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NACA 64-210 (naca64210-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 64-210 (naca64210-il)
Reynolds number: 50,000
Max Cl/Cd: 30.29 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca64210-il-50000.txt
Download as CSV file: xf-naca64210-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-210                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5253   0.12428   0.11709   0.0014   1.0000   0.2539
 -10.250  -0.5335   0.12213   0.11502   0.0001   1.0000   0.2653
 -10.000  -0.5343   0.11959   0.11252  -0.0004   1.0000   0.2787
  -9.750  -0.5070   0.11414   0.10702   0.0013   1.0000   0.2977
  -9.500  -0.4981   0.11077   0.10368   0.0018   1.0000   0.3160
  -9.250  -0.4953   0.10791   0.10086   0.0019   1.0000   0.3335
  -9.000  -0.5013   0.10580   0.09882   0.0020   1.0000   0.3505
  -8.500  -0.4726   0.09777   0.09078   0.0031   1.0000   0.3840
  -8.250  -0.4627   0.09446   0.08748   0.0036   1.0000   0.4009
  -8.000  -0.4714   0.09288   0.08600   0.0046   1.0000   0.4222
  -7.750  -0.4544   0.08870   0.08182   0.0050   1.0000   0.4389
  -7.000  -0.5823   0.06145   0.05483  -0.0328   1.0000   0.2028
  -6.750  -0.5860   0.05374   0.04640  -0.0372   1.0000   0.1608
  -6.500  -0.5759   0.04874   0.04092  -0.0374   1.0000   0.1443
  -6.250  -0.5637   0.04461   0.03609  -0.0368   1.0000   0.1327
  -6.000  -0.5480   0.04099   0.03210  -0.0358   1.0000   0.1274
  -5.750  -0.5307   0.03800   0.02824  -0.0344   1.0000   0.1219
  -5.500  -0.5119   0.03521   0.02530  -0.0332   1.0000   0.1240
  -5.250  -0.4923   0.03296   0.02279  -0.0320   1.0000   0.1275
  -5.000  -0.4711   0.03081   0.02029  -0.0306   1.0000   0.1293
  -4.750  -0.4488   0.02889   0.01805  -0.0291   1.0000   0.1318
  -4.500  -0.4268   0.02714   0.01615  -0.0276   1.0000   0.1382
  -4.250  -0.4053   0.02580   0.01470  -0.0260   1.0000   0.1492
  -4.000  -0.3845   0.02433   0.01336  -0.0240   1.0000   0.1606
  -3.750  -0.3659   0.02300   0.01212  -0.0221   1.0000   0.1812
  -3.500  -0.3486   0.02143   0.01084  -0.0205   1.0000   0.2200
  -3.250  -0.3504   0.01847   0.01069  -0.0142   1.0000   0.6192
  -3.000  -0.1079   0.02269   0.01354  -0.0257   1.0000   0.9762
  -2.750  -0.0500   0.02158   0.01206  -0.0334   1.0000   0.9942
  -2.500  -0.0254   0.02097   0.01133  -0.0351   1.0000   1.0000
  -2.250  -0.0241   0.02077   0.01112  -0.0326   1.0000   1.0000
  -2.000  -0.0282   0.02067   0.01102  -0.0293   1.0000   1.0000
  -1.750  -0.0369   0.02061   0.01097  -0.0253   1.0000   1.0000
  -1.500  -0.0485   0.02056   0.01091  -0.0210   1.0000   1.0000
  -1.250  -0.0617   0.02045   0.01080  -0.0166   1.0000   1.0000
  -1.000  -0.0759   0.02028   0.01062  -0.0121   1.0000   1.0000
  -0.750  -0.0902   0.02003   0.01035  -0.0076   1.0000   1.0000
  -0.500  -0.1014   0.01976   0.01001  -0.0035   1.0000   1.0000
  -0.250  -0.1015   0.01963   0.00978  -0.0011   1.0000   1.0000
   0.000  -0.0899   0.01971   0.00973  -0.0004   1.0000   1.0000
   0.250  -0.0733   0.01993   0.00982  -0.0005   1.0000   1.0000
   0.500  -0.0545   0.02024   0.01000  -0.0008   1.0000   1.0000
   0.750  -0.0348   0.02062   0.01027  -0.0011   1.0000   1.0000
   1.000  -0.0149   0.02106   0.01060  -0.0015   1.0000   1.0000
   1.250   0.0052   0.02154   0.01101  -0.0019   1.0000   1.0000
   1.500   0.0254   0.02207   0.01148  -0.0023   1.0000   1.0000
   1.750   0.0452   0.02265   0.01201  -0.0026   1.0000   1.0000
   2.000   0.0767   0.02355   0.01290  -0.0052   0.9949   1.0000
   2.250   0.1160   0.02464   0.01400  -0.0092   0.9852   1.0000
   2.500   0.1530   0.02569   0.01509  -0.0127   0.9750   1.0000
   2.750   0.1901   0.02678   0.01626  -0.0161   0.9645   1.0000
   3.000   0.2290   0.02795   0.01752  -0.0198   0.9535   1.0000
   3.250   0.2675   0.02910   0.01879  -0.0233   0.9418   1.0000
   3.500   0.2998   0.03012   0.01997  -0.0257   0.9292   1.0000
   3.750   0.3338   0.03120   0.02121  -0.0282   0.9158   1.0000
   4.000   0.3704   0.03231   0.02252  -0.0310   0.9007   1.0000
   4.250   0.4143   0.03344   0.02395  -0.0346   0.8831   1.0000
   4.500   0.4461   0.03430   0.02507  -0.0360   0.8616   1.0000
   4.750   0.4959   0.03488   0.02605  -0.0391   0.8333   1.0000
   5.000   0.6736   0.02224   0.01479  -0.0342   0.6651   1.0000
   5.250   0.6607   0.02192   0.01221  -0.0202   0.2805   1.0000
   5.500   0.6654   0.02509   0.01429  -0.0172   0.1946   1.0000
   5.750   0.6883   0.02727   0.01615  -0.0159   0.1637   1.0000
   6.000   0.7194   0.02923   0.01804  -0.0155   0.1416   1.0000
   6.250   0.7560   0.03163   0.02046  -0.0156   0.1307   1.0000
   6.500   0.7866   0.03420   0.02305  -0.0155   0.1210   1.0000
   6.750   0.8145   0.03679   0.02611  -0.0149   0.1168   1.0000
   7.000   0.8403   0.03984   0.02958  -0.0141   0.1155   1.0000
   7.250   0.8622   0.04311   0.03332  -0.0131   0.1150   1.0000
   7.500   0.8808   0.04643   0.03704  -0.0121   0.1132   1.0000
   7.750   0.8959   0.05005   0.04112  -0.0109   0.1129   1.0000
   8.000   0.9040   0.05442   0.04614  -0.0094   0.1169   1.0000
   8.250   0.9143   0.05923   0.05128  -0.0085   0.1212   1.0000
   8.500   0.9079   0.06419   0.05696  -0.0073   0.1299   1.0000
   8.750   0.9087   0.06975   0.06284  -0.0070   0.1396   1.0000
   9.250   0.8631   0.08288   0.07656  -0.0096   0.1671   1.0000
   9.500   0.8107   0.08971   0.08337  -0.0144   0.1706   1.0000
   9.750   0.6872   0.11633   0.10958  -0.0491   0.3585   1.0000
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