619   0.00817  -0.0858   0.9237   0.0277
  -4.250  -0.1080   0.01532   0.00732  -0.0858   0.9189   0.0304
  -4.000  -0.0822   0.01476   0.00672  -0.0855   0.9130   0.0328
  -3.750  -0.0535   0.01418   0.00607  -0.0857   0.9088   0.0355
  -3.500  -0.0274   0.01369   0.00549  -0.0854   0.9031   0.0387
  -3.250  -0.0009   0.01322   0.00498  -0.0853   0.8973   0.0455
  -3.000   0.0278   0.01275   0.00445  -0.0855   0.8931   0.0551
  -2.750   0.0527   0.01231   0.00420  -0.0852   0.8862   0.0937
  -2.500   0.0804   0.01196   0.00389  -0.0852   0.8804   0.1327
  -2.250   0.1055   0.01134   0.00363  -0.0850   0.8730   0.2309
  -2.000   0.1287   0.01038   0.00347  -0.0846   0.8655   0.4609
  -1.750   0.1530   0.01007   0.00346  -0.0837   0.8567   0.5625
  -1.500   0.1793   0.00988   0.00338  -0.0831   0.8494   0.6192
  -1.250   0.2040   0.00979   0.00338  -0.0823   0.8400   0.6632
  -1.000   0.2308   0.00970   0.00331  -0.0818   0.8333   0.6933
  -0.750   0.2566   0.00965   0.00328  -0.0813   0.8238   0.7157
  -0.500   0.2832   0.00958   0.00320  -0.0808   0.8144   0.7325
  -0.250   0.3102   0.00950   0.00310  -0.0804   0.8051   0.7483
   0.000   0.3367   0.00946   0.00306  -0.0801   0.7950   0.7625
   0.250   0.3637   0.00942   0.00301  -0.0798   0.7860   0.7764
   0.500   0.3909   0.00936   0.00295  -0.0795   0.7772   0.7911
   0.750   0.4175   0.00931   0.00294  -0.0791   0.7674   0.8071
   1.000   0.4441   0.00926   0.00293  -0.0786   0.7582   0.8274
   1.250   0.4712   0.00918   0.00292  -0.0782   0.7489   0.8588
   1.500   0.5048   0.00910   0.00295  -0.0792   0.7383   0.9163
   1.750   0.5450   0.00909   0.00294  -0.0818   0.7256   1.0000
   2.000   0.5718   0.00918   0.00299  -0.0817   0.7145   1.0000
   2.250   0.5986   0.00929   0.00306  -0.0815   0.7032   1.0000
   2.500   0.6250   0.00941   0.00316  -0.0812   0.6906   1.0000
   2.750   0.6508   0.00954   0.00326  -0.0808   0.6723   1.0000
   3.000   0.6757   0.00970   0.00335  -0.0802   0.6476   1.0000
   3.500   0.7234   0.01015   0.00356  -0.0785   0.5821   1.0000
   3.750   0.7455   0.01049   0.00374  -0.0773   0.5356   1.0000
   4.000   0.7656   0.01099   0.00395  -0.0759   0.4721   1.0000
   4.250   0.7809   0.01187   0.00432  -0.0738   0.3662   1.0000
   4.500   0.7936   0.01314   0.00496  -0.0716   0.2445   1.0000
   5.000   0.8290   0.01501   0.00619  -0.0689   0.1228   1.0000
   5.250   0.8504   0.01560   0.00672  -0.0681   0.1003   1.0000
   5.500   0.8698   0.01638   0.00723  -0.0669   0.0548   1.0000
   5.750   0.8897   0.01712   0.00797  -0.0658   0.0434   1.0000
   6.000   0.9099   0.01782   0.00875  -0.0646   0.0370   1.0000
   6.250   0.9299   0.01853   0.00953  -0.0635   0.0322   1.0000
   6.500   0.9477   0.01945   0.01050  -0.0620   0.0290   1.0000
   6.750   0.9668   0.02022   0.01137  -0.0607   0.0271   1.0000
   7.000   0.9855   0.02101   0.01224  -0.0593   0.0251   1.0000
   7.250   1.0040   0.02180   0.01309  -0.0581   0.0232   1.0000
   7.500   1.0191   0.02294   0.01425  -0.0564   0.0217   1.0000
   7.750   1.0352   0.02409   0.01547  -0.0547   0.0210   1.0000
   8.000   1.0527   0.02519   0.01667  -0.0533   0.0204   1.0000
   8.250   1.0706   0.02639   0.01799  -0.0519   0.0197   1.0000
   8.500   1.0896   0.02773   0.01946  -0.0507   0.0191   1.0000
   8.750   1.1099   0.02920   0.02106  -0.0497   0.0185   1.0000
   9.000   1.1299   0.03069   0.02271  -0.0488   0.0179   1.0000
   9.250   1.1475   0.03197   0.02412  -0.0476   0.0171   1.0000
   9.500   1.1629   0.03317   0.02542  -0.0462   0.0163   1.0000
   9.750   1.1782   0.03484   0.02720  -0.0449   0.0157   1.0000
  10.000   1.1941   0.03781   0.03041  -0.0439   0.0152   1.0000
  10.250   1.2046   0.03987   0.03281  -0.0418   0.0150   1.0000
  10.500   1.2114   0.04222   0.03550  -0.0394   0.0147   1.0000
  10.750   1.2137   0.04482   0.03844  -0.0366   0.0145   1.0000
  11.000   1.2115   0.04752   0.04149  -0.0335   0.0141   1.0000
  11.250   1.2059   0.05037   0.04466  -0.0306   0.0137   1.0000
  11.500   1.1976   0.05339   0.04799  -0.0279   0.0134   1.0000
  11.750   1.1874   0.05662   0.05149  -0.0256   0.0130   1.0000
  12.000   1.1750   0.06017   0.05528  -0.0239   0.0128   1.0000
  12.250   1.1598   0.06426   0.05963  -0.0227   0.0126   1.0000
  12.500   1.1418   0.06896   0.06457  -0.0223   0.0125   1.0000
  12.750   1.1210   0.07445   0.07030  -0.0230   0.0125   1.0000
  13.000   1.0978   0.08083   0.07690  -0.0248   0.0125   1.0000
  13.250   1.0720   0.08837   0.08465  -0.0280   0.0126   1.0000
  13.500   1.0435   0.09750   0.09398  -0.0331   0.0128   1.0000
  13.750   1.0101   0.10971   0.10638  -0.0410   0.0132   1.0000
<< Back to NACA 64A410 (naca64a410-il)

Polar data table (+)

Polar graphs


<< Back to NACA 64A410 (naca64a410-il)