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NACA 642-015A AIRFOIL (n64015a-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 642-015A AIRFOIL (n64015a-il)
Reynolds number: 100,000
Max Cl/Cd: 36.81 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n64015a-il-100000-n5.txt
Download as CSV file: xf-n64015a-il-100000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.000  -0.7511   0.11842   0.11288  -0.0148   1.0000   0.0333
 -14.750  -0.7867   0.10562   0.09996  -0.0228   1.0000   0.0330
 -14.500  -0.8199   0.09535   0.08953  -0.0293   1.0000   0.0327
 -14.250  -0.8495   0.08708   0.08106  -0.0340   1.0000   0.0325
 -14.000  -0.8757   0.08015   0.07393  -0.0373   1.0000   0.0324
 -13.750  -0.8987   0.07420   0.06775  -0.0396   1.0000   0.0323
 -13.500  -0.9188   0.06903   0.06232  -0.0410   1.0000   0.0323
 -13.250  -0.9358   0.06449   0.05752  -0.0416   1.0000   0.0324
 -13.000  -0.9498   0.06046   0.05322  -0.0415   1.0000   0.0325
 -12.750  -0.9606   0.05686   0.04931  -0.0410   1.0000   0.0327
 -12.500  -0.9681   0.05362   0.04577  -0.0399   1.0000   0.0329
 -12.250  -0.9722   0.05071   0.04254  -0.0387   1.0000   0.0332
 -12.000  -0.9719   0.04808   0.03963  -0.0372   1.0000   0.0336
 -11.750  -0.9620   0.04587   0.03732  -0.0364   1.0000   0.0341
 -11.500  -0.9522   0.04404   0.03540  -0.0354   1.0000   0.0348
 -11.250  -0.9424   0.04240   0.03366  -0.0343   1.0000   0.0357
 -11.000  -0.9316   0.04079   0.03191  -0.0331   1.0000   0.0368
 -10.750  -0.9186   0.03916   0.03008  -0.0319   1.0000   0.0381
 -10.500  -0.9023   0.03751   0.02823  -0.0310   1.0000   0.0394
 -10.250  -0.8834   0.03595   0.02644  -0.0301   1.0000   0.0405
 -10.000  -0.8641   0.03443   0.02495  -0.0295   1.0000   0.0417
  -9.750  -0.8476   0.03317   0.02369  -0.0286   1.0000   0.0431
  -9.500  -0.8321   0.03203   0.02250  -0.0274   1.0000   0.0451
  -9.250  -0.8163   0.03096   0.02132  -0.0261   1.0000   0.0476
  -9.000  -0.8020   0.02982   0.02015  -0.0246   1.0000   0.0499
  -8.750  -0.7908   0.02879   0.01915  -0.0227   1.0000   0.0522
  -8.500  -0.7799   0.02784   0.01818  -0.0206   1.0000   0.0549
  -8.250  -0.7688   0.02702   0.01725  -0.0183   1.0000   0.0584
  -8.000  -0.7616   0.02606   0.01638  -0.0156   1.0000   0.0620
  -7.750  -0.7532   0.02530   0.01560  -0.0128   1.0000   0.0665
  -7.500  -0.7476   0.02453   0.01485  -0.0095   1.0000   0.0713
  -7.250  -0.7432   0.02385   0.01420  -0.0060   1.0000   0.0772
  -7.000  -0.7404   0.02323   0.01360  -0.0022   1.0000   0.0840
  -6.750  -0.7294   0.02252   0.01292  -0.0001   0.9968   0.0951
  -6.500  -0.7004   0.02138   0.01195  -0.0017   0.9866   0.1203
  -6.250  -0.6737   0.02012   0.01099  -0.0030   0.9760   0.1690
  -6.000  -0.6517   0.01859   0.01001  -0.0037   0.9646   0.2620
  -5.750  -0.6341   0.01723   0.00949  -0.0029   0.9524   0.3973
  -5.500  -0.6063   0.01690   0.00945  -0.0031   0.9429   0.4872
  -5.250  -0.5777   0.01681   0.00936  -0.0032   0.9324   0.5301
  -5.000  -0.5490   0.01678   0.00928  -0.0033   0.9223   0.5593
  -4.750  -0.5182   0.01679   0.00920  -0.0037   0.9137   0.5842
  -4.500  -0.4915   0.01690   0.00927  -0.0031   0.9029   0.6069
  -4.250  -0.4622   0.01708   0.00941  -0.0028   0.8947   0.6293
  -4.000  -0.4353   0.01720   0.00948  -0.0022   0.8845   0.6456
  -3.750  -0.4070   0.01723   0.00942  -0.0020   0.8756   0.6573
  -3.500  -0.3802   0.01714   0.00920  -0.0018   0.8665   0.6680
  -3.250  -0.3515   0.01714   0.00914  -0.0017   0.8575   0.6751
  -3.000  -0.3248   0.01698   0.00884  -0.0016   0.8491   0.6836
  -2.750  -0.2967   0.01694   0.00875  -0.0015   0.8402   0.6888
  -2.500  -0.2691   0.01682   0.00853  -0.0015   0.8324   0.6956
  -2.250  -0.2429   0.01672   0.00836  -0.0012   0.8234   0.7017
  -2.000  -0.2145   0.01665   0.00822  -0.0012   0.8161   0.7071
  -1.750  -0.1892   0.01655   0.00804  -0.0010   0.8077   0.7143
  -1.500  -0.1610   0.01649   0.00795  -0.0009   0.8004   0.7195
  -1.250  -0.1341   0.01645   0.00787  -0.0008   0.7927   0.7253
  -1.000  -0.1082   0.01637   0.00772  -0.0005   0.7851   0.7326
  -0.750  -0.0800   0.01636   0.00770  -0.0005   0.7786   0.7378
  -0.500  -0.0541   0.01633   0.00766  -0.0003   0.7709   0.7447
  -0.250  -0.0262   0.01629   0.00757  -0.0002   0.7652   0.7509
   0.000   0.0000   0.01632   0.00764   0.0000   0.7572   0.7572
   0.250   0.0263   0.01629   0.00757   0.0002   0.7509   0.7652
   0.500   0.0541   0.01633   0.00766   0.0003   0.7447   0.7709
   0.750   0.0801   0.01636   0.00770   0.0005   0.7378   0.7786
   1.000   0.1082   0.01637   0.00772   0.0005   0.7326   0.7851
   1.250   0.1341   0.01645   0.00787   0.0008   0.7253   0.7927
   1.500   0.1610   0.01649   0.00795   0.0009   0.7195   0.8005
   1.750   0.1892   0.01655   0.00804   0.0010   0.7143   0.8077
   2.000   0.2145   0.01665   0.00822   0.0012   0.7071   0.8161
   2.250   0.2429   0.01672   0.00836   0.0012   0.7017   0.8235
   2.500   0.2691   0.01682   0.00853   0.0015   0.6956   0.8324
   2.750   0.2967   0.01694   0.00875   0.0015   0.6888   0.8402
   3.000   0.3248   0.01698   0.00884   0.0016   0.6836   0.8491
   3.250   0.3515   0.01713   0.00914   0.0017   0.6751   0.8575
   3.500   0.3802   0.01714   0.00920   0.0018   0.6680   0.8665
   3.750   0.4070   0.01723   0.00942   0.0020   0.6573   0.8756
   4.000   0.4353   0.01720   0.00947   0.0022   0.6456   0.8845
   4.250   0.4622   0.01707   0.00941   0.0028   0.6293   0.8947
   4.500   0.4915   0.01690   0.00927   0.0031   0.6069   0.9030
   4.750   0.5182   0.01678   0.00920   0.0037   0.5842   0.9137
   5.000   0.5490   0.01678   0.00928   0.0033   0.5593   0.9224
   5.250   0.5777   0.01681   0.00936   0.0032   0.5300   0.9324
   5.500   0.6063   0.01690   0.00944   0.0031   0.4872   0.9429
   5.750   0.6342   0.01723   0.00949   0.0029   0.3973   0.9525
   6.000   0.6518   0.01859   0.01000   0.0036   0.2619   0.9646
   6.250   0.6738   0.02012   0.01099   0.0030   0.1690   0.9760
   6.500   0.7005   0.02138   0.01194   0.0017   0.1202   0.9867
   6.750   0.7295   0.02252   0.01291   0.0000   0.0951   0.9969
   7.000   0.7404   0.02322   0.01359   0.0022   0.0840   1.0000
   7.250   0.7432   0.02385   0.01420   0.0060   0.0772   1.0000
   7.500   0.7476   0.02453   0.01484   0.0095   0.0713   1.0000
   7.750   0.7533   0.02529   0.01560   0.0128   0.0665   1.0000
   8.000   0.7617   0.02605   0.01637   0.0155   0.0619   1.0000
   8.250   0.7690   0.02701   0.01725   0.0182   0.0583   1.0000
   8.500   0.7802   0.02784   0.01818   0.0205   0.0549   1.0000
   8.750   0.7911   0.02879   0.01915   0.0227   0.0522   1.0000
   9.000   0.8025   0.02982   0.02015   0.0245   0.0499   1.0000
   9.250   0.8168   0.03096   0.02132   0.0260   0.0475   1.0000
   9.500   0.8327   0.03203   0.02250   0.0273   0.0451   1.0000
   9.750   0.8482   0.03317   0.02370   0.0285   0.0431   1.0000
  10.000   0.8647   0.03443   0.02496   0.0294   0.0417   1.0000
  10.250   0.8841   0.03596   0.02645   0.0300   0.0405   1.0000
  10.500   0.9029   0.03752   0.02824   0.0309   0.0394   1.0000
  10.750   0.9192   0.03916   0.03009   0.0318   0.0381   1.0000
  11.000   0.9323   0.04080   0.03192   0.0329   0.0368   1.0000
  11.250   0.9431   0.04241   0.03367   0.0341   0.0357   1.0000
  11.500   0.9530   0.04404   0.03541   0.0352   0.0348   1.0000
  11.750   0.9629   0.04588   0.03733   0.0362   0.0341   1.0000
  12.000   0.9729   0.04811   0.03965   0.0371   0.0336   1.0000
  12.250   0.9729   0.05073   0.04258   0.0385   0.0332   1.0000
  12.500   0.9688   0.05366   0.04582   0.0398   0.0329   1.0000
  12.750   0.9614   0.05690   0.04936   0.0408   0.0327   1.0000
  13.000   0.9507   0.06050   0.05327   0.0414   0.0325   1.0000
  13.250   0.9367   0.06454   0.05758   0.0414   0.0324   1.0000
  13.500   0.9196   0.06911   0.06241   0.0408   0.0323   1.0000
  13.750   0.8995   0.07430   0.06785   0.0394   0.0323   1.0000
  14.000   0.8764   0.08028   0.07406   0.0370   0.0324   1.0000
  14.250   0.8501   0.08724   0.08122   0.0336   0.0325   1.0000
  14.500   0.8206   0.09555   0.08973   0.0289   0.0327   1.0000
  14.750   0.7872   0.10590   0.10025   0.0224   0.0330   1.0000
  15.000   0.7514   0.11884   0.11330   0.0143   0.0333   1.0000
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