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NACA 63-015A AIRFOIL (n63015a-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 63-015A AIRFOIL (n63015a-il)
Reynolds number: 100,000
Max Cl/Cd: 44.44 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n63015a-il-100000.txt
Download as CSV file: xf-n63015a-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-015A 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
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.7813   0.10155   0.09618  -0.0287   1.0000   0.0742
 -13.250  -0.7859   0.09557   0.09019  -0.0302   1.0000   0.0733
 -13.000  -0.8050   0.08853   0.08310  -0.0333   1.0000   0.0722
 -12.750  -0.8349   0.08114   0.07558  -0.0367   1.0000   0.0708
 -12.500  -0.8679   0.07446   0.06872  -0.0392   1.0000   0.0695
 -12.250  -0.9015   0.06864   0.06265  -0.0401   1.0000   0.0682
 -12.000  -0.9356   0.06360   0.05730  -0.0392   1.0000   0.0669
 -11.750  -0.9741   0.05937   0.05263  -0.0358   1.0000   0.0655
 -11.500  -0.9942   0.05616   0.04905  -0.0321   1.0000   0.0651
 -11.250  -0.9958   0.05307   0.04571  -0.0300   1.0000   0.0654
 -11.000  -0.9952   0.05002   0.04236  -0.0278   1.0000   0.0657
 -10.750  -0.9909   0.04704   0.03907  -0.0257   1.0000   0.0659
 -10.500  -0.9808   0.04430   0.03608  -0.0241   1.0000   0.0665
 -10.250  -0.9675   0.04182   0.03334  -0.0226   1.0000   0.0675
 -10.000  -0.9521   0.03956   0.03085  -0.0213   1.0000   0.0690
  -9.750  -0.9369   0.03763   0.02866  -0.0198   1.0000   0.0715
  -9.500  -0.9224   0.03600   0.02667  -0.0179   1.0000   0.0740
  -9.250  -0.8944   0.03338   0.02412  -0.0184   1.0000   0.0775
  -9.000  -0.8710   0.03172   0.02240  -0.0178   1.0000   0.0815
  -8.500  -0.8271   0.02862   0.01931  -0.0163   1.0000   0.0941
  -8.250  -0.8069   0.02713   0.01784  -0.0152   1.0000   0.1025
  -8.000  -0.7916   0.02596   0.01669  -0.0133   1.0000   0.1136
  -7.750  -0.7800   0.02470   0.01559  -0.0110   1.0000   0.1275
  -7.500  -0.7740   0.02342   0.01456  -0.0077   1.0000   0.1446
  -7.250  -0.7715   0.02222   0.01359  -0.0039   1.0000   0.1687
  -7.000  -0.7740   0.02090   0.01265   0.0007   1.0000   0.2031
  -6.750  -0.7815   0.01946   0.01175   0.0060   1.0000   0.2593
  -6.500  -0.7896   0.01817   0.01119   0.0115   1.0000   0.3563
  -6.250  -0.7877   0.01772   0.01118   0.0158   1.0000   0.4439
  -6.000  -0.7786   0.01773   0.01126   0.0191   1.0000   0.4960
  -5.750  -0.7660   0.01792   0.01148   0.0219   1.0000   0.5326
  -5.500  -0.7518   0.01819   0.01171   0.0243   1.0000   0.5625
  -5.250  -0.7351   0.01859   0.01212   0.0265   1.0000   0.5867
  -5.000  -0.7192   0.01888   0.01234   0.0285   1.0000   0.6094
  -4.750  -0.6984   0.01930   0.01275   0.0300   0.9992   0.6281
  -4.500  -0.6556   0.01997   0.01337   0.0275   0.9913   0.6483
  -4.250  -0.6125   0.02058   0.01392   0.0249   0.9835   0.6674
  -4.000  -0.5742   0.02111   0.01439   0.0234   0.9745   0.6852
  -3.750  -0.5337   0.02165   0.01488   0.0215   0.9668   0.7020
  -3.500  -0.4940   0.02205   0.01522   0.0197   0.9585   0.7159
  -3.250  -0.4567   0.02224   0.01532   0.0180   0.9502   0.7287
  -3.000  -0.4169   0.02227   0.01525   0.0155   0.9423   0.7416
  -2.750  -0.3783   0.02250   0.01544   0.0138   0.9344   0.7503
  -2.500  -0.3378   0.02243   0.01528   0.0112   0.9268   0.7604
  -2.250  -0.2979   0.02246   0.01526   0.0088   0.9196   0.7694
  -2.000  -0.2610   0.02238   0.01512   0.0070   0.9113   0.7780
  -1.750  -0.2224   0.02232   0.01501   0.0049   0.9043   0.7869
  -1.500  -0.1900   0.02227   0.01492   0.0040   0.8951   0.7949
  -1.250  -0.1528   0.02219   0.01479   0.0022   0.8882   0.8036
  -1.000  -0.1237   0.02216   0.01475   0.0020   0.8786   0.8116
  -0.750  -0.0893   0.02208   0.01465   0.0009   0.8714   0.8204
  -0.500  -0.0609   0.02208   0.01464   0.0008   0.8618   0.8283
  -0.250  -0.0294   0.02203   0.01457   0.0002   0.8543   0.8373
   0.000   0.0000   0.02205   0.01459   0.0000   0.8450   0.8450
   0.250   0.0294   0.02203   0.01457  -0.0002   0.8373   0.8543
   0.500   0.0609   0.02208   0.01464  -0.0008   0.8283   0.8619
   0.750   0.0893   0.02208   0.01464  -0.0009   0.8203   0.8714
   1.000   0.1237   0.02216   0.01475  -0.0020   0.8116   0.8786
   1.250   0.1527   0.02219   0.01479  -0.0022   0.8036   0.8883
   1.500   0.1900   0.02227   0.01492  -0.0040   0.7949   0.8951
   1.750   0.2223   0.02232   0.01501  -0.0049   0.7868   0.9043
   2.000   0.2610   0.02238   0.01512  -0.0070   0.7780   0.9113
   2.250   0.2979   0.02246   0.01526  -0.0088   0.7694   0.9196
   2.500   0.3378   0.02242   0.01528  -0.0112   0.7604   0.9269
   2.750   0.3783   0.02250   0.01544  -0.0138   0.7503   0.9344
   3.000   0.4169   0.02226   0.01525  -0.0155   0.7416   0.9424
   3.250   0.4566   0.02224   0.01532  -0.0180   0.7287   0.9503
   3.500   0.4940   0.02204   0.01521  -0.0197   0.7160   0.9586
   3.750   0.5336   0.02165   0.01488  -0.0215   0.7020   0.9669
   4.000   0.5742   0.02111   0.01439  -0.0234   0.6853   0.9746
   4.250   0.6125   0.02057   0.01391  -0.0249   0.6674   0.9835
   4.500   0.6556   0.01996   0.01337  -0.0275   0.6483   0.9914
   4.750   0.6984   0.01930   0.01275  -0.0300   0.6281   0.9992
   5.000   0.7190   0.01888   0.01233  -0.0285   0.6095   1.0000
   5.250   0.7349   0.01859   0.01212  -0.0265   0.5867   1.0000
   5.500   0.7516   0.01818   0.01171  -0.0243   0.5625   1.0000
   5.750   0.7658   0.01792   0.01148  -0.0218   0.5327   1.0000
   6.000   0.7785   0.01773   0.01126  -0.0191   0.4962   1.0000
   6.250   0.7875   0.01772   0.01118  -0.0158   0.4441   1.0000
   6.500   0.7895   0.01816   0.01119  -0.0115   0.3566   1.0000
   6.750   0.7814   0.01945   0.01174  -0.0060   0.2596   1.0000
   7.000   0.7740   0.02090   0.01264  -0.0007   0.2031   1.0000
   7.250   0.7715   0.02222   0.01359   0.0039   0.1688   1.0000
   7.500   0.7740   0.02341   0.01456   0.0077   0.1446   1.0000
   7.750   0.7800   0.02470   0.01559   0.0110   0.1275   1.0000
   8.000   0.7917   0.02596   0.01669   0.0133   0.1136   1.0000
   8.250   0.8070   0.02713   0.01784   0.0152   0.1025   1.0000
   8.500   0.8272   0.02862   0.01931   0.0163   0.0941   1.0000
   8.750   0.8521   0.03047   0.02090   0.0164   0.0864   1.0000
   9.000   0.8712   0.03172   0.02240   0.0178   0.0815   1.0000
   9.250   0.8946   0.03338   0.02412   0.0184   0.0775   1.0000
   9.500   0.9226   0.03600   0.02667   0.0179   0.0740   1.0000
   9.750   0.9370   0.03763   0.02867   0.0198   0.0715   1.0000
  10.000   0.9523   0.03956   0.03086   0.0213   0.0690   1.0000
  10.250   0.9677   0.04183   0.03335   0.0226   0.0675   1.0000
  10.500   0.9810   0.04431   0.03609   0.0240   0.0665   1.0000
  10.750   0.9911   0.04705   0.03908   0.0257   0.0659   1.0000
  11.000   0.9955   0.05003   0.04238   0.0277   0.0657   1.0000
  11.250   0.9958   0.05309   0.04574   0.0300   0.0654   1.0000
  11.500   0.9930   0.05620   0.04911   0.0322   0.0652   1.0000
  11.750   0.9734   0.05942   0.05270   0.0358   0.0656   1.0000
  12.000   0.9359   0.06365   0.05736   0.0391   0.0669   1.0000
  12.250   0.9017   0.06872   0.06274   0.0399   0.0682   1.0000
  12.500   0.8683   0.07455   0.06881   0.0390   0.0695   1.0000
  12.750   0.8354   0.08126   0.07571   0.0365   0.0708   1.0000
  13.000   0.8059   0.08862   0.08319   0.0331   0.0722   1.0000
  13.250   0.7870   0.09566   0.09028   0.0300   0.0733   1.0000
  13.500   0.7829   0.10160   0.09624   0.0286   0.0742   1.0000
  13.750   0.6421   0.15038   0.14509  -0.0033   0.1424   1.0000
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