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NACA 642-015A AIRFOIL (n64015a-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 642-015A AIRFOIL (n64015a-il)
Reynolds number: 50,000
Max Cl/Cd: 27.88 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n64015a-il-50000-n5.txt
Download as CSV file: xf-n64015a-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.7529   0.09641   0.08854  -0.0323   1.0000   0.0566
 -13.000  -0.7820   0.08859   0.08058  -0.0365   1.0000   0.0562
 -12.750  -0.8089   0.08199   0.07381  -0.0394   1.0000   0.0559
 -12.500  -0.8327   0.07641   0.06801  -0.0411   1.0000   0.0557
 -12.250  -0.8531   0.07163   0.06301  -0.0418   1.0000   0.0557
 -12.000  -0.8702   0.06745   0.05857  -0.0416   1.0000   0.0558
 -11.750  -0.8837   0.06374   0.05457  -0.0406   1.0000   0.0561
 -11.500  -0.8942   0.06043   0.05095  -0.0391   1.0000   0.0567
 -11.250  -0.9022   0.05744   0.04762  -0.0371   1.0000   0.0575
 -11.000  -0.9080   0.05475   0.04453  -0.0346   1.0000   0.0584
 -10.750  -0.8946   0.05235   0.04214  -0.0339   1.0000   0.0602
 -10.500  -0.8831   0.05022   0.03988  -0.0328   1.0000   0.0621
 -10.250  -0.8691   0.04798   0.03742  -0.0318   1.0000   0.0641
 -10.000  -0.8492   0.04568   0.03483  -0.0312   1.0000   0.0664
  -9.750  -0.8273   0.04363   0.03244  -0.0307   1.0000   0.0698
  -9.500  -0.8005   0.04194   0.03083  -0.0310   1.0000   0.0740
  -9.250  -0.7701   0.04038   0.02907  -0.0311   1.0000   0.0792
  -9.000  -0.7417   0.03901   0.02769  -0.0309   1.0000   0.0853
  -8.750  -0.7191   0.03781   0.02637  -0.0301   1.0000   0.0928
  -8.500  -0.7022   0.03652   0.02515  -0.0289   1.0000   0.1001
  -8.250  -0.6886   0.03526   0.02386  -0.0272   1.0000   0.1096
  -8.000  -0.6799   0.03394   0.02260  -0.0252   1.0000   0.1200
  -7.750  -0.6752   0.03259   0.02136  -0.0226   1.0000   0.1324
  -7.500  -0.6738   0.03126   0.02017  -0.0194   1.0000   0.1477
  -7.250  -0.6745   0.02987   0.01899  -0.0159   1.0000   0.1688
  -7.000  -0.6788   0.02844   0.01787  -0.0119   1.0000   0.1985
  -6.750  -0.6868   0.02700   0.01686  -0.0071   1.0000   0.2424
  -6.500  -0.6967   0.02566   0.01615  -0.0018   1.0000   0.3100
  -6.250  -0.6995   0.02510   0.01641   0.0038   1.0000   0.4143
  -6.000  -0.6972   0.02508   0.01655   0.0085   1.0000   0.4847
  -5.750  -0.6937   0.02515   0.01661   0.0130   1.0000   0.5279
  -5.500  -0.6873   0.02534   0.01675   0.0170   1.0000   0.5615
  -5.250  -0.6798   0.02557   0.01691   0.0208   1.0000   0.5901
  -5.000  -0.6627   0.02607   0.01732   0.0232   0.9969   0.6202
  -4.750  -0.6263   0.02720   0.01833   0.0233   0.9881   0.6530
  -4.500  -0.5870   0.02830   0.01929   0.0229   0.9803   0.6776
  -4.250  -0.5481   0.02876   0.01954   0.0215   0.9724   0.6950
  -4.000  -0.5107   0.02897   0.01955   0.0199   0.9635   0.7072
  -3.750  -0.4765   0.02886   0.01925   0.0183   0.9543   0.7187
  -3.500  -0.4376   0.02878   0.01897   0.0158   0.9465   0.7286
  -3.250  -0.4032   0.02867   0.01870   0.0142   0.9372   0.7366
  -3.000  -0.3644   0.02844   0.01830   0.0115   0.9301   0.7452
  -2.750  -0.3328   0.02827   0.01800   0.0102   0.9203   0.7523
  -2.500  -0.2934   0.02809   0.01769   0.0076   0.9135   0.7593
  -2.250  -0.2682   0.02782   0.01731   0.0073   0.9030   0.7672
  -2.000  -0.2276   0.02771   0.01711   0.0047   0.8968   0.7729
  -1.750  -0.2078   0.02741   0.01672   0.0053   0.8857   0.7819
  -1.500  -0.1663   0.02735   0.01658   0.0026   0.8800   0.7868
  -1.250  -0.1452   0.02720   0.01638   0.0032   0.8694   0.7951
  -1.000  -0.1098   0.02707   0.01619   0.0015   0.8632   0.8012
  -0.750  -0.0849   0.02705   0.01615   0.0015   0.8535   0.8083
  -0.500  -0.0538   0.02688   0.01593   0.0005   0.8473   0.8161
  -0.250  -0.0279   0.02696   0.01602   0.0004   0.8378   0.8227
   0.000   0.0000   0.02681   0.01584   0.0000   0.8314   0.8314
   0.250   0.0279   0.02696   0.01602  -0.0004   0.8227   0.8378
   0.500   0.0538   0.02688   0.01593  -0.0005   0.8161   0.8473
   0.750   0.0849   0.02705   0.01615  -0.0015   0.8083   0.8535
   1.000   0.1097   0.02707   0.01619  -0.0015   0.8012   0.8632
   1.250   0.1453   0.02720   0.01638  -0.0032   0.7951   0.8694
   1.500   0.1662   0.02735   0.01657  -0.0026   0.7868   0.8801
   1.750   0.2078   0.02741   0.01672  -0.0053   0.7819   0.8857
   2.000   0.2276   0.02771   0.01710  -0.0047   0.7730   0.8968
   2.250   0.2682   0.02782   0.01731  -0.0073   0.7672   0.9030
   2.500   0.2934   0.02809   0.01769  -0.0076   0.7593   0.9135
   2.750   0.3328   0.02827   0.01800  -0.0102   0.7523   0.9204
   3.000   0.3645   0.02844   0.01829  -0.0115   0.7453   0.9301
   3.250   0.4032   0.02866   0.01870  -0.0142   0.7366   0.9373
   3.500   0.4377   0.02878   0.01897  -0.0158   0.7286   0.9465
   3.750   0.4765   0.02885   0.01925  -0.0183   0.7188   0.9544
   4.000   0.5108   0.02896   0.01955  -0.0199   0.7072   0.9636
   4.250   0.5481   0.02876   0.01953  -0.0215   0.6951   0.9725
   4.500   0.5871   0.02829   0.01928  -0.0229   0.6776   0.9804
   4.750   0.6264   0.02719   0.01832  -0.0233   0.6530   0.9881
   5.000   0.6628   0.02606   0.01731  -0.0233   0.6202   0.9969
   5.250   0.6796   0.02557   0.01691  -0.0208   0.5902   1.0000
   5.500   0.6872   0.02533   0.01675  -0.0170   0.5616   1.0000
   5.750   0.6936   0.02514   0.01660  -0.0129   0.5280   1.0000
   6.000   0.6971   0.02508   0.01655  -0.0085   0.4849   1.0000
   6.250   0.6994   0.02509   0.01641  -0.0038   0.4146   1.0000
   6.500   0.6966   0.02565   0.01614   0.0018   0.3101   1.0000
   6.750   0.6868   0.02700   0.01685   0.0071   0.2424   1.0000
   7.000   0.6789   0.02844   0.01786   0.0119   0.1984   1.0000
   7.250   0.6746   0.02987   0.01899   0.0159   0.1688   1.0000
   7.500   0.6740   0.03126   0.02016   0.0194   0.1476   1.0000
   7.750   0.6755   0.03259   0.02135   0.0225   0.1323   1.0000
   8.000   0.6802   0.03394   0.02260   0.0251   0.1199   1.0000
   8.250   0.6890   0.03526   0.02386   0.0272   0.1096   1.0000
   8.500   0.7026   0.03652   0.02514   0.0288   0.1000   1.0000
   8.750   0.7196   0.03781   0.02637   0.0300   0.0927   1.0000
   9.000   0.7423   0.03901   0.02768   0.0308   0.0853   1.0000
   9.250   0.7707   0.04038   0.02907   0.0310   0.0792   1.0000
   9.500   0.8011   0.04195   0.03083   0.0309   0.0740   1.0000
   9.750   0.8280   0.04364   0.03244   0.0306   0.0697   1.0000
  10.000   0.8498   0.04569   0.03484   0.0311   0.0664   1.0000
  10.250   0.8696   0.04799   0.03743   0.0317   0.0641   1.0000
  10.500   0.8837   0.05023   0.03990   0.0327   0.0621   1.0000
  10.750   0.8952   0.05237   0.04216   0.0338   0.0602   1.0000
  11.000   0.9085   0.05477   0.04456   0.0345   0.0584   1.0000
  11.250   0.9027   0.05747   0.04765   0.0370   0.0575   1.0000
  11.500   0.8948   0.06046   0.05099   0.0390   0.0567   1.0000
  11.750   0.8843   0.06378   0.05461   0.0405   0.0561   1.0000
  12.000   0.8708   0.06749   0.05862   0.0414   0.0558   1.0000
  12.250   0.8538   0.07168   0.06307   0.0416   0.0557   1.0000
  12.500   0.8334   0.07648   0.06808   0.0409   0.0557   1.0000
  12.750   0.8096   0.08207   0.07389   0.0392   0.0559   1.0000
  13.000   0.7827   0.08869   0.08068   0.0363   0.0562   1.0000
  13.250   0.7536   0.09653   0.08867   0.0320   0.0566   1.0000
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