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NACA M7 AIRFOIL (m7-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA M7 AIRFOIL (m7-il)
Reynolds number: 200,000
Max Cl/Cd: 68.23 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m7-il-200000-n5.txt
Download as CSV file: xf-m7-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M7 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5254   0.13535   0.13236   0.0432   0.8990   0.0087
  -9.500  -0.5224   0.13280   0.12973   0.0426   0.8641   0.0088
  -9.250  -0.5183   0.13006   0.12692   0.0413   0.8433   0.0088
  -9.000  -0.5139   0.12724   0.12407   0.0398   0.8270   0.0088
  -8.750  -0.5093   0.12438   0.12117   0.0380   0.8131   0.0089
  -8.500  -0.5048   0.12157   0.11833   0.0360   0.8008   0.0089
  -8.250  -0.5003   0.11875   0.11548   0.0336   0.7895   0.0089
  -8.000  -0.4958   0.11586   0.11256   0.0310   0.7790   0.0090
  -7.750  -0.4904   0.11284   0.10950   0.0285   0.7688   0.0090
  -7.500  -0.4814   0.10952   0.10615   0.0258   0.7597   0.0090
  -7.250  -0.4758   0.10434   0.10095   0.0250   0.7520   0.0092
  -7.000  -0.4692   0.09932   0.09591   0.0261   0.7438   0.0094
  -6.750  -0.4609   0.09547   0.09201   0.0249   0.7362   0.0096
  -6.500  -0.4507   0.09180   0.08831   0.0230   0.7281   0.0098
  -6.250  -0.4390   0.08826   0.08472   0.0208   0.7210   0.0100
  -6.000  -0.4254   0.08472   0.08111   0.0184   0.7133   0.0102
  -5.750  -0.4104   0.08123   0.07754   0.0160   0.7066   0.0105
  -5.500  -0.3934   0.07773   0.07397   0.0134   0.6991   0.0108
  -5.000  -0.3550   0.07084   0.06692   0.0085   0.6856   0.0115
  -4.750  -0.3337   0.06749   0.06345   0.0062   0.6793   0.0119
  -4.500  -0.3108   0.06418   0.06004   0.0040   0.6725   0.0123
  -4.250  -0.2866   0.06100   0.05673   0.0020   0.6661   0.0128
  -4.000  -0.2604   0.05798   0.05358   0.0001   0.6599   0.0135
  -3.750  -0.2312   0.05535   0.05077  -0.0017   0.6532   0.0142
  -3.500  -0.1994   0.05320   0.04841  -0.0032   0.6474   0.0148
  -3.250  -0.1709   0.05075   0.04581  -0.0042   0.6407   0.0151
  -3.000  -0.1437   0.04813   0.04300  -0.0048   0.6350   0.0152
  -2.750  -0.1163   0.04543   0.04013  -0.0053   0.6288   0.0153
  -2.500  -0.0891   0.04275   0.03727  -0.0056   0.6228   0.0153
  -2.250  -0.0672   0.03775   0.03203  -0.0060   0.6182   0.0164
  -2.000  -0.0455   0.03513   0.02932  -0.0063   0.6116   0.0183
  -1.750  -0.0188   0.03303   0.02702  -0.0064   0.6060   0.0208
  -1.500   0.0103   0.03088   0.02464  -0.0063   0.6002   0.0232
  -1.250   0.0472   0.02964   0.02293  -0.0053   0.5944   0.0272
  -1.000   0.0685   0.02673   0.01995  -0.0058   0.5893   0.0308
  -0.750   0.0975   0.02510   0.01809  -0.0056   0.5829   0.0395
   0.250   0.2188   0.01763   0.00924  -0.0026   0.5616   0.0141
   0.500   0.2481   0.01645   0.00780  -0.0022   0.5559   0.0142
   0.750   0.2769   0.01555   0.00666  -0.0019   0.5500   0.0160
   1.000   0.3048   0.01462   0.00555  -0.0015   0.5452   0.0162
   1.250   0.3322   0.01385   0.00472  -0.0012   0.5391   0.0166
   1.500   0.3589   0.01331   0.00408  -0.0007   0.5336   0.0176
   1.750   0.3860   0.01297   0.00365  -0.0005   0.5282   0.0222
   2.000   0.4136   0.01279   0.00337  -0.0003   0.5223   0.0251
   2.500   0.4674   0.01240   0.00311   0.0001   0.5046   0.1717
   3.000   0.5771   0.01101   0.00327  -0.0118   0.4750   1.0000
   3.500   0.6298   0.01120   0.00332  -0.0114   0.4590   1.0000
   3.750   0.6561   0.01130   0.00339  -0.0112   0.4508   1.0000
   4.250   0.7085   0.01153   0.00358  -0.0108   0.4335   1.0000
   4.500   0.7347   0.01166   0.00370  -0.0107   0.4252   1.0000
   4.750   0.7608   0.01181   0.00381  -0.0105   0.4111   1.0000
   5.000   0.7868   0.01197   0.00398  -0.0104   0.3963   1.0000
   5.250   0.8128   0.01215   0.00415  -0.0102   0.3813   1.0000
   5.500   0.8388   0.01237   0.00435  -0.0101   0.3616   1.0000
   5.750   0.8645   0.01267   0.00459  -0.0101   0.3352   1.0000
   6.000   0.8894   0.01329   0.00497  -0.0103   0.2779   1.0000
   6.250   0.9120   0.01486   0.00589  -0.0110   0.1617   1.0000
   6.500   0.9329   0.01671   0.00718  -0.0117   0.0614   1.0000
   6.750   0.9569   0.01728   0.00781  -0.0115   0.0550   1.0000
   7.000   0.9809   0.01777   0.00840  -0.0113   0.0529   1.0000
   7.250   1.0045   0.01829   0.00904  -0.0111   0.0514   1.0000
   7.500   1.0276   0.01886   0.00973  -0.0109   0.0502   1.0000
   7.750   1.0502   0.01949   0.01052  -0.0106   0.0490   1.0000
   8.000   1.0721   0.02020   0.01138  -0.0103   0.0479   1.0000
   8.250   1.0930   0.02101   0.01233  -0.0099   0.0469   1.0000
   8.500   1.1126   0.02194   0.01341  -0.0095   0.0458   1.0000
   8.750   1.1303   0.02302   0.01465  -0.0090   0.0447   1.0000
   9.000   1.1454   0.02433   0.01614  -0.0083   0.0436   1.0000
   9.250   1.1623   0.02530   0.01726  -0.0078   0.0411   1.0000
   9.500   1.1797   0.02612   0.01818  -0.0074   0.0359   1.0000
   9.750   1.1917   0.02746   0.01959  -0.0069   0.0320   1.0000
  10.000   1.2205   0.02707   0.01942  -0.0068   0.0226   1.0000
  10.250   1.2366   0.02797   0.02019  -0.0064   0.0104   1.0000
  10.500   1.2390   0.03015   0.02238  -0.0057   0.0083   1.0000
  10.750   1.2386   0.03246   0.02484  -0.0048   0.0074   1.0000
  11.000   1.2386   0.03500   0.02754  -0.0043   0.0066   1.0000
  11.250   1.2374   0.03778   0.03052  -0.0040   0.0060   1.0000
  11.500   1.2334   0.04097   0.03386  -0.0038   0.0054   1.0000
  11.750   1.2330   0.04382   0.03688  -0.0037   0.0052   1.0000
  12.000   1.2322   0.04678   0.04001  -0.0036   0.0049   1.0000
  12.250   1.2304   0.04990   0.04331  -0.0036   0.0047   1.0000
  12.500   1.2278   0.05316   0.04673  -0.0038   0.0046   1.0000
  12.750   1.2246   0.05656   0.05029  -0.0040   0.0044   1.0000
  13.000   1.2206   0.06009   0.05400  -0.0043   0.0043   1.0000
  13.250   1.2160   0.06379   0.05786  -0.0047   0.0042   1.0000
  13.500   1.2103   0.06769   0.06192  -0.0053   0.0041   1.0000
  13.750   1.2043   0.07178   0.06618  -0.0061   0.0040   1.0000
  14.000   1.1977   0.07617   0.07074  -0.0072   0.0040   1.0000
  14.250   1.1903   0.08081   0.07555  -0.0085   0.0039   1.0000
  14.500   1.1822   0.08575   0.08065  -0.0100   0.0039   1.0000
  14.750   1.1734   0.09097   0.08605  -0.0119   0.0038   1.0000
  15.000   1.1636   0.09652   0.09176  -0.0140   0.0038   1.0000
  15.250   1.1532   0.10238   0.09778  -0.0164   0.0037   1.0000
  15.500   1.1422   0.10858   0.10414  -0.0191   0.0037   1.0000
  15.750   1.1309   0.11505   0.11077  -0.0220   0.0037   1.0000
  16.000   1.1192   0.12187   0.11776  -0.0253   0.0037   1.0000
  16.250   1.1072   0.12908   0.12512  -0.0290   0.0037   1.0000
  16.500   1.0949   0.13676   0.13298  -0.0330   0.0037   1.0000
  16.750   1.0815   0.14513   0.14152  -0.0374   0.0038   1.0000
  17.000   1.0660   0.15473   0.15129  -0.0425   0.0039   1.0000
  17.250   1.0494   0.16541   0.16211  -0.0481   0.0041   1.0000
  17.500   1.0325   0.17706   0.17385  -0.0539   0.0043   1.0000
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