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NACA 63-015A AIRFOIL (n63015a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 63-015A AIRFOIL (n63015a-il)
Reynolds number: 1,000,000
Max Cl/Cd: 72.82 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n63015a-il-1000000.txt
Download as CSV file: xf-n63015a-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -18.250  -1.1799   0.08928   0.08583  -0.0163   1.0000   0.0119
 -18.000  -1.1959   0.08331   0.07972  -0.0187   1.0000   0.0120
 -17.750  -1.2099   0.07787   0.07414  -0.0207   1.0000   0.0121
 -17.500  -1.2207   0.07302   0.06918  -0.0223   1.0000   0.0121
 -17.250  -1.2290   0.06860   0.06464  -0.0237   1.0000   0.0122
 -17.000  -1.2354   0.06453   0.06048  -0.0249   1.0000   0.0123
 -16.750  -1.2400   0.06080   0.05666  -0.0259   1.0000   0.0124
 -16.500  -1.2430   0.05734   0.05311  -0.0268   1.0000   0.0125
 -16.250  -1.2442   0.05416   0.04986  -0.0275   1.0000   0.0126
 -16.000  -1.2442   0.05123   0.04686  -0.0280   1.0000   0.0127
 -15.750  -1.2432   0.04850   0.04405  -0.0285   1.0000   0.0129
 -15.500  -1.2408   0.04598   0.04145  -0.0287   1.0000   0.0130
 -15.250  -1.2380   0.04358   0.03898  -0.0289   1.0000   0.0132
 -15.000  -1.2345   0.04131   0.03663  -0.0289   1.0000   0.0133
 -14.750  -1.2303   0.03913   0.03437  -0.0287   1.0000   0.0134
 -14.500  -1.2254   0.03707   0.03223  -0.0285   1.0000   0.0136
 -14.250  -1.2197   0.03514   0.03022  -0.0282   1.0000   0.0137
 -14.000  -1.2130   0.03331   0.02832  -0.0278   1.0000   0.0139
 -13.750  -1.2055   0.03162   0.02654  -0.0273   1.0000   0.0141
 -13.500  -1.1969   0.03004   0.02489  -0.0267   1.0000   0.0142
 -13.250  -1.1876   0.02857   0.02334  -0.0261   1.0000   0.0144
 -13.000  -1.1771   0.02723   0.02193  -0.0254   1.0000   0.0145
 -12.750  -1.1655   0.02602   0.02066  -0.0247   1.0000   0.0147
 -12.500  -1.1528   0.02493   0.01950  -0.0239   1.0000   0.0148
 -12.250  -1.1509   0.02308   0.01756  -0.0222   1.0000   0.0151
 -12.000  -1.1435   0.02174   0.01617  -0.0207   1.0000   0.0154
 -11.750  -1.1325   0.02072   0.01510  -0.0192   1.0000   0.0157
 -11.500  -1.1194   0.01989   0.01422  -0.0179   1.0000   0.0160
 -11.250  -1.1051   0.01917   0.01347  -0.0165   1.0000   0.0163
 -11.000  -1.0901   0.01854   0.01281  -0.0150   1.0000   0.0167
 -10.750  -1.0751   0.01796   0.01219  -0.0134   1.0000   0.0171
 -10.500  -1.0603   0.01742   0.01161  -0.0116   1.0000   0.0175
 -10.250  -1.0443   0.01692   0.01107  -0.0100   1.0000   0.0178
 -10.000  -1.0264   0.01647   0.01058  -0.0086   1.0000   0.0181
  -9.750  -1.0147   0.01570   0.00977  -0.0062   1.0000   0.0188
  -9.500  -1.0000   0.01521   0.00926  -0.0041   1.0000   0.0195
  -9.250  -0.9854   0.01483   0.00886  -0.0019   1.0000   0.0202
  -9.000  -0.9656   0.01444   0.00846  -0.0008   0.9991   0.0210
  -8.750  -0.9313   0.01402   0.00801  -0.0026   0.9955   0.0219
  -8.500  -0.8996   0.01337   0.00736  -0.0041   0.9905   0.0241
  -8.250  -0.8662   0.01295   0.00693  -0.0058   0.9842   0.0261
  -8.000  -0.8359   0.01244   0.00644  -0.0068   0.9742   0.0296
  -7.750  -0.8065   0.01202   0.00602  -0.0075   0.9613   0.0338
  -7.500  -0.7805   0.01166   0.00564  -0.0074   0.9440   0.0387
  -7.250  -0.7574   0.01132   0.00530  -0.0066   0.9242   0.0455
  -7.000  -0.7349   0.01099   0.00496  -0.0057   0.9046   0.0552
  -6.750  -0.7119   0.01066   0.00464  -0.0049   0.8861   0.0676
  -6.500  -0.6884   0.01034   0.00434  -0.0043   0.8692   0.0819
  -6.250  -0.6645   0.01005   0.00406  -0.0037   0.8541   0.0986
  -6.000  -0.6411   0.00968   0.00376  -0.0031   0.8401   0.1233
  -5.750  -0.6175   0.00928   0.00346  -0.0025   0.8273   0.1555
  -5.500  -0.5944   0.00882   0.00316  -0.0019   0.8159   0.1965
  -5.250  -0.5717   0.00834   0.00285  -0.0013   0.8053   0.2468
  -5.000  -0.5499   0.00774   0.00253  -0.0005   0.7950   0.3148
  -4.750  -0.5272   0.00724   0.00229   0.0002   0.7858   0.3821
  -4.500  -0.5019   0.00698   0.00213   0.0006   0.7769   0.4216
  -4.250  -0.4753   0.00682   0.00202   0.0007   0.7686   0.4467
  -4.000  -0.4483   0.00671   0.00193   0.0008   0.7602   0.4674
  -3.750  -0.4214   0.00658   0.00184   0.0010   0.7526   0.4890
  -3.500  -0.3939   0.00650   0.00177   0.0010   0.7446   0.5059
  -3.250  -0.3662   0.00644   0.00170   0.0010   0.7373   0.5184
  -2.750  -0.3103   0.00635   0.00158   0.0009   0.7224   0.5406
  -2.500  -0.2824   0.00628   0.00154   0.0009   0.7148   0.5533
  -2.000  -0.2261   0.00622   0.00146   0.0007   0.7004   0.5764
  -1.750  -0.1984   0.00619   0.00143   0.0007   0.6930   0.5865
  -1.500  -0.1700   0.00617   0.00140   0.0006   0.6859   0.5962
  -1.250  -0.1419   0.00614   0.00138   0.0006   0.6785   0.6057
  -1.000  -0.1136   0.00613   0.00136   0.0005   0.6715   0.6136
  -0.750  -0.0852   0.00611   0.00134   0.0004   0.6641   0.6213
  -0.500  -0.0568   0.00612   0.00133   0.0002   0.6571   0.6282
  -0.250  -0.0284   0.00610   0.00133   0.0001   0.6498   0.6356
   0.000   0.0000   0.00613   0.00132   0.0000   0.6427   0.6427
   0.250   0.0284   0.00610   0.00133  -0.0001   0.6356   0.6498
   0.500   0.0568   0.00612   0.00133  -0.0002   0.6282   0.6571
   0.750   0.0851   0.00611   0.00134  -0.0004   0.6213   0.6641
   1.000   0.1135   0.00613   0.00136  -0.0005   0.6136   0.6715
   1.250   0.1418   0.00614   0.00138  -0.0006   0.6057   0.6785
   1.500   0.1699   0.00617   0.00140  -0.0006   0.5962   0.6859
   1.750   0.1984   0.00619   0.00143  -0.0007   0.5866   0.6929
   2.000   0.2261   0.00622   0.00146  -0.0007   0.5764   0.7004
   2.500   0.2824   0.00628   0.00154  -0.0009   0.5533   0.7148
   2.750   0.3103   0.00635   0.00158  -0.0009   0.5407   0.7224
   3.250   0.3662   0.00644   0.00170  -0.0010   0.5184   0.7372
   3.500   0.3940   0.00650   0.00177  -0.0010   0.5060   0.7446
   3.750   0.4213   0.00658   0.00184  -0.0010   0.4889   0.7526
   4.000   0.4483   0.00671   0.00193  -0.0008   0.4673   0.7602
   4.250   0.4753   0.00682   0.00202  -0.0007   0.4466   0.7686
   4.500   0.5020   0.00698   0.00213  -0.0006   0.4216   0.7769
   4.750   0.5272   0.00724   0.00229  -0.0002   0.3820   0.7858
   5.000   0.5499   0.00774   0.00253   0.0005   0.3148   0.7950
   5.250   0.5717   0.00834   0.00286   0.0013   0.2465   0.8053
   5.500   0.5944   0.00882   0.00316   0.0019   0.1963   0.8159
   5.750   0.6176   0.00928   0.00346   0.0025   0.1554   0.8273
   6.000   0.6411   0.00968   0.00376   0.0031   0.1232   0.8401
   6.250   0.6646   0.01005   0.00406   0.0037   0.0988   0.8541
   6.500   0.6885   0.01034   0.00434   0.0042   0.0818   0.8693
   6.750   0.7120   0.01066   0.00464   0.0049   0.0675   0.8862
   7.000   0.7349   0.01099   0.00496   0.0057   0.0552   0.9047
   7.250   0.7575   0.01132   0.00530   0.0066   0.0455   0.9242
   7.500   0.7806   0.01166   0.00565   0.0074   0.0387   0.9439
   7.750   0.8066   0.01202   0.00602   0.0075   0.0337   0.9612
   8.000   0.8361   0.01244   0.00644   0.0068   0.0296   0.9742
   8.250   0.8665   0.01295   0.00693   0.0057   0.0261   0.9842
   8.500   0.8998   0.01337   0.00736   0.0041   0.0241   0.9906
   8.750   0.9315   0.01402   0.00801   0.0026   0.0219   0.9956
   9.000   0.9657   0.01444   0.00846   0.0007   0.0210   0.9991
   9.250   0.9853   0.01482   0.00886   0.0019   0.0202   1.0000
   9.500   1.0001   0.01521   0.00926   0.0041   0.0195   1.0000
   9.750   1.0148   0.01570   0.00977   0.0062   0.0188   1.0000
  10.000   1.0265   0.01647   0.01058   0.0086   0.0181   1.0000
  10.250   1.0445   0.01692   0.01106   0.0099   0.0178   1.0000
  10.500   1.0606   0.01742   0.01161   0.0116   0.0175   1.0000
  10.750   1.0755   0.01796   0.01219   0.0133   0.0171   1.0000
  11.000   1.0907   0.01853   0.01280   0.0149   0.0167   1.0000
  11.250   1.1057   0.01917   0.01347   0.0164   0.0163   1.0000
  11.500   1.1201   0.01988   0.01422   0.0177   0.0160   1.0000
  11.750   1.1333   0.02072   0.01510   0.0191   0.0157   1.0000
  12.000   1.1443   0.02175   0.01617   0.0205   0.0154   1.0000
  12.250   1.1519   0.02308   0.01756   0.0220   0.0151   1.0000
  12.500   1.1539   0.02493   0.01951   0.0237   0.0148   1.0000
  12.750   1.1667   0.02601   0.02065   0.0245   0.0146   1.0000
  13.000   1.1784   0.02722   0.02193   0.0252   0.0145   1.0000
  13.250   1.1889   0.02856   0.02333   0.0259   0.0144   1.0000
  13.500   1.1985   0.03002   0.02486   0.0265   0.0142   1.0000
  13.750   1.2070   0.03160   0.02652   0.0270   0.0140   1.0000
  14.000   1.2146   0.03329   0.02830   0.0275   0.0139   1.0000
  14.250   1.2214   0.03511   0.03019   0.0279   0.0137   1.0000
  14.500   1.2273   0.03704   0.03220   0.0282   0.0136   1.0000
  14.750   1.2322   0.03909   0.03433   0.0285   0.0134   1.0000
  15.000   1.2364   0.04128   0.03660   0.0286   0.0133   1.0000
  15.250   1.2401   0.04354   0.03893   0.0286   0.0132   1.0000
  15.500   1.2430   0.04593   0.04140   0.0284   0.0130   1.0000
  15.750   1.2452   0.04847   0.04402   0.0282   0.0129   1.0000
  16.000   1.2465   0.05117   0.04680   0.0277   0.0127   1.0000
  16.250   1.2465   0.05410   0.04980   0.0272   0.0126   1.0000
  16.500   1.2453   0.05728   0.05305   0.0264   0.0125   1.0000
  16.750   1.2424   0.06074   0.05660   0.0256   0.0124   1.0000
  17.000   1.2376   0.06449   0.06044   0.0246   0.0123   1.0000
  17.250   1.2315   0.06853   0.06458   0.0234   0.0122   1.0000
  17.500   1.2227   0.07302   0.06918   0.0219   0.0121   1.0000
  17.750   1.2114   0.07794   0.07422   0.0203   0.0120   1.0000
  18.000   1.1976   0.08338   0.07979   0.0183   0.0120   1.0000
  18.250   1.1806   0.08948   0.08605   0.0159   0.0119   1.0000
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