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NACA 642-015A AIRFOIL (n64015a-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 642-015A AIRFOIL (n64015a-il)
Reynolds number: 100,000
Max Cl/Cd: 43.17 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n64015a-il-100000.txt
Download as CSV file: xf-n64015a-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 642-015A AIRFOIL                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.6264   0.12887   0.12365  -0.0075   1.0000   0.1618
 -12.250  -0.7671   0.07011   0.06457  -0.0482   1.0000   0.0776
 -12.000  -0.9045   0.07581   0.06979  -0.0397   1.0000   0.0771
 -11.750  -0.8913   0.07015   0.06409  -0.0402   1.0000   0.0755
 -11.500  -0.9016   0.06595   0.05975  -0.0389   1.0000   0.0746
 -11.250  -0.9160   0.06220   0.05583  -0.0366   1.0000   0.0735
 -11.000  -0.9286   0.05853   0.05192  -0.0339   1.0000   0.0724
 -10.750  -0.9384   0.05470   0.04777  -0.0310   1.0000   0.0710
 -10.500  -0.9454   0.05099   0.04365  -0.0280   1.0000   0.0698
 -10.250  -0.9468   0.04757   0.03980  -0.0251   1.0000   0.0690
 -10.000  -0.9414   0.04457   0.03643  -0.0227   1.0000   0.0688
  -9.750  -0.9301   0.04204   0.03362  -0.0208   1.0000   0.0695
  -9.500  -0.9164   0.03995   0.03132  -0.0192   1.0000   0.0713
  -9.250  -0.9022   0.03794   0.02902  -0.0174   1.0000   0.0733
  -9.000  -0.8860   0.03598   0.02675  -0.0156   1.0000   0.0750
  -8.750  -0.8680   0.03424   0.02469  -0.0140   1.0000   0.0765
  -8.500  -0.8383   0.03162   0.02212  -0.0146   1.0000   0.0797
  -8.250  -0.8174   0.03026   0.02075  -0.0137   1.0000   0.0843
  -8.000  -0.7980   0.02910   0.01940  -0.0122   1.0000   0.0890
  -7.750  -0.7715   0.02726   0.01778  -0.0121   1.0000   0.0951
  -7.500  -0.7561   0.02634   0.01677  -0.0100   1.0000   0.1026
  -7.250  -0.7429   0.02503   0.01571  -0.0079   1.0000   0.1115
  -7.000  -0.7362   0.02402   0.01482  -0.0045   1.0000   0.1213
  -6.750  -0.7346   0.02317   0.01408  -0.0003   1.0000   0.1336
  -6.500  -0.7367   0.02230   0.01337   0.0043   1.0000   0.1490
  -6.250  -0.7403   0.02130   0.01259   0.0091   1.0000   0.1742
  -6.000  -0.7484   0.01972   0.01161   0.0141   1.0000   0.2323
  -5.750  -0.7628   0.01767   0.01103   0.0202   1.0000   0.4279
  -5.500  -0.7567   0.01777   0.01145   0.0244   1.0000   0.5407
  -5.250  -0.7436   0.01818   0.01187   0.0273   1.0000   0.5851
  -5.000  -0.7193   0.01882   0.01248   0.0283   0.9971   0.6192
  -4.750  -0.6788   0.01973   0.01331   0.0266   0.9890   0.6498
  -4.500  -0.6379   0.02055   0.01404   0.0247   0.9813   0.6746
  -4.250  -0.5991   0.02129   0.01471   0.0234   0.9729   0.6944
  -4.000  -0.5603   0.02235   0.01575   0.0229   0.9655   0.7136
  -3.750  -0.5190   0.02353   0.01689   0.0224   0.9586   0.7329
  -3.500  -0.4799   0.02412   0.01739   0.0211   0.9514   0.7471
  -3.250  -0.4432   0.02416   0.01731   0.0192   0.9434   0.7595
  -3.000  -0.3914   0.02462   0.01767   0.0154   0.9394   0.7664
  -2.750  -0.3660   0.02432   0.01727   0.0150   0.9289   0.7766
  -2.500  -0.3119   0.02453   0.01738   0.0104   0.9250   0.7820
  -2.250  -0.2917   0.02411   0.01687   0.0106   0.9142   0.7920
  -2.000  -0.2423   0.02420   0.01690   0.0068   0.9097   0.7962
  -1.750  -0.2135   0.02410   0.01674   0.0061   0.9010   0.8033
  -1.500  -0.1798   0.02381   0.01639   0.0044   0.8939   0.8104
  -1.250  -0.1428   0.02383   0.01638   0.0027   0.8872   0.8154
  -1.000  -0.1238   0.02352   0.01601   0.0033   0.8782   0.8250
  -0.750  -0.0766   0.02350   0.01597   0.0000   0.8744   0.8287
  -0.500  -0.0579   0.02355   0.01601   0.0011   0.8639   0.8361
  -0.250  -0.0247   0.02333   0.01577  -0.0001   0.8586   0.8434
   0.000   0.0000   0.02354   0.01600   0.0000   0.8497   0.8497
   0.250   0.0247   0.02333   0.01577   0.0001   0.8434   0.8586
   0.500   0.0579   0.02355   0.01601  -0.0011   0.8361   0.8639
   0.750   0.0766   0.02350   0.01597   0.0000   0.8287   0.8744
   1.000   0.1237   0.02352   0.01601  -0.0033   0.8250   0.8782
   1.250   0.1427   0.02383   0.01638  -0.0027   0.8154   0.8872
   1.500   0.1798   0.02381   0.01639  -0.0044   0.8104   0.8939
   1.750   0.2135   0.02409   0.01674  -0.0061   0.8033   0.9011
   2.000   0.2424   0.02420   0.01690  -0.0068   0.7962   0.9097
   2.250   0.2917   0.02410   0.01687  -0.0106   0.7920   0.9142
   2.500   0.3119   0.02452   0.01738  -0.0104   0.7820   0.9250
   2.750   0.3659   0.02432   0.01726  -0.0150   0.7766   0.9289
   3.000   0.3911   0.02461   0.01767  -0.0154   0.7664   0.9394
   3.250   0.4432   0.02416   0.01730  -0.0192   0.7595   0.9435
   3.500   0.4799   0.02412   0.01739  -0.0211   0.7471   0.9515
   3.750   0.5190   0.02352   0.01689  -0.0224   0.7329   0.9587
   4.000   0.5603   0.02235   0.01574  -0.0229   0.7136   0.9655
   4.250   0.5991   0.02128   0.01471  -0.0234   0.6944   0.9730
   4.500   0.6378   0.02055   0.01404  -0.0247   0.6746   0.9813
   4.750   0.6788   0.01972   0.01331  -0.0266   0.6498   0.9891
   5.000   0.7193   0.01882   0.01248  -0.0283   0.6193   0.9972
   5.250   0.7434   0.01818   0.01187  -0.0273   0.5852   1.0000
   5.500   0.7565   0.01776   0.01145  -0.0244   0.5409   1.0000
   5.750   0.7628   0.01767   0.01103  -0.0202   0.4291   1.0000
   6.000   0.7484   0.01971   0.01160  -0.0141   0.2329   1.0000
   6.250   0.7402   0.02129   0.01258  -0.0090   0.1744   1.0000
   6.500   0.7366   0.02229   0.01336  -0.0043   0.1490   1.0000
   6.750   0.7345   0.02316   0.01407   0.0003   0.1337   1.0000
   7.000   0.7362   0.02401   0.01481   0.0045   0.1214   1.0000
   7.250   0.7428   0.02502   0.01570   0.0079   0.1115   1.0000
   7.500   0.7561   0.02634   0.01677   0.0100   0.1026   1.0000
   7.750   0.7715   0.02725   0.01778   0.0121   0.0952   1.0000
   8.000   0.7980   0.02910   0.01940   0.0121   0.0890   1.0000
   8.250   0.8174   0.03026   0.02074   0.0137   0.0843   1.0000
   8.500   0.8383   0.03162   0.02212   0.0146   0.0797   1.0000
   8.750   0.8680   0.03424   0.02469   0.0140   0.0765   1.0000
   9.000   0.8860   0.03598   0.02674   0.0156   0.0750   1.0000
   9.250   0.9023   0.03795   0.02902   0.0174   0.0733   1.0000
   9.500   0.9165   0.03996   0.03132   0.0191   0.0713   1.0000
   9.750   0.9302   0.04204   0.03362   0.0208   0.0695   1.0000
  10.000   0.9415   0.04458   0.03644   0.0226   0.0688   1.0000
  10.250   0.9470   0.04757   0.03981   0.0250   0.0690   1.0000
  10.500   0.9456   0.05100   0.04366   0.0279   0.0698   1.0000
  10.750   0.9386   0.05472   0.04779   0.0310   0.0710   1.0000
  11.000   0.9289   0.05856   0.05195   0.0338   0.0724   1.0000
  11.250   0.9164   0.06224   0.05586   0.0365   0.0736   1.0000
  11.500   0.9022   0.06600   0.05980   0.0388   0.0746   1.0000
  11.750   0.8920   0.07021   0.06415   0.0400   0.0755   1.0000
  12.000   0.9050   0.07583   0.06982   0.0396   0.0771   1.0000
  12.250   0.6637   0.10804   0.10285   0.0190   0.1074   1.0000
  12.500   0.6283   0.12891   0.12369   0.0073   0.1618   1.0000
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