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NACA 64A410 (naca64a410-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 64A410 (naca64a410-il)
Reynolds number: 500,000
Max Cl/Cd: 75.21 at α=2.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca64a410-il-500000-n5.txt
Download as CSV file: xf-naca64a410-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4712   0.08381   0.08156  -0.0424   1.0000   0.0072
  -9.500  -0.4812   0.07757   0.07536  -0.0459   1.0000   0.0072
  -9.000  -0.5624   0.03048   0.02708  -0.0858   0.9654   0.0073
  -8.750  -0.5495   0.02629   0.02241  -0.0866   0.9585   0.0076
  -8.500  -0.5243   0.02579   0.02185  -0.0871   0.9542   0.0079
  -8.250  -0.4989   0.02508   0.02101  -0.0876   0.9506   0.0082
  -8.000  -0.4785   0.02327   0.01893  -0.0874   0.9448   0.0087
  -7.750  -0.4583   0.02073   0.01596  -0.0871   0.9394   0.0093
  -7.500  -0.4362   0.01864   0.01348  -0.0868   0.9348   0.0099
  -7.250  -0.4129   0.01734   0.01190  -0.0864   0.9292   0.0103
  -7.000  -0.3895   0.01595   0.01028  -0.0860   0.9244   0.0108
  -6.750  -0.3643   0.01526   0.00949  -0.0858   0.9202   0.0113
  -6.500  -0.3387   0.01479   0.00894  -0.0857   0.9153   0.0119
  -6.250  -0.3128   0.01434   0.00840  -0.0855   0.9108   0.0128
  -6.000  -0.2867   0.01377   0.00770  -0.0853   0.9069   0.0136
  -5.750  -0.2611   0.01317   0.00699  -0.0851   0.9018   0.0142
  -5.500  -0.2358   0.01245   0.00615  -0.0848   0.8970   0.0148
  -5.250  -0.2102   0.01182   0.00545  -0.0845   0.8928   0.0158
  -5.000  -0.1837   0.01150   0.00511  -0.0844   0.8876   0.0169
  -4.750  -0.1571   0.01118   0.00473  -0.0843   0.8825   0.0181
  -4.500  -0.1307   0.01080   0.00426  -0.0841   0.8769   0.0190
  -4.250  -0.1044   0.01046   0.00386  -0.0838   0.8690   0.0198
  -4.000  -0.0781   0.01006   0.00337  -0.0836   0.8616   0.0211
  -3.750  -0.0515   0.00978   0.00308  -0.0834   0.8537   0.0235
  -3.500  -0.0242   0.00958   0.00281  -0.0833   0.8478   0.0261
  -3.250   0.0029   0.00935   0.00255  -0.0833   0.8406   0.0293
  -3.000   0.0301   0.00915   0.00233  -0.0832   0.8338   0.0349
  -2.750   0.0574   0.00898   0.00214  -0.0831   0.8258   0.0411
  -2.500   0.0847   0.00882   0.00194  -0.0830   0.8177   0.0487
  -2.250   0.1117   0.00858   0.00176  -0.0830   0.8084   0.0684
  -2.000   0.1391   0.00846   0.00169  -0.0830   0.7990   0.1075
  -1.750   0.1661   0.00834   0.00155  -0.0828   0.7867   0.1207
  -1.500   0.1931   0.00827   0.00142  -0.0827   0.7724   0.1289
  -1.250   0.2200   0.00818   0.00132  -0.0826   0.7597   0.1443
  -1.000   0.2449   0.00754   0.00119  -0.0825   0.7469   0.3248
  -0.750   0.2699   0.00711   0.00115  -0.0822   0.7338   0.4725
  -0.500   0.2960   0.00696   0.00117  -0.0820   0.7210   0.5463
  -0.250   0.3225   0.00690   0.00120  -0.0817   0.7094   0.5912
   0.000   0.3493   0.00689   0.00123  -0.0815   0.6980   0.6219
   0.250   0.3760   0.00689   0.00127  -0.0813   0.6864   0.6490
   0.750   0.4301   0.00697   0.00134  -0.0810   0.6622   0.6784
   1.000   0.4570   0.00702   0.00139  -0.0809   0.6480   0.6920
   1.500   0.5099   0.00719   0.00151  -0.0803   0.6161   0.7203
   1.750   0.5356   0.00732   0.00159  -0.0800   0.5914   0.7339
   2.000   0.5603   0.00753   0.00170  -0.0794   0.5566   0.7487
   2.250   0.5844   0.00777   0.00183  -0.0787   0.5154   0.7664
   2.500   0.6067   0.00819   0.00200  -0.0778   0.4495   0.7811
   2.750   0.6255   0.00900   0.00235  -0.0765   0.3338   0.7960
   3.000   0.6432   0.00996   0.00281  -0.0750   0.2076   0.8142
   3.250   0.6634   0.01050   0.00315  -0.0738   0.1347   0.8440
   3.500   0.6963   0.01055   0.00337  -0.0749   0.1227   0.9884
   3.750   0.7223   0.01080   0.00360  -0.0748   0.1157   1.0000
   4.000   0.7477   0.01105   0.00383  -0.0745   0.1082   1.0000
   4.250   0.7726   0.01136   0.00409  -0.0741   0.0967   1.0000
   4.500   0.7979   0.01161   0.00428  -0.0738   0.0688   1.0000
   4.750   0.8210   0.01209   0.00462  -0.0732   0.0481   1.0000
   5.000   0.8450   0.01247   0.00499  -0.0727   0.0401   1.0000
   5.250   0.8697   0.01277   0.00532  -0.0722   0.0349   1.0000
   5.500   0.8935   0.01316   0.00569  -0.0717   0.0285   1.0000
   5.750   0.9171   0.01355   0.00607  -0.0711   0.0230   1.0000
   6.000   0.9406   0.01395   0.00649  -0.0705   0.0196   1.0000
   6.250   0.9637   0.01437   0.00692  -0.0699   0.0175   1.0000
   6.500   0.9860   0.01488   0.00744  -0.0691   0.0160   1.0000
   6.750   1.0074   0.01546   0.00809  -0.0681   0.0150   1.0000
   7.000   1.0293   0.01597   0.00866  -0.0672   0.0145   1.0000
   7.250   1.0504   0.01654   0.00929  -0.0663   0.0140   1.0000
   7.500   1.0709   0.01714   0.00996  -0.0652   0.0135   1.0000
   7.750   1.0908   0.01779   0.01067  -0.0641   0.0131   1.0000
   8.000   1.1100   0.01848   0.01142  -0.0629   0.0126   1.0000
   8.250   1.1291   0.01915   0.01216  -0.0617   0.0122   1.0000
   8.500   1.1476   0.01985   0.01291  -0.0604   0.0117   1.0000
   8.750   1.1633   0.02074   0.01386  -0.0587   0.0112   1.0000
   9.000   1.1755   0.02194   0.01515  -0.0565   0.0108   1.0000
   9.250   1.1891   0.02308   0.01639  -0.0545   0.0106   1.0000
   9.500   1.2046   0.02401   0.01742  -0.0529   0.0104   1.0000
   9.750   1.2197   0.02498   0.01852  -0.0512   0.0102   1.0000
  10.000   1.2347   0.02595   0.01960  -0.0496   0.0099   1.0000
  10.250   1.2490   0.02695   0.02072  -0.0480   0.0096   1.0000
  10.500   1.2627   0.02798   0.02187  -0.0464   0.0092   1.0000
  10.750   1.2752   0.02914   0.02315  -0.0447   0.0089   1.0000
  11.000   1.2867   0.03036   0.02449  -0.0429   0.0087   1.0000
  11.250   1.2973   0.03162   0.02587  -0.0412   0.0084   1.0000
  11.500   1.3070   0.03293   0.02729  -0.0394   0.0082   1.0000
  11.750   1.3153   0.03433   0.02881  -0.0377   0.0080   1.0000
  12.000   1.3222   0.03588   0.03049  -0.0360   0.0078   1.0000
  12.250   1.3260   0.03780   0.03255  -0.0341   0.0076   1.0000
  12.500   1.3211   0.04090   0.03587  -0.0318   0.0073   1.0000
  12.750   1.3245   0.04284   0.03800  -0.0303   0.0072   1.0000
  13.000   1.3263   0.04503   0.04038  -0.0289   0.0071   1.0000
  13.250   1.3255   0.04756   0.04312  -0.0276   0.0069   1.0000
  13.500   1.3213   0.05061   0.04637  -0.0265   0.0067   1.0000
  13.750   1.3153   0.05395   0.04993  -0.0258   0.0066   1.0000
  14.000   1.3064   0.05780   0.05399  -0.0254   0.0064   1.0000
  14.250   1.2942   0.06229   0.05869  -0.0255   0.0063   1.0000
  14.500   1.2796   0.06733   0.06395  -0.0263   0.0062   1.0000
  14.750   1.2628   0.07309   0.06991  -0.0278   0.0062   1.0000
  15.000   1.2435   0.07973   0.07675  -0.0302   0.0061   1.0000
  15.250   1.2212   0.08746   0.08469  -0.0336   0.0061   1.0000
  15.500   1.1946   0.09686   0.09430  -0.0385   0.0062   1.0000
  15.750   1.1631   0.10840   0.10605  -0.0452   0.0062   1.0000
  16.000   1.1197   0.12496   0.12282  -0.0553   0.0064   1.0000
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