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NACA M21 AIRFOIL (m21-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA M21 AIRFOIL (m21-il)
Reynolds number: 100,000
Max Cl/Cd: 48.52 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m21-il-100000-n5.txt
Download as CSV file: xf-m21-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M21 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2654   0.11119   0.10624  -0.0297   0.7941   0.0587
  -9.000  -0.2659   0.10867   0.10369  -0.0331   0.7849   0.0589
  -8.750  -0.2666   0.10591   0.10091  -0.0374   0.7762   0.0591
  -8.500  -0.2505   0.10084   0.09580  -0.0344   0.7686   0.0598
  -8.250  -0.2371   0.09733   0.09223  -0.0328   0.7611   0.0611
  -8.000  -0.2293   0.09436   0.08924  -0.0337   0.7532   0.0624
  -7.750  -0.2237   0.09143   0.08626  -0.0353   0.7464   0.0634
  -7.500  -0.2194   0.08858   0.08339  -0.0373   0.7387   0.0645
  -7.250  -0.2139   0.08575   0.08049  -0.0394   0.7326   0.0659
  -7.000  -0.2056   0.08290   0.07758  -0.0431   0.7257   0.0677
  -6.750  -0.1948   0.08058   0.07508  -0.0494   0.7193   0.0692
  -6.500  -0.1807   0.07824   0.07247  -0.0539   0.7140   0.0697
  -6.250  -0.1690   0.07372   0.06799  -0.0537   0.7073   0.0702
  -6.000  -0.1567   0.07023   0.06449  -0.0528   0.7015   0.0711
  -5.750  -0.1423   0.06729   0.06146  -0.0530   0.6961   0.0719
  -5.500  -0.1261   0.06451   0.05861  -0.0539   0.6897   0.0729
  -5.250  -0.1090   0.06182   0.05579  -0.0547   0.6844   0.0739
  -5.000  -0.0905   0.05918   0.05300  -0.0558   0.6792   0.0749
  -4.750  -0.0706   0.05661   0.05031  -0.0569   0.6731   0.0763
  -4.500  -0.0389   0.05569   0.04876  -0.0597   0.6680   0.0819
  -4.250  -0.0178   0.05315   0.04598  -0.0600   0.6633   0.0820
  -3.750   0.0222   0.04322   0.03553  -0.0599   0.6532   0.0590
  -3.500   0.0437   0.04102   0.03312  -0.0596   0.6490   0.0587
  -3.250   0.0675   0.03864   0.03046  -0.0595   0.6432   0.0594
  -3.000   0.0890   0.03766   0.02952  -0.0594   0.6377   0.0611
  -2.750   0.1128   0.03623   0.02788  -0.0591   0.6333   0.0625
  -2.500   0.1380   0.03430   0.02568  -0.0588   0.6281   0.0625
  -2.250   0.1635   0.03245   0.02353  -0.0585   0.6228   0.0624
  -2.000   0.1894   0.03082   0.02159  -0.0580   0.6184   0.0627
  -1.750   0.2157   0.02940   0.01986  -0.0576   0.6140   0.0635
  -1.500   0.2424   0.02830   0.01852  -0.0574   0.6083   0.0660
  -1.250   0.2700   0.02709   0.01689  -0.0570   0.6036   0.0687
  -1.000   0.2977   0.02592   0.01534  -0.0566   0.5998   0.0699
  -0.750   0.3244   0.02513   0.01450  -0.0566   0.5942   0.0715
  -0.500   0.3514   0.02456   0.01385  -0.0566   0.5890   0.0737
  -0.250   0.3790   0.02405   0.01315  -0.0564   0.5849   0.0781
   0.000   0.4071   0.02354   0.01238  -0.0562   0.5801   0.0817
   0.250   0.4344   0.02295   0.01179  -0.0563   0.5747   0.0843
   0.500   0.4617   0.02260   0.01140  -0.0562   0.5702   0.0892
   0.750   0.4898   0.02225   0.01086  -0.0561   0.5665   0.0941
   1.000   0.5169   0.02193   0.01060  -0.0562   0.5607   0.0976
   1.250   0.5438   0.02169   0.01037  -0.0562   0.5559   0.1035
   1.500   0.5719   0.02142   0.01000  -0.0560   0.5520   0.1084
   1.750   0.6000   0.02122   0.00986  -0.0562   0.5471   0.1128
   2.000   0.6271   0.02116   0.00983  -0.0563   0.5419   0.1199
   2.250   0.6542   0.02105   0.00964  -0.0561   0.5377   0.1255
   2.500   0.6807   0.02094   0.00948  -0.0559   0.5340   0.1315
   2.750   0.7052   0.02109   0.00969  -0.0556   0.5282   0.1407
   3.000   0.7306   0.02112   0.00974  -0.0553   0.5237   0.1531
   3.500   0.8584   0.01988   0.01027  -0.0707   0.5128   1.0000
   3.750   0.8819   0.02013   0.01044  -0.0701   0.5082   1.0000
   4.000   0.9062   0.02030   0.01051  -0.0694   0.5044   1.0000
   4.250   0.9294   0.02060   0.01077  -0.0688   0.5001   1.0000
   4.500   0.9514   0.02097   0.01117  -0.0681   0.4947   1.0000
   4.750   0.9748   0.02120   0.01136  -0.0674   0.4905   1.0000
   5.000   0.9993   0.02137   0.01145  -0.0668   0.4871   1.0000
   5.250   1.0198   0.02187   0.01203  -0.0659   0.4819   1.0000
   5.500   1.0415   0.02223   0.01243  -0.0652   0.4770   1.0000
   5.750   1.0652   0.02244   0.01261  -0.0645   0.4732   1.0000
   6.000   1.0878   0.02276   0.01292  -0.0638   0.4692   1.0000
   6.250   1.1068   0.02332   0.01361  -0.0627   0.4640   1.0000
   6.500   1.1286   0.02366   0.01398  -0.0619   0.4597   1.0000
   6.750   1.1527   0.02386   0.01415  -0.0614   0.4562   1.0000
   7.000   1.1710   0.02444   0.01484  -0.0602   0.4513   1.0000
   7.250   1.1896   0.02498   0.01549  -0.0591   0.4464   1.0000
   7.500   1.2116   0.02531   0.01585  -0.0583   0.4426   1.0000
   7.750   1.2367   0.02549   0.01601  -0.0579   0.4395   1.0000
   8.000   1.2484   0.02639   0.01713  -0.0560   0.4336   1.0000
   8.250   1.2668   0.02691   0.01774  -0.0549   0.4291   1.0000
   8.500   1.2899   0.02719   0.01805  -0.0542   0.4257   1.0000
   8.750   1.3072   0.02779   0.01876  -0.0530   0.4214   1.0000
   9.000   1.3182   0.02869   0.01983  -0.0511   0.4161   1.0000
   9.250   1.3375   0.02913   0.02037  -0.0500   0.4120   1.0000
   9.500   1.3630   0.02931   0.02058  -0.0497   0.4088   1.0000
   9.750   1.3658   0.03059   0.02208  -0.0469   0.4031   1.0000
  10.000   1.3784   0.03121   0.02282  -0.0452   0.3975   1.0000
  10.250   1.3996   0.03121   0.02286  -0.0441   0.3912   1.0000
  10.500   1.3940   0.03249   0.02431  -0.0403   0.3835   1.0000
  10.750   1.4070   0.03257   0.02440  -0.0383   0.3753   1.0000
  11.000   1.3967   0.03424   0.02622  -0.0346   0.3674   1.0000
  11.250   1.4028   0.03504   0.02707  -0.0326   0.3590   1.0000
  11.500   1.3962   0.03705   0.02920  -0.0304   0.3508   1.0000
  11.750   1.3940   0.03888   0.03113  -0.0287   0.3422   1.0000
  12.000   1.3959   0.04042   0.03274  -0.0273   0.3324   1.0000
  12.250   1.3786   0.04421   0.03670  -0.0260   0.3240   1.0000
  12.500   1.3775   0.04634   0.03887  -0.0250   0.3136   1.0000
  12.750   1.3633   0.05017   0.04284  -0.0243   0.3043   1.0000
  13.000   1.3487   0.05424   0.04702  -0.0238   0.2945   1.0000
  13.250   1.3406   0.05756   0.05039  -0.0233   0.2830   1.0000
  13.500   1.3303   0.06125   0.05413  -0.0230   0.2703   1.0000
  13.750   1.3126   0.06625   0.05923  -0.0231   0.2585   1.0000
  14.000   1.3003   0.07056   0.06356  -0.0233   0.2424   1.0000
  14.250   1.2848   0.07554   0.06856  -0.0237   0.2241   1.0000
  14.500   1.2738   0.07978   0.07266  -0.0239   0.1959   1.0000
  14.750   1.2594   0.08450   0.07713  -0.0242   0.1632   1.0000
  15.000   1.2404   0.09013   0.08255  -0.0250   0.1334   1.0000
  15.250   1.2194   0.09628   0.08851  -0.0260   0.1062   1.0000
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