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NACA 63-015A AIRFOIL (n63015a-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 63-015A AIRFOIL (n63015a-il)
Reynolds number: 50,000
Max Cl/Cd: 28.88 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n63015a-il-50000.txt
Download as CSV file: xf-n63015a-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.7044   0.10730   0.09997  -0.0218   1.0000   0.1414
 -12.000  -0.7059   0.10116   0.09384  -0.0235   1.0000   0.1402
 -11.750  -0.8157   0.08347   0.07602  -0.0358   1.0000   0.1263
 -11.500  -0.8340   0.07797   0.07044  -0.0366   1.0000   0.1251
 -11.250  -0.8578   0.07302   0.06536  -0.0365   1.0000   0.1240
 -11.000  -0.8821   0.06877   0.06094  -0.0348   1.0000   0.1230
 -10.750  -0.9025   0.06487   0.05680  -0.0325   1.0000   0.1224
 -10.500  -0.9162   0.06108   0.05272  -0.0301   1.0000   0.1224
 -10.250  -0.9251   0.05754   0.04883  -0.0276   1.0000   0.1231
 -10.000  -0.9302   0.05422   0.04510  -0.0249   1.0000   0.1245
  -9.750  -0.9322   0.05116   0.04155  -0.0221   1.0000   0.1262
  -9.500  -0.9200   0.04775   0.03795  -0.0207   1.0000   0.1292
  -9.250  -0.9007   0.04497   0.03507  -0.0198   1.0000   0.1340
  -9.000  -0.8902   0.04255   0.03223  -0.0177   1.0000   0.1398
  -8.750  -0.8675   0.03992   0.02961  -0.0171   1.0000   0.1482
  -8.500  -0.8471   0.03756   0.02709  -0.0160   1.0000   0.1589
  -8.250  -0.8225   0.03536   0.02492  -0.0153   1.0000   0.1743
  -8.000  -0.7991   0.03332   0.02306  -0.0144   1.0000   0.1959
  -7.750  -0.7792   0.03128   0.02131  -0.0130   1.0000   0.2261
  -7.500  -0.7678   0.02930   0.01979  -0.0103   1.0000   0.2677
  -7.250  -0.7669   0.02752   0.01870  -0.0059   1.0000   0.3262
  -7.000  -0.7706   0.02669   0.01878   0.0003   1.0000   0.4104
  -6.750  -0.7673   0.02760   0.02014   0.0071   1.0000   0.4945
  -6.500  -0.7414   0.03037   0.02298   0.0124   1.0000   0.5533
  -6.250  -0.7183   0.03245   0.02495   0.0171   1.0000   0.5931
  -6.000  -0.6787   0.03527   0.02757   0.0205   1.0000   0.6259
  -5.750  -0.6060   0.03936   0.03131   0.0211   1.0000   0.6567
  -5.500  -0.5144   0.04279   0.03425   0.0184   1.0000   0.6865
  -5.250  -0.4703   0.04318   0.03438   0.0178   1.0000   0.7106
  -5.000  -0.4181   0.04330   0.03425   0.0155   1.0000   0.7327
  -4.750  -0.3931   0.04274   0.03356   0.0160   1.0000   0.7517
  -4.500  -0.3711   0.04209   0.03282   0.0165   1.0000   0.7689
  -4.250  -0.3498   0.04142   0.03208   0.0170   1.0000   0.7848
  -4.000  -0.3320   0.04074   0.03135   0.0178   1.0000   0.7995
  -3.750  -0.3239   0.04010   0.03066   0.0199   1.0000   0.8131
  -3.500  -0.3313   0.03951   0.03008   0.0241   1.0000   0.8261
  -3.250  -0.3325   0.03898   0.02952   0.0273   1.0000   0.8392
  -3.000  -0.3050   0.03846   0.02892   0.0260   1.0000   0.8513
  -2.750  -0.2961   0.03792   0.02835   0.0274   1.0000   0.8631
  -2.500  -0.2987   0.03740   0.02780   0.0304   1.0000   0.8755
  -2.250  -0.2801   0.03696   0.02730   0.0300   1.0000   0.8872
  -2.000  -0.2569   0.03654   0.02683   0.0287   1.0000   0.8985
  -1.750  -0.2450   0.03614   0.02638   0.0292   1.0000   0.9104
  -1.500  -0.2324   0.03580   0.02600   0.0294   1.0000   0.9229
  -1.250  -0.1959   0.03555   0.02570   0.0254   1.0000   0.9337
  -1.000  -0.1690   0.03533   0.02545   0.0229   1.0000   0.9454
  -0.750  -0.1418   0.03518   0.02526   0.0201   1.0000   0.9577
  -0.500  -0.1101   0.03511   0.02516   0.0165   1.0000   0.9701
  -0.250  -0.0699   0.03509   0.02512   0.0110   1.0000   0.9821
   0.000   0.0000   0.03510   0.02513   0.0000   0.9919   0.9919
   0.250   0.0699   0.03509   0.02512  -0.0110   0.9821   1.0000
   0.500   0.1100   0.03510   0.02516  -0.0164   0.9701   1.0000
   0.750   0.1417   0.03517   0.02525  -0.0201   0.9577   1.0000
   1.000   0.1690   0.03532   0.02544  -0.0229   0.9454   1.0000
   1.250   0.1959   0.03554   0.02569  -0.0254   0.9337   1.0000
   1.500   0.2324   0.03579   0.02599  -0.0294   0.9230   1.0000
   1.750   0.2449   0.03612   0.02637  -0.0291   0.9104   1.0000
   2.000   0.2569   0.03653   0.02681  -0.0287   0.8985   1.0000
   2.250   0.2802   0.03695   0.02728  -0.0301   0.8873   1.0000
   2.500   0.2985   0.03739   0.02778  -0.0304   0.8755   1.0000
   2.750   0.2960   0.03791   0.02833  -0.0274   0.8632   1.0000
   3.000   0.3050   0.03844   0.02890  -0.0260   0.8513   1.0000
   3.250   0.3327   0.03896   0.02951  -0.0274   0.8392   1.0000
   3.500   0.3311   0.03950   0.03006  -0.0241   0.8262   1.0000
   3.750   0.3238   0.04008   0.03064  -0.0198   0.8131   1.0000
   4.000   0.3321   0.04073   0.03133  -0.0178   0.7995   1.0000
   4.250   0.3499   0.04140   0.03206  -0.0170   0.7848   1.0000
   4.500   0.3713   0.04207   0.03281  -0.0165   0.7690   1.0000
   4.750   0.3934   0.04272   0.03354  -0.0160   0.7517   1.0000
   5.000   0.4184   0.04328   0.03423  -0.0156   0.7327   1.0000
   5.250   0.4707   0.04316   0.03436  -0.0178   0.7106   1.0000
   5.500   0.5148   0.04277   0.03423  -0.0184   0.6865   1.0000
   5.750   0.6062   0.03934   0.03129  -0.0212   0.6567   1.0000
   6.000   0.6779   0.03531   0.02761  -0.0205   0.6260   1.0000
   6.250   0.7183   0.03244   0.02494  -0.0171   0.5931   1.0000
   6.500   0.7413   0.03037   0.02298  -0.0124   0.5533   1.0000
   6.750   0.7672   0.02760   0.02013  -0.0071   0.4946   1.0000
   7.000   0.7706   0.02668   0.01877  -0.0003   0.4105   1.0000
   7.250   0.7669   0.02752   0.01870   0.0059   0.3263   1.0000
   7.500   0.7678   0.02930   0.01978   0.0103   0.2677   1.0000
   7.750   0.7792   0.03128   0.02131   0.0130   0.2260   1.0000
   8.000   0.7991   0.03332   0.02306   0.0144   0.1959   1.0000
   8.250   0.8226   0.03536   0.02492   0.0153   0.1742   1.0000
   8.500   0.8472   0.03756   0.02709   0.0159   0.1589   1.0000
   8.750   0.8676   0.03992   0.02961   0.0171   0.1482   1.0000
   9.000   0.8902   0.04255   0.03223   0.0177   0.1398   1.0000
   9.250   0.9008   0.04498   0.03507   0.0198   0.1340   1.0000
   9.500   0.9202   0.04776   0.03795   0.0207   0.1292   1.0000
   9.750   0.9323   0.05116   0.04155   0.0221   0.1261   1.0000
  10.000   0.9303   0.05423   0.04511   0.0249   0.1245   1.0000
  10.250   0.9252   0.05755   0.04884   0.0276   0.1231   1.0000
  10.500   0.9164   0.06109   0.05273   0.0301   0.1224   1.0000
  10.750   0.9028   0.06489   0.05682   0.0324   0.1224   1.0000
  11.000   0.8824   0.06881   0.06097   0.0347   0.1230   1.0000
  11.250   0.8581   0.07307   0.06541   0.0364   0.1240   1.0000
  11.500   0.8344   0.07803   0.07049   0.0365   0.1251   1.0000
  11.750   0.8163   0.08354   0.07609   0.0357   0.1263   1.0000
  12.000   0.7066   0.10127   0.09395   0.0233   0.1402   1.0000
  12.250   0.7052   0.10740   0.10008   0.0216   0.1414   1.0000
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