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NACA M2 (nacam2-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA M2 (nacam2-il)
Reynolds number: 500,000
Max Cl/Cd: 44.55 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nacam2-il-500000.txt
Download as CSV file: xf-nacam2-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M2                                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.8947   0.05520   0.05251  -0.0194   1.0000   0.0150
 -10.250  -0.9149   0.05083   0.04790  -0.0180   1.0000   0.0150
 -10.000  -0.9318   0.04536   0.04207  -0.0165   1.0000   0.0150
  -9.750  -0.9472   0.03894   0.03516  -0.0143   1.0000   0.0151
  -9.500  -0.9467   0.03455   0.03040  -0.0126   1.0000   0.0154
  -9.250  -0.9305   0.03314   0.02888  -0.0118   1.0000   0.0159
  -9.000  -0.9120   0.03204   0.02767  -0.0112   1.0000   0.0164
  -8.750  -0.8945   0.03037   0.02580  -0.0103   1.0000   0.0170
  -8.500  -0.8770   0.02836   0.02353  -0.0092   1.0000   0.0179
  -8.250  -0.8577   0.02659   0.02143  -0.0082   1.0000   0.0190
  -8.000  -0.8350   0.02588   0.02045  -0.0073   1.0000   0.0198
  -7.750  -0.8198   0.02194   0.01616  -0.0061   1.0000   0.0209
  -7.500  -0.7966   0.02107   0.01523  -0.0056   1.0000   0.0218
  -7.250  -0.7727   0.02027   0.01434  -0.0051   1.0000   0.0230
  -7.000  -0.7483   0.01952   0.01348  -0.0046   1.0000   0.0244
  -6.750  -0.7230   0.01908   0.01291  -0.0042   1.0000   0.0259
  -6.500  -0.7001   0.01734   0.01095  -0.0034   1.0000   0.0273
  -6.250  -0.6770   0.01597   0.00956  -0.0028   1.0000   0.0290
  -6.000  -0.6523   0.01535   0.00890  -0.0023   1.0000   0.0307
  -5.750  -0.6273   0.01481   0.00831  -0.0018   1.0000   0.0326
  -5.500  -0.6024   0.01425   0.00769  -0.0012   1.0000   0.0341
  -5.250  -0.5773   0.01382   0.00720  -0.0007   1.0000   0.0350
  -5.000  -0.5554   0.01258   0.00590   0.0004   1.0000   0.0371
  -4.750  -0.5320   0.01194   0.00523   0.0011   1.0000   0.0392
  -4.500  -0.5081   0.01147   0.00474   0.0019   1.0000   0.0408
  -4.250  -0.4840   0.01107   0.00432   0.0026   1.0000   0.0426
  -4.000  -0.4599   0.01074   0.00396   0.0034   1.0000   0.0445
  -3.750  -0.4357   0.01044   0.00362   0.0041   1.0000   0.0456
  -3.500  -0.4120   0.01001   0.00316   0.0049   1.0000   0.0487
  -3.250  -0.3881   0.00970   0.00288   0.0057   1.0000   0.0532
  -3.000  -0.3641   0.00942   0.00264   0.0065   1.0000   0.0631
  -2.750  -0.3414   0.00867   0.00234   0.0071   1.0000   0.1598
  -2.500  -0.3185   0.00787   0.00215   0.0075   1.0000   0.3035
  -2.250  -0.2948   0.00726   0.00204   0.0079   1.0000   0.4288
  -2.000  -0.2705   0.00678   0.00200   0.0083   1.0000   0.5395
  -1.750  -0.2456   0.00639   0.00200   0.0087   1.0000   0.6398
  -1.500  -0.2162   0.00612   0.00202   0.0083   0.9987   0.7138
  -1.250  -0.1797   0.00586   0.00203   0.0066   0.9950   0.7846
  -1.000  -0.1437   0.00565   0.00205   0.0052   0.9895   0.8473
  -0.750  -0.1055   0.00554   0.00207   0.0033   0.9844   0.8905
  -0.500  -0.0717   0.00551   0.00212   0.0026   0.9780   0.9260
  -0.250  -0.0361   0.00554   0.00219   0.0015   0.9718   0.9513
   0.000   0.0000   0.00555   0.00220   0.0000   0.9630   0.9630
   0.250   0.0361   0.00554   0.00219  -0.0015   0.9516   0.9718
   0.500   0.0717   0.00551   0.00212  -0.0026   0.9261   0.9780
   0.750   0.1055   0.00554   0.00207  -0.0033   0.8906   0.9844
   1.000   0.1437   0.00565   0.00205  -0.0052   0.8475   0.9895
   1.250   0.1797   0.00585   0.00203  -0.0066   0.7853   0.9950
   1.500   0.2161   0.00612   0.00202  -0.0083   0.7139   0.9987
   1.750   0.2456   0.00639   0.00200  -0.0087   0.6398   1.0000
   2.000   0.2705   0.00678   0.00200  -0.0083   0.5396   1.0000
   2.250   0.2947   0.00726   0.00204  -0.0079   0.4288   1.0000
   2.500   0.3184   0.00787   0.00215  -0.0075   0.3039   1.0000
   2.750   0.3413   0.00867   0.00234  -0.0071   0.1590   1.0000
   3.000   0.3640   0.00942   0.00264  -0.0064   0.0632   1.0000
   3.250   0.3880   0.00970   0.00288  -0.0057   0.0532   1.0000
   3.500   0.4120   0.01001   0.00316  -0.0049   0.0487   1.0000
   3.750   0.4356   0.01044   0.00362  -0.0041   0.0457   1.0000
   4.000   0.4598   0.01074   0.00396  -0.0033   0.0445   1.0000
   4.250   0.4840   0.01107   0.00432  -0.0026   0.0427   1.0000
   4.500   0.5080   0.01147   0.00474  -0.0019   0.0408   1.0000
   4.750   0.5319   0.01194   0.00523  -0.0011   0.0392   1.0000
   5.000   0.5554   0.01258   0.00590  -0.0003   0.0371   1.0000
   5.250   0.5773   0.01382   0.00720   0.0007   0.0350   1.0000
   5.500   0.6024   0.01425   0.00769   0.0012   0.0341   1.0000
   5.750   0.6273   0.01481   0.00831   0.0018   0.0326   1.0000
   6.000   0.6523   0.01534   0.00889   0.0023   0.0306   1.0000
   6.250   0.6770   0.01597   0.00956   0.0028   0.0290   1.0000
   6.500   0.7001   0.01733   0.01095   0.0034   0.0273   1.0000
   6.750   0.7230   0.01909   0.01291   0.0042   0.0259   1.0000
   7.000   0.7483   0.01951   0.01347   0.0046   0.0244   1.0000
   7.250   0.7727   0.02026   0.01433   0.0051   0.0230   1.0000
   7.500   0.7966   0.02107   0.01522   0.0056   0.0218   1.0000
   7.750   0.8199   0.02193   0.01615   0.0061   0.0209   1.0000
   8.000   0.8351   0.02588   0.02046   0.0073   0.0198   1.0000
   8.250   0.8577   0.02660   0.02144   0.0081   0.0190   1.0000
   8.500   0.8771   0.02836   0.02352   0.0092   0.0179   1.0000
   8.750   0.8946   0.03038   0.02582   0.0102   0.0170   1.0000
   9.000   0.9120   0.03207   0.02769   0.0111   0.0164   1.0000
   9.250   0.9305   0.03317   0.02890   0.0118   0.0159   1.0000
   9.500   0.9470   0.03453   0.03037   0.0126   0.0154   1.0000
   9.750   0.9471   0.03900   0.03521   0.0143   0.0151   1.0000
  10.000   0.9319   0.04540   0.04212   0.0164   0.0150   1.0000
  10.250   0.9147   0.05091   0.04798   0.0179   0.0150   1.0000
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