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NACA M3 (nacam3-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA M3 (nacam3-il)
Reynolds number: 100,000
Max Cl/Cd: 37.94 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nacam3-il-100000.txt
Download as CSV file: xf-nacam3-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M3                                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5320   0.11150   0.10633  -0.0127   1.0000   0.1820
 -10.750  -0.8318   0.07298   0.06731  -0.0326   1.0000   0.0934
 -10.500  -0.8480   0.06838   0.06261  -0.0315   1.0000   0.0920
 -10.250  -0.8690   0.06367   0.05772  -0.0296   1.0000   0.0904
 -10.000  -0.8915   0.05838   0.05209  -0.0272   1.0000   0.0881
  -9.750  -0.9239   0.05188   0.04479  -0.0228   1.0000   0.0844
  -9.500  -0.9296   0.04814   0.04039  -0.0194   1.0000   0.0832
  -9.250  -0.9224   0.04504   0.03688  -0.0171   1.0000   0.0829
  -9.000  -0.9114   0.04183   0.03335  -0.0153   1.0000   0.0832
  -8.750  -0.8959   0.03915   0.03054  -0.0141   1.0000   0.0849
  -8.500  -0.8779   0.03717   0.02846  -0.0129   1.0000   0.0869
  -8.250  -0.8611   0.03508   0.02609  -0.0113   1.0000   0.0884
  -8.000  -0.8430   0.03303   0.02375  -0.0097   1.0000   0.0897
  -7.750  -0.8235   0.03120   0.02164  -0.0083   1.0000   0.0914
  -7.500  -0.8039   0.02977   0.01991  -0.0067   1.0000   0.0941
  -7.250  -0.7816   0.02790   0.01798  -0.0058   1.0000   0.0972
  -7.000  -0.7589   0.02650   0.01660  -0.0049   1.0000   0.1006
  -6.750  -0.7366   0.02526   0.01528  -0.0038   1.0000   0.1047
  -6.500  -0.7144   0.02402   0.01395  -0.0026   1.0000   0.1098
  -6.250  -0.6941   0.02289   0.01297  -0.0013   1.0000   0.1174
  -6.000  -0.6747   0.02175   0.01190   0.0002   1.0000   0.1269
  -5.750  -0.6573   0.02061   0.01091   0.0022   1.0000   0.1416
  -5.500  -0.6425   0.01936   0.00993   0.0044   1.0000   0.1708
  -5.250  -0.6303   0.01797   0.00903   0.0070   1.0000   0.2311
  -5.000  -0.6179   0.01681   0.00842   0.0095   1.0000   0.3136
  -4.750  -0.6033   0.01603   0.00806   0.0118   1.0000   0.3921
  -4.500  -0.5871   0.01547   0.00784   0.0140   1.0000   0.4621
  -4.250  -0.5701   0.01506   0.00772   0.0162   1.0000   0.5290
  -4.000  -0.5528   0.01480   0.00775   0.0187   1.0000   0.5944
  -3.750  -0.5347   0.01468   0.00785   0.0213   1.0000   0.6508
  -3.500  -0.5156   0.01466   0.00794   0.0236   1.0000   0.6973
  -3.250  -0.4955   0.01472   0.00809   0.0260   1.0000   0.7354
  -3.000  -0.4758   0.01486   0.00828   0.0284   1.0000   0.7722
  -2.750  -0.4563   0.01508   0.00854   0.0311   1.0000   0.8067
  -2.500  -0.4359   0.01540   0.00886   0.0336   1.0000   0.8382
  -2.250  -0.4124   0.01577   0.00921   0.0356   1.0000   0.8666
  -2.000  -0.3852   0.01616   0.00955   0.0365   1.0000   0.8939
  -1.750  -0.3429   0.01670   0.01000   0.0346   1.0000   0.9163
  -1.500  -0.2910   0.01721   0.01040   0.0304   1.0000   0.9362
  -1.250  -0.2263   0.01762   0.01070   0.0233   1.0000   0.9506
  -1.000  -0.1623   0.01785   0.01085   0.0159   1.0000   0.9638
  -0.750  -0.1009   0.01795   0.01088   0.0087   1.0000   0.9769
  -0.500  -0.0391   0.01793   0.01083   0.0012   1.0000   0.9895
  -0.250   0.0161   0.01784   0.01072  -0.0054   1.0000   1.0000
   0.000   0.0000   0.01781   0.01070   0.0000   1.0000   1.0000
   0.250  -0.0161   0.01783   0.01072   0.0054   1.0000   1.0000
   0.500   0.0391   0.01793   0.01083  -0.0012   0.9895   1.0000
   0.750   0.1008   0.01795   0.01088  -0.0087   0.9769   1.0000
   1.000   0.1623   0.01785   0.01085  -0.0159   0.9638   1.0000
   1.250   0.2263   0.01762   0.01070  -0.0233   0.9506   1.0000
   1.500   0.2910   0.01720   0.01040  -0.0304   0.9363   1.0000
   1.750   0.3428   0.01670   0.01000  -0.0346   0.9163   1.0000
   2.000   0.3851   0.01616   0.00954  -0.0365   0.8939   1.0000
   2.250   0.4124   0.01577   0.00921  -0.0355   0.8666   1.0000
   2.500   0.4358   0.01539   0.00885  -0.0336   0.8383   1.0000
   2.750   0.4562   0.01508   0.00854  -0.0310   0.8067   1.0000
   3.000   0.4757   0.01485   0.00828  -0.0284   0.7722   1.0000
   3.250   0.4954   0.01471   0.00808  -0.0260   0.7355   1.0000
   3.500   0.5155   0.01466   0.00794  -0.0236   0.6973   1.0000
   3.750   0.5346   0.01468   0.00785  -0.0212   0.6508   1.0000
   4.000   0.5527   0.01479   0.00775  -0.0187   0.5946   1.0000
   4.250   0.5700   0.01506   0.00771  -0.0162   0.5292   1.0000
   4.500   0.5870   0.01547   0.00783  -0.0140   0.4622   1.0000
   4.750   0.6032   0.01602   0.00806  -0.0117   0.3922   1.0000
   5.000   0.6178   0.01680   0.00842  -0.0094   0.3138   1.0000
   5.250   0.6303   0.01796   0.00903  -0.0070   0.2313   1.0000
   5.500   0.6424   0.01936   0.00992  -0.0044   0.1710   1.0000
   5.750   0.6572   0.02061   0.01090  -0.0021   0.1417   1.0000
   6.000   0.6747   0.02174   0.01190  -0.0002   0.1270   1.0000
   6.250   0.6941   0.02289   0.01297   0.0013   0.1174   1.0000
   6.500   0.7144   0.02402   0.01395   0.0026   0.1098   1.0000
   6.750   0.7365   0.02526   0.01527   0.0038   0.1047   1.0000
   7.000   0.7589   0.02649   0.01659   0.0049   0.1006   1.0000
   7.250   0.7815   0.02790   0.01797   0.0058   0.0972   1.0000
   7.500   0.8038   0.02977   0.01990   0.0067   0.0941   1.0000
   7.750   0.8235   0.03120   0.02164   0.0083   0.0914   1.0000
   8.000   0.8430   0.03302   0.02375   0.0097   0.0897   1.0000
   8.250   0.8611   0.03508   0.02609   0.0113   0.0884   1.0000
   8.500   0.8780   0.03716   0.02845   0.0129   0.0869   1.0000
   8.750   0.8960   0.03914   0.03053   0.0140   0.0849   1.0000
   9.000   0.9114   0.04184   0.03335   0.0152   0.0832   1.0000
   9.250   0.9224   0.04506   0.03690   0.0171   0.0829   1.0000
   9.500   0.9297   0.04815   0.04040   0.0193   0.0832   1.0000
   9.750   0.9232   0.05194   0.04486   0.0229   0.0845   1.0000
  10.000   0.8916   0.05841   0.05212   0.0271   0.0881   1.0000
  10.250   0.8692   0.06370   0.05775   0.0295   0.0904   1.0000
  10.500   0.8483   0.06841   0.06265   0.0315   0.0920   1.0000
  10.750   0.8322   0.07304   0.06736   0.0325   0.0934   1.0000
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