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NASA/LANGLEY 64-012 AIRFOIL (n64012-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NASA/LANGLEY 64-012 AIRFOIL (n64012-il)
Reynolds number: 1,000,000
Max Cl/Cd: 60.93 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n64012-il-1000000.txt
Download as CSV file: xf-n64012-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY 64-012 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
  ------ -------- --------- --------- -------- -------- --------
 -15.750  -1.0425   0.08111   0.07882  -0.0110   1.0000   0.0098
 -15.500  -1.0658   0.07277   0.07031  -0.0163   1.0000   0.0098
 -15.250  -1.0851   0.06597   0.06335  -0.0201   1.0000   0.0098
 -15.000  -1.1082   0.05916   0.05633  -0.0234   1.0000   0.0098
 -14.750  -1.1188   0.05469   0.05175  -0.0253   1.0000   0.0098
 -14.500  -1.1331   0.04996   0.04684  -0.0268   1.0000   0.0099
 -14.250  -1.1395   0.04653   0.04329  -0.0276   1.0000   0.0100
 -14.000  -1.1410   0.04387   0.04056  -0.0279   1.0000   0.0101
 -13.750  -1.1500   0.04040   0.03690  -0.0279   1.0000   0.0101
 -13.500  -1.1458   0.03868   0.03513  -0.0276   1.0000   0.0103
 -13.250  -1.1423   0.03697   0.03335  -0.0271   1.0000   0.0104
 -13.000  -1.1414   0.03499   0.03124  -0.0262   1.0000   0.0106
 -12.750  -1.1408   0.03301   0.02912  -0.0250   1.0000   0.0106
 -12.500  -1.1372   0.03144   0.02744  -0.0236   1.0000   0.0108
 -12.250  -1.1318   0.03014   0.02603  -0.0220   1.0000   0.0110
 -12.000  -1.1277   0.02858   0.02434  -0.0201   1.0000   0.0111
 -11.750  -1.1210   0.02741   0.02306  -0.0181   1.0000   0.0114
 -11.500  -1.1130   0.02633   0.02187  -0.0159   1.0000   0.0116
 -11.250  -1.1020   0.02525   0.02068  -0.0141   1.0000   0.0118
 -11.000  -1.0858   0.02454   0.01988  -0.0129   1.0000   0.0121
 -10.750  -1.0688   0.02372   0.01895  -0.0118   1.0000   0.0123
 -10.500  -1.0499   0.02316   0.01830  -0.0109   1.0000   0.0124
 -10.250  -1.0399   0.02051   0.01544  -0.0092   1.0000   0.0128
 -10.000  -1.0226   0.01939   0.01425  -0.0081   1.0000   0.0132
  -9.750  -1.0029   0.01860   0.01342  -0.0073   1.0000   0.0135
  -9.500  -0.9815   0.01798   0.01277  -0.0067   1.0000   0.0139
  -9.250  -0.9598   0.01736   0.01210  -0.0061   1.0000   0.0142
  -9.000  -0.9377   0.01674   0.01144  -0.0056   1.0000   0.0146
  -8.750  -0.9148   0.01621   0.01086  -0.0051   1.0000   0.0151
  -8.500  -0.8914   0.01569   0.01030  -0.0047   1.0000   0.0156
  -8.250  -0.8678   0.01518   0.00975  -0.0043   1.0000   0.0159
  -8.000  -0.8355   0.01470   0.00921  -0.0057   0.9766   0.0162
  -7.750  -0.8120   0.01341   0.00781  -0.0058   0.9516   0.0171
  -7.500  -0.7911   0.01297   0.00730  -0.0046   0.9322   0.0177
  -7.250  -0.7689   0.01264   0.00691  -0.0037   0.9168   0.0184
  -7.000  -0.7457   0.01231   0.00651  -0.0029   0.9034   0.0192
  -6.750  -0.7218   0.01200   0.00613  -0.0023   0.8913   0.0200
  -6.500  -0.6967   0.01179   0.00586  -0.0019   0.8802   0.0207
  -6.000  -0.6490   0.01086   0.00481  -0.0007   0.8587   0.0240
  -5.750  -0.6231   0.01062   0.00451  -0.0004   0.8494   0.0256
  -5.500  -0.5971   0.01038   0.00421  -0.0002   0.8399   0.0271
  -5.250  -0.5717   0.00999   0.00379   0.0001   0.8306   0.0311
  -5.000  -0.5451   0.00980   0.00355   0.0003   0.8218   0.0337
  -4.750  -0.5188   0.00949   0.00324   0.0004   0.8126   0.0398
  -4.500  -0.4923   0.00923   0.00298   0.0006   0.8043   0.0489
  -4.250  -0.4664   0.00885   0.00271   0.0007   0.7956   0.0760
  -4.000  -0.4412   0.00832   0.00241   0.0009   0.7873   0.1337
  -3.750  -0.4175   0.00757   0.00205   0.0012   0.7789   0.2351
  -3.500  -0.3950   0.00658   0.00164   0.0015   0.7706   0.3814
  -3.250  -0.3695   0.00613   0.00148   0.0017   0.7623   0.4739
  -3.000  -0.3418   0.00596   0.00140   0.0016   0.7539   0.5074
  -2.750  -0.3139   0.00587   0.00132   0.0016   0.7460   0.5301
  -2.500  -0.2855   0.00580   0.00126   0.0014   0.7379   0.5452
  -2.250  -0.2572   0.00576   0.00121   0.0013   0.7303   0.5601
  -2.000  -0.2287   0.00570   0.00117   0.0012   0.7224   0.5784
  -1.750  -0.2006   0.00566   0.00114   0.0011   0.7151   0.5970
  -1.500  -0.1723   0.00560   0.00113   0.0010   0.7073   0.6160
  -1.250  -0.1437   0.00561   0.00111   0.0009   0.6999   0.6270
  -1.000  -0.1150   0.00557   0.00109   0.0007   0.6921   0.6349
  -0.750  -0.0864   0.00558   0.00106   0.0006   0.6850   0.6425
  -0.500  -0.0576   0.00556   0.00105   0.0004   0.6778   0.6503
  -0.250  -0.0289   0.00557   0.00104   0.0002   0.6710   0.6574
   0.000  -0.0001   0.00555   0.00104   0.0000   0.6642   0.6642
   0.250   0.0287   0.00557   0.00104  -0.0002   0.6574   0.6710
   0.500   0.0574   0.00556   0.00105  -0.0004   0.6503   0.6778
   0.750   0.0862   0.00558   0.00106  -0.0005   0.6425   0.6850
   1.000   0.1149   0.00557   0.00109  -0.0007   0.6349   0.6922
   1.250   0.1436   0.00561   0.00111  -0.0009   0.6270   0.7000
   1.500   0.1721   0.00560   0.00113  -0.0010   0.6160   0.7073
   1.750   0.2004   0.00566   0.00114  -0.0011   0.5969   0.7151
   2.000   0.2286   0.00570   0.00117  -0.0012   0.5784   0.7224
   2.250   0.2570   0.00576   0.00121  -0.0013   0.5601   0.7304
   2.500   0.2853   0.00580   0.00126  -0.0014   0.5452   0.7379
   2.750   0.3137   0.00587   0.00132  -0.0015   0.5301   0.7460
   3.000   0.3417   0.00596   0.00140  -0.0016   0.5071   0.7539
   3.250   0.3694   0.00613   0.00148  -0.0016   0.4739   0.7623
   3.500   0.3949   0.00657   0.00164  -0.0015   0.3827   0.7706
   3.750   0.4174   0.00756   0.00204  -0.0011   0.2366   0.7789
   4.000   0.4411   0.00832   0.00240  -0.0009   0.1347   0.7874
   4.250   0.4662   0.00885   0.00271  -0.0007   0.0762   0.7956
   4.500   0.4921   0.00923   0.00298  -0.0005   0.0489   0.8043
   4.750   0.5186   0.00949   0.00324  -0.0004   0.0398   0.8126
   5.000   0.5449   0.00980   0.00355  -0.0002   0.0337   0.8218
   5.250   0.5715   0.00999   0.00379  -0.0001   0.0311   0.8306
   5.500   0.5971   0.01035   0.00418   0.0002   0.0274   0.8399
   5.750   0.6230   0.01061   0.00451   0.0005   0.0256   0.8494
   6.000   0.6488   0.01086   0.00481   0.0008   0.0240   0.8587
   6.500   0.6967   0.01176   0.00582   0.0019   0.0207   0.8803
   6.750   0.7217   0.01198   0.00611   0.0023   0.0200   0.8914
   7.000   0.7456   0.01230   0.00650   0.0029   0.0192   0.9036
   7.250   0.7687   0.01264   0.00691   0.0037   0.0185   0.9170
   7.500   0.7909   0.01298   0.00731   0.0047   0.0178   0.9323
   7.750   0.8119   0.01341   0.00781   0.0058   0.0171   0.9518
   8.000   0.8357   0.01467   0.00918   0.0057   0.0162   0.9765
   8.250   0.8677   0.01518   0.00975   0.0043   0.0159   1.0000
   8.500   0.8913   0.01570   0.01032   0.0047   0.0156   1.0000
   8.750   0.9152   0.01614   0.01079   0.0050   0.0151   1.0000
   9.000   0.9378   0.01673   0.01142   0.0056   0.0146   1.0000
   9.250   0.9598   0.01736   0.01210   0.0061   0.0142   1.0000
   9.500   0.9815   0.01798   0.01277   0.0067   0.0138   1.0000
   9.750   1.0028   0.01860   0.01342   0.0074   0.0135   1.0000
  10.000   1.0227   0.01937   0.01423   0.0081   0.0132   1.0000
  10.250   1.0386   0.02073   0.01567   0.0093   0.0128   1.0000
  10.500   1.0505   0.02300   0.01813   0.0109   0.0124   1.0000
  10.750   1.0686   0.02378   0.01902   0.0119   0.0123   1.0000
  11.000   1.0857   0.02458   0.01992   0.0129   0.0121   1.0000
  11.250   1.1008   0.02551   0.02096   0.0142   0.0118   1.0000
  11.500   1.1131   0.02634   0.02188   0.0159   0.0116   1.0000
  11.750   1.1199   0.02764   0.02331   0.0182   0.0114   1.0000
  12.000   1.1271   0.02872   0.02450   0.0201   0.0112   1.0000
  12.250   1.1309   0.03032   0.02623   0.0221   0.0111   1.0000
  12.500   1.1363   0.03163   0.02765   0.0236   0.0109   1.0000
  12.750   1.1380   0.03346   0.02961   0.0251   0.0108   1.0000
  13.000   1.1437   0.03475   0.03099   0.0261   0.0105   1.0000
  13.250   1.1419   0.03705   0.03343   0.0271   0.0104   1.0000
  13.500   1.1439   0.03897   0.03545   0.0276   0.0103   1.0000
  13.750   1.1442   0.04118   0.03776   0.0279   0.0102   1.0000
  14.000   1.1474   0.04313   0.03976   0.0279   0.0100   1.0000
  14.250   1.1412   0.04637   0.04312   0.0275   0.0099   1.0000
  14.500   1.1323   0.05013   0.04702   0.0267   0.0099   1.0000
  14.750   1.1206   0.05451   0.05156   0.0253   0.0098   1.0000
  15.000   1.1056   0.05964   0.05683   0.0231   0.0098   1.0000
  15.250   1.0873   0.06572   0.06310   0.0201   0.0098   1.0000
  15.500   1.0679   0.07250   0.07003   0.0163   0.0097   1.0000
  15.750   1.0353   0.08274   0.08051   0.0099   0.0099   1.0000
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