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NACA M11 AIRFOIL (m11-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA M11 AIRFOIL (m11-il)
Reynolds number: 200,000
Max Cl/Cd: 65.7 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m11-il-200000.txt
Download as CSV file: xf-m11-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M11 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5194   0.09565   0.09204  -0.0226   1.0000   0.0477
  -9.000  -0.5268   0.09130   0.08773  -0.0273   1.0000   0.0479
  -8.750  -0.5360   0.08748   0.08389  -0.0293   1.0000   0.0480
  -8.500  -0.5277   0.08181   0.07831  -0.0260   1.0000   0.0495
  -8.250  -0.5219   0.07922   0.07572  -0.0246   1.0000   0.0505
  -8.000  -0.5206   0.07633   0.07284  -0.0244   1.0000   0.0519
  -7.750  -0.5204   0.07285   0.06936  -0.0255   1.0000   0.0537
  -7.500  -0.5204   0.06903   0.06550  -0.0269   1.0000   0.0555
  -7.250  -0.5275   0.06477   0.06085  -0.0307   1.0000   0.0599
  -7.000  -0.5328   0.05932   0.05520  -0.0300   1.0000   0.0609
  -6.750  -0.5201   0.05606   0.05216  -0.0287   1.0000   0.0627
  -6.500  -0.5095   0.05416   0.05029  -0.0271   1.0000   0.0654
  -6.250  -0.5052   0.05334   0.04882  -0.0252   1.0000   0.0734
  -6.000  -0.5026   0.04725   0.04280  -0.0240   1.0000   0.0751
  -5.750  -0.4911   0.04482   0.04046  -0.0224   1.0000   0.0769
  -5.500  -0.4808   0.04290   0.03851  -0.0203   1.0000   0.0803
  -5.250  -0.4784   0.04055   0.03565  -0.0168   1.0000   0.0889
  -5.000  -0.4676   0.03822   0.03344  -0.0150   1.0000   0.0912
  -4.750  -0.4577   0.03689   0.03206  -0.0124   1.0000   0.0974
  -4.500  -0.4526   0.03475   0.02967  -0.0093   1.0000   0.1049
  -4.250  -0.4427   0.03321   0.02812  -0.0069   1.0000   0.1087
  -4.000  -0.4155   0.03097   0.02562  -0.0079   0.9960   0.1205
  -3.750  -0.3756   0.02393   0.01722  -0.0069   0.9909   0.0705
  -3.500  -0.3373   0.02081   0.01333  -0.0077   0.9858   0.0613
  -3.250  -0.2972   0.01986   0.01215  -0.0099   0.9800   0.0604
  -3.000  -0.2589   0.01818   0.01027  -0.0119   0.9741   0.0607
  -2.750  -0.2177   0.01649   0.00851  -0.0147   0.9702   0.0625
  -2.500  -0.1810   0.01549   0.00746  -0.0164   0.9623   0.0630
  -2.250  -0.1391   0.01457   0.00657  -0.0192   0.9574   0.0645
  -2.000  -0.1012   0.01386   0.00589  -0.0211   0.9498   0.0668
  -1.750  -0.0606   0.01322   0.00524  -0.0236   0.9434   0.0699
  -1.500  -0.0253   0.01269   0.00474  -0.0250   0.9339   0.0754
  -1.250   0.0129   0.01214   0.00422  -0.0268   0.9264   0.0855
  -1.000   0.0401   0.01130   0.00380  -0.0265   0.9134   0.1734
  -0.750   0.2016   0.00924   0.00431  -0.0532   0.9400   1.0000
  -0.500   0.2391   0.00909   0.00404  -0.0551   0.9206   1.0000
  -0.250   0.2709   0.00898   0.00382  -0.0557   0.9000   1.0000
   0.000   0.2966   0.00893   0.00367  -0.0550   0.8788   1.0000
   0.250   0.3193   0.00893   0.00356  -0.0537   0.8577   1.0000
   0.500   0.3417   0.00895   0.00346  -0.0523   0.8385   1.0000
   0.750   0.3635   0.00899   0.00341  -0.0509   0.8192   1.0000
   1.000   0.3855   0.00904   0.00339  -0.0495   0.8006   1.0000
   1.250   0.4078   0.00911   0.00337  -0.0482   0.7828   1.0000
   1.500   0.4304   0.00919   0.00336  -0.0469   0.7658   1.0000
   1.750   0.4532   0.00928   0.00338  -0.0456   0.7490   1.0000
   2.000   0.4760   0.00937   0.00343  -0.0445   0.7318   1.0000
   2.250   0.4989   0.00947   0.00348  -0.0433   0.7143   1.0000
   2.500   0.5219   0.00958   0.00355  -0.0421   0.6969   1.0000
   2.750   0.5446   0.00969   0.00362  -0.0409   0.6780   1.0000
   3.000   0.5672   0.00980   0.00368  -0.0396   0.6573   1.0000
   3.250   0.5897   0.00991   0.00375  -0.0383   0.6351   1.0000
   3.500   0.6118   0.01002   0.00380  -0.0369   0.6092   1.0000
   3.750   0.6338   0.01016   0.00388  -0.0354   0.5816   1.0000
   4.000   0.6559   0.01033   0.00399  -0.0341   0.5549   1.0000
   4.250   0.6779   0.01053   0.00412  -0.0328   0.5272   1.0000
   4.500   0.6999   0.01075   0.00429  -0.0315   0.4979   1.0000
   4.750   0.7216   0.01099   0.00451  -0.0302   0.4651   1.0000
   5.000   0.7424   0.01130   0.00471  -0.0287   0.4247   1.0000
   5.250   0.7622   0.01171   0.00497  -0.0272   0.3722   1.0000
   5.500   0.7792   0.01240   0.00533  -0.0253   0.2957   1.0000
   5.750   0.7903   0.01385   0.00603  -0.0228   0.1634   1.0000
   6.000   0.8036   0.01521   0.00700  -0.0206   0.1044   1.0000
   6.250   0.8195   0.01627   0.00792  -0.0186   0.0838   1.0000
   6.500   0.8361   0.01726   0.00887  -0.0167   0.0710   1.0000
   6.750   0.8533   0.01819   0.00980  -0.0148   0.0621   1.0000
   7.000   0.8700   0.01925   0.01092  -0.0129   0.0552   1.0000
   7.250   0.8860   0.02044   0.01208  -0.0110   0.0494   1.0000
   7.500   0.9036   0.02183   0.01354  -0.0092   0.0461   1.0000
   7.750   0.9229   0.02289   0.01469  -0.0077   0.0425   1.0000
   8.000   0.9413   0.02410   0.01589  -0.0063   0.0394   1.0000
   8.250   0.9603   0.02644   0.01835  -0.0050   0.0371   1.0000
   8.500   0.9799   0.02798   0.02015  -0.0035   0.0357   1.0000
   8.750   0.9982   0.02990   0.02232  -0.0019   0.0344   1.0000
   9.000   1.0149   0.03165   0.02429  -0.0002   0.0328   1.0000
   9.250   1.0305   0.03328   0.02607   0.0014   0.0314   1.0000
   9.500   1.0444   0.03528   0.02818   0.0029   0.0301   1.0000
   9.750   1.0539   0.03865   0.03183   0.0049   0.0295   1.0000
  10.000   1.0592   0.04208   0.03560   0.0073   0.0294   1.0000
  10.250   1.0608   0.04547   0.03936   0.0101   0.0294   1.0000
  10.500   1.0604   0.04829   0.04253   0.0131   0.0298   1.0000
  10.750   1.0140   0.05499   0.05012   0.0201   0.0330   1.0000
  11.000   0.9900   0.05883   0.05420   0.0237   0.0340   1.0000
  11.250   0.9672   0.06291   0.05846   0.0252   0.0347   1.0000
  11.500   0.9438   0.06757   0.06330   0.0250   0.0352   1.0000
  11.750   0.9233   0.07272   0.06856   0.0234   0.0360   1.0000
  12.000   0.9019   0.07865   0.07460   0.0205   0.0365   1.0000
  12.250   0.7783   0.07805   0.07431   0.0207   0.0350   1.0000
  12.500   0.7456   0.08763   0.08398   0.0155   0.0356   1.0000
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