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NACA 64(2)-415 (naca642415-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 64(2)-415 (naca642415-il)
Reynolds number: 100,000
Max Cl/Cd: 51.88 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca642415-il-100000.txt
Download as CSV file: xf-naca642415-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(2)-415                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4133   0.10081   0.09575  -0.0466   1.0000   0.1734
 -10.250  -0.3921   0.09851   0.09343  -0.0446   1.0000   0.1782
 -10.000  -0.4383   0.09364   0.08878  -0.0496   1.0000   0.1881
  -9.750  -0.3961   0.09221   0.08726  -0.0450   1.0000   0.1937
  -9.500  -0.5088   0.08698   0.08245  -0.0520   1.0000   0.2031
  -9.250  -0.4074   0.08617   0.08139  -0.0445   1.0000   0.2091
  -9.000  -0.4882   0.08345   0.07903  -0.0451   1.0000   0.2186
  -8.500  -0.7529   0.05756   0.05195  -0.0425   0.9994   0.0972
  -8.250  -0.7345   0.05047   0.04378  -0.0455   0.9919   0.0826
  -8.000  -0.7077   0.04522   0.03833  -0.0481   0.9861   0.0809
  -7.750  -0.6794   0.04152   0.03414  -0.0505   0.9796   0.0806
  -7.500  -0.6478   0.03875   0.03081  -0.0528   0.9726   0.0818
  -7.250  -0.6160   0.03635   0.02793  -0.0546   0.9660   0.0824
  -7.000  -0.5830   0.03354   0.02481  -0.0564   0.9598   0.0836
  -6.750  -0.5423   0.03144   0.02268  -0.0596   0.9555   0.0875
  -6.500  -0.5150   0.03022   0.02133  -0.0600   0.9470   0.0911
  -6.250  -0.4740   0.02883   0.01966  -0.0624   0.9419   0.0951
  -6.000  -0.4430   0.02737   0.01832  -0.0633   0.9353   0.1006
  -5.750  -0.4087   0.02644   0.01732  -0.0647   0.9284   0.1083
  -5.500  -0.3674   0.02512   0.01618  -0.0673   0.9245   0.1192
  -5.250  -0.3474   0.02434   0.01552  -0.0664   0.9150   0.1315
  -5.000  -0.3116   0.02305   0.01447  -0.0685   0.9098   0.1613
  -4.750  -0.2993   0.02035   0.01331  -0.0683   0.9012   0.3623
  -4.500  -0.2705   0.02097   0.01448  -0.0671   0.8945   0.5726
  -4.250  -0.2303   0.02196   0.01545  -0.0673   0.8908   0.6138
  -4.000  -0.2169   0.02270   0.01616  -0.0638   0.8800   0.6356
  -3.750  -0.1817   0.02357   0.01696  -0.0630   0.8757   0.6608
  -3.500  -0.1685   0.02439   0.01777  -0.0591   0.8662   0.6781
  -3.250  -0.1419   0.02530   0.01867  -0.0565   0.8609   0.6980
  -3.000  -0.1096   0.02618   0.01949  -0.0544   0.8576   0.7195
  -2.750  -0.1052   0.02680   0.02010  -0.0494   0.8467   0.7331
  -2.500  -0.0717   0.02692   0.02011  -0.0493   0.8427   0.7464
  -2.250  -0.0590   0.02701   0.02011  -0.0475   0.8335   0.7567
  -2.000  -0.0317   0.02697   0.01999  -0.0471   0.8282   0.7631
  -1.750   0.0048   0.02673   0.01964  -0.0487   0.8249   0.7705
  -1.500   0.0103   0.02695   0.01982  -0.0462   0.8150   0.7778
  -1.250   0.0410   0.02684   0.01964  -0.0466   0.8105   0.7840
  -1.000   0.0801   0.02648   0.01916  -0.0491   0.8076   0.7919
  -0.750   0.0790   0.02703   0.01973  -0.0450   0.7970   0.7978
  -0.500   0.1110   0.02690   0.01952  -0.0462   0.7933   0.8049
  -0.250   0.1473   0.02668   0.01924  -0.0478   0.7908   0.8107
   0.000   0.1428   0.02744   0.02002  -0.0439   0.7802   0.8181
   0.250   0.1772   0.02728   0.01981  -0.0455   0.7765   0.8253
   0.500   0.2117   0.02712   0.01962  -0.0463   0.7742   0.8305
   0.750   0.2036   0.02824   0.02076  -0.0431   0.7637   0.8404
   1.000   0.2318   0.02819   0.02072  -0.0428   0.7601   0.8468
   1.250   0.2693   0.02803   0.02053  -0.0444   0.7578   0.8546
   1.500   0.2501   0.02942   0.02198  -0.0391   0.7469   0.8645
   1.750   0.2846   0.02939   0.02194  -0.0404   0.7437   0.8732
   2.000   0.3193   0.02919   0.02176  -0.0409   0.7414   0.8813
   2.250   0.2930   0.03078   0.02340  -0.0348   0.7300   0.8960
   2.500   0.3278   0.03068   0.02333  -0.0358   0.7268   0.9064
   2.750   0.3705   0.03039   0.02307  -0.0377   0.7248   0.9163
   3.000   0.3450   0.03222   0.02497  -0.0324   0.7133   0.9370
   3.250   0.3885   0.03210   0.02489  -0.0348   0.7102   0.9498
   3.500   0.4372   0.03215   0.02502  -0.0385   0.7069   0.9619
   3.750   0.4629   0.03377   0.02675  -0.0420   0.6971   0.9808
   4.000   0.5269   0.03346   0.02654  -0.0478   0.6941   0.9897
   4.250   0.5960   0.03272   0.02589  -0.0538   0.6923   0.9962
   4.500   0.5553   0.03499   0.02812  -0.0478   0.6785   1.0000
   4.750   0.5927   0.03509   0.02828  -0.0498   0.6730   1.0000
   5.000   0.6119   0.03598   0.02922  -0.0503   0.6630   1.0000
   5.250   0.6771   0.03430   0.02766  -0.0536   0.6605   1.0000
   5.500   0.6834   0.03581   0.02922  -0.0528   0.6472   1.0000
   5.750   0.7559   0.03319   0.02676  -0.0559   0.6447   1.0000
   6.000   0.7796   0.03331   0.02696  -0.0556   0.6322   1.0000
   6.250   0.8788   0.02765   0.02143  -0.0593   0.6275   1.0000
   6.500   0.9185   0.02609   0.01997  -0.0594   0.6130   1.0000
   6.750   0.9685   0.02359   0.01748  -0.0599   0.5955   1.0000
   7.000   0.9999   0.02246   0.01642  -0.0592   0.5755   1.0000
   7.250   1.0262   0.02168   0.01572  -0.0581   0.5529   1.0000
   7.500   1.0512   0.02093   0.01501  -0.0566   0.5259   1.0000
   7.750   1.0667   0.02061   0.01475  -0.0541   0.4887   1.0000
   8.000   1.0723   0.02067   0.01472  -0.0502   0.4229   1.0000
   8.250   1.0576   0.02192   0.01508  -0.0437   0.3079   1.0000
   8.500   1.0349   0.02444   0.01689  -0.0379   0.2287   1.0000
   8.750   1.0172   0.02725   0.01916  -0.0337   0.1772   1.0000
   9.000   1.0092   0.02978   0.02132  -0.0307   0.1462   1.0000
   9.250   1.0105   0.03189   0.02321  -0.0285   0.1257   1.0000
   9.500   1.0186   0.03367   0.02484  -0.0269   0.1115   1.0000
   9.750   1.0333   0.03528   0.02627  -0.0257   0.1007   1.0000
  10.000   1.0515   0.03669   0.02762  -0.0248   0.0918   1.0000
  10.250   1.0793   0.03812   0.02905  -0.0244   0.0845   1.0000
  10.500   1.1191   0.03985   0.03051  -0.0253   0.0770   1.0000
  10.750   1.1416   0.04145   0.03238  -0.0247   0.0731   1.0000
  11.000   1.1741   0.04339   0.03442  -0.0252   0.0695   1.0000
  11.250   1.2218   0.04659   0.03759  -0.0277   0.0655   1.0000
  11.500   1.2300   0.04866   0.04001  -0.0259   0.0639   1.0000
  11.750   1.2412   0.05123   0.04292  -0.0246   0.0625   1.0000
  12.000   1.2499   0.05417   0.04618  -0.0233   0.0617   1.0000
  12.250   1.2529   0.05731   0.04966  -0.0217   0.0613   1.0000
  12.500   1.2505   0.06067   0.05334  -0.0199   0.0611   1.0000
  12.750   1.2429   0.06431   0.05731  -0.0182   0.0613   1.0000
  13.000   1.2301   0.06822   0.06153  -0.0167   0.0614   1.0000
  13.250   1.2135   0.07247   0.06608  -0.0155   0.0617   1.0000
  13.500   1.1933   0.07713   0.07102  -0.0150   0.0620   1.0000
  13.750   1.1707   0.08229   0.07645  -0.0151   0.0625   1.0000
  14.000   1.1459   0.08802   0.08243  -0.0160   0.0630   1.0000
  14.250   1.1204   0.09431   0.08894  -0.0178   0.0636   1.0000
  14.500   1.0944   0.10121   0.09603  -0.0203   0.0643   1.0000
  14.750   1.0708   0.10852   0.10349  -0.0234   0.0649   1.0000
  15.000   1.0537   0.11589   0.11096  -0.0266   0.0656   1.0000
  15.250   0.6934   0.17091   0.16688  -0.0553   0.1443   1.0000
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