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NASA/LANGLEY 64-012 AIRFOIL (n64012-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NASA/LANGLEY 64-012 AIRFOIL (n64012-il)
Reynolds number: 500,000
Max Cl/Cd: 51.48 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n64012-il-500000-n5.txt
Download as CSV file: xf-n64012-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.500  -1.0015   0.08651   0.08373  -0.0070   1.0000   0.0099
 -15.250  -1.0621   0.07087   0.06767  -0.0166   1.0000   0.0097
 -15.000  -1.0683   0.06631   0.06301  -0.0192   1.0000   0.0098
 -14.750  -1.0815   0.06097   0.05751  -0.0219   1.0000   0.0098
 -14.500  -1.0890   0.05682   0.05324  -0.0237   1.0000   0.0100
 -14.250  -1.0942   0.05316   0.04945  -0.0251   1.0000   0.0101
 -14.000  -1.0994   0.04971   0.04586  -0.0261   1.0000   0.0101
 -13.750  -1.1032   0.04660   0.04262  -0.0267   1.0000   0.0103
 -13.500  -1.1071   0.04360   0.03947  -0.0269   1.0000   0.0104
 -13.250  -1.1084   0.04102   0.03673  -0.0268   1.0000   0.0105
 -13.000  -1.1085   0.03867   0.03423  -0.0264   1.0000   0.0107
 -12.750  -1.1074   0.03649   0.03190  -0.0256   1.0000   0.0109
 -12.500  -1.1049   0.03451   0.02976  -0.0247   1.0000   0.0110
 -12.250  -1.1010   0.03268   0.02776  -0.0235   1.0000   0.0112
 -12.000  -1.0956   0.03100   0.02593  -0.0221   1.0000   0.0114
 -11.750  -1.0885   0.02950   0.02428  -0.0207   1.0000   0.0116
 -11.500  -1.0798   0.02820   0.02283  -0.0191   1.0000   0.0118
 -11.250  -1.0700   0.02699   0.02146  -0.0175   1.0000   0.0120
 -11.000  -1.0583   0.02604   0.02040  -0.0159   1.0000   0.0122
 -10.750  -1.0466   0.02490   0.01913  -0.0142   1.0000   0.0124
 -10.500  -1.0335   0.02366   0.01782  -0.0128   1.0000   0.0128
 -10.250  -1.0171   0.02273   0.01682  -0.0117   1.0000   0.0131
 -10.000  -0.9990   0.02194   0.01596  -0.0108   1.0000   0.0134
  -9.750  -0.9801   0.02116   0.01512  -0.0099   1.0000   0.0136
  -9.500  -0.9607   0.02039   0.01427  -0.0091   1.0000   0.0139
  -9.250  -0.9408   0.01962   0.01344  -0.0084   1.0000   0.0143
  -9.000  -0.9203   0.01889   0.01265  -0.0076   1.0000   0.0147
  -8.750  -0.8992   0.01821   0.01190  -0.0070   1.0000   0.0151
  -8.500  -0.8773   0.01761   0.01124  -0.0064   1.0000   0.0156
  -8.250  -0.8484   0.01698   0.01052  -0.0073   0.9696   0.0161
  -8.000  -0.8205   0.01617   0.00962  -0.0080   0.9473   0.0166
  -7.750  -0.7988   0.01555   0.00893  -0.0073   0.9276   0.0173
  -7.500  -0.7773   0.01510   0.00842  -0.0064   0.9111   0.0179
  -7.250  -0.7554   0.01469   0.00794  -0.0055   0.8968   0.0186
  -7.000  -0.7331   0.01428   0.00744  -0.0046   0.8837   0.0194
  -6.750  -0.7101   0.01391   0.00698  -0.0039   0.8720   0.0203
  -6.500  -0.6863   0.01356   0.00654  -0.0033   0.8605   0.0211
  -6.250  -0.6629   0.01310   0.00602  -0.0027   0.8498   0.0226
  -6.000  -0.6385   0.01276   0.00564  -0.0022   0.8399   0.0245
  -5.750  -0.6134   0.01248   0.00529  -0.0019   0.8301   0.0266
  -5.500  -0.5879   0.01219   0.00494  -0.0016   0.8207   0.0286
  -5.250  -0.5628   0.01186   0.00456  -0.0012   0.8117   0.0318
  -5.000  -0.5368   0.01159   0.00426  -0.0010   0.8026   0.0350
  -4.750  -0.5107   0.01133   0.00396  -0.0008   0.7941   0.0398
  -4.500  -0.4847   0.01106   0.00368  -0.0006   0.7853   0.0481
  -4.250  -0.4589   0.01071   0.00339  -0.0004   0.7767   0.0671
  -4.000  -0.4338   0.01028   0.00309  -0.0002   0.7685   0.1041
  -3.750  -0.4089   0.00973   0.00278  -0.0001   0.7604   0.1631
  -3.250  -0.3618   0.00822   0.00205   0.0005   0.7448   0.3678
  -3.000  -0.3367   0.00778   0.00188   0.0007   0.7371   0.4518
  -2.750  -0.3096   0.00758   0.00178   0.0007   0.7289   0.4911
  -2.500  -0.2825   0.00743   0.00171   0.0008   0.7214   0.5283
  -2.250  -0.2552   0.00730   0.00167   0.0009   0.7137   0.5629
  -1.750  -0.1996   0.00718   0.00161   0.0009   0.6996   0.6058
  -1.500  -0.1712   0.00716   0.00155   0.0008   0.6927   0.6139
  -1.250  -0.1427   0.00713   0.00152   0.0007   0.6858   0.6215
  -1.000  -0.1142   0.00712   0.00147   0.0006   0.6787   0.6284
  -0.750  -0.0857   0.00711   0.00144   0.0004   0.6719   0.6342
  -0.500  -0.0572   0.00710   0.00142   0.0003   0.6649   0.6405
  -0.250  -0.0285   0.00710   0.00141   0.0001   0.6589   0.6467
   0.000   0.0000   0.00709   0.00141   0.0000   0.6525   0.6525
   0.250   0.0286   0.00710   0.00141  -0.0001   0.6467   0.6589
   0.500   0.0572   0.00710   0.00142  -0.0003   0.6406   0.6649
   0.750   0.0857   0.00711   0.00144  -0.0004   0.6342   0.6719
   1.000   0.1143   0.00712   0.00147  -0.0006   0.6284   0.6787
   1.250   0.1428   0.00713   0.00152  -0.0007   0.6215   0.6858
   1.500   0.1712   0.00716   0.00155  -0.0008   0.6140   0.6927
   1.750   0.1996   0.00718   0.00161  -0.0009   0.6058   0.6996
   2.250   0.2553   0.00730   0.00167  -0.0009   0.5633   0.7137
   2.500   0.2826   0.00743   0.00171  -0.0008   0.5282   0.7214
   2.750   0.3096   0.00759   0.00178  -0.0007   0.4908   0.7289
   3.000   0.3367   0.00778   0.00188  -0.0007   0.4517   0.7371
   3.250   0.3619   0.00822   0.00205  -0.0005   0.3676   0.7448
   3.750   0.4089   0.00974   0.00278   0.0000   0.1624   0.7604
   4.000   0.4338   0.01028   0.00309   0.0002   0.1040   0.7685
   4.250   0.4590   0.01071   0.00340   0.0004   0.0670   0.7768
   4.500   0.4847   0.01106   0.00369   0.0006   0.0479   0.7853
   4.750   0.5108   0.01133   0.00396   0.0008   0.0397   0.7942
   5.000   0.5368   0.01160   0.00426   0.0010   0.0350   0.8026
   5.250   0.5628   0.01186   0.00456   0.0012   0.0318   0.8117
   5.500   0.5880   0.01219   0.00494   0.0016   0.0285   0.8207
   5.750   0.6135   0.01248   0.00529   0.0018   0.0265   0.8301
   6.000   0.6386   0.01276   0.00564   0.0022   0.0245   0.8399
   6.250   0.6630   0.01310   0.00602   0.0027   0.0227   0.8497
   6.500   0.6864   0.01357   0.00655   0.0033   0.0211   0.8605
   6.750   0.7102   0.01391   0.00698   0.0039   0.0203   0.8720
   7.000   0.7331   0.01429   0.00744   0.0046   0.0194   0.8837
   7.250   0.7555   0.01469   0.00794   0.0055   0.0186   0.8968
   7.500   0.7774   0.01510   0.00842   0.0064   0.0178   0.9111
   7.750   0.7987   0.01555   0.00894   0.0073   0.0172   0.9276
   8.000   0.8204   0.01618   0.00963   0.0081   0.0166   0.9473
   8.250   0.8483   0.01698   0.01051   0.0073   0.0161   0.9696
   8.500   0.8775   0.01758   0.01121   0.0064   0.0155   1.0000
   8.750   0.8992   0.01820   0.01189   0.0070   0.0151   1.0000
   9.000   0.9201   0.01890   0.01266   0.0076   0.0147   1.0000
   9.250   0.9406   0.01964   0.01346   0.0084   0.0143   1.0000
   9.500   0.9606   0.02040   0.01428   0.0091   0.0140   1.0000
   9.750   0.9803   0.02113   0.01509   0.0099   0.0136   1.0000
  10.000   0.9988   0.02198   0.01601   0.0108   0.0134   1.0000
  10.250   1.0168   0.02277   0.01686   0.0117   0.0131   1.0000
  10.500   1.0337   0.02363   0.01778   0.0128   0.0128   1.0000
  10.750   1.0469   0.02487   0.01911   0.0142   0.0125   1.0000
  11.000   1.0582   0.02606   0.02041   0.0159   0.0122   1.0000
  11.250   1.0698   0.02705   0.02153   0.0175   0.0120   1.0000
  11.500   1.0798   0.02823   0.02286   0.0191   0.0118   1.0000
  11.750   1.0883   0.02959   0.02437   0.0207   0.0116   1.0000
  12.000   1.0955   0.03107   0.02601   0.0221   0.0114   1.0000
  12.250   1.1011   0.03271   0.02781   0.0234   0.0112   1.0000
  12.500   1.1049   0.03457   0.02982   0.0246   0.0111   1.0000
  12.750   1.1074   0.03657   0.03198   0.0256   0.0109   1.0000
  13.000   1.1091   0.03866   0.03423   0.0263   0.0107   1.0000
  13.250   1.1087   0.04107   0.03680   0.0267   0.0106   1.0000
  13.500   1.1069   0.04372   0.03959   0.0268   0.0104   1.0000
  13.750   1.1020   0.04686   0.04290   0.0266   0.0103   1.0000
  14.000   1.1013   0.04957   0.04571   0.0260   0.0101   1.0000
  14.250   1.0975   0.05284   0.04911   0.0251   0.0101   1.0000
  14.500   1.0964   0.05590   0.05227   0.0239   0.0099   1.0000
  14.750   1.0812   0.06119   0.05776   0.0216   0.0099   1.0000
  15.000   1.0720   0.06592   0.06261   0.0192   0.0098   1.0000
  15.250   1.0667   0.07030   0.06707   0.0167   0.0097   1.0000
  15.500   1.0066   0.08571   0.08291   0.0073   0.0099   1.0000
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