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NACA M22 AIRFOIL (m22-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA M22 AIRFOIL (m22-il)
Reynolds number: 100,000
Max Cl/Cd: 55.14 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m22-il-100000-n5.txt
Download as CSV file: xf-m22-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M22 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
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.3648   0.10126   0.09683   0.0094   0.7303   0.0235
  -6.750  -0.3568   0.09693   0.09246   0.0097   0.7245   0.0244
  -6.500  -0.3455   0.09350   0.08900   0.0080   0.7182   0.0254
  -6.250  -0.3323   0.09023   0.08568   0.0056   0.7120   0.0265
  -6.000  -0.3176   0.08699   0.08237   0.0030   0.7067   0.0276
  -5.750  -0.3001   0.08369   0.07902  -0.0001   0.7002   0.0288
  -5.500  -0.2805   0.08063   0.07583  -0.0033   0.6950   0.0304
  -5.250  -0.2509   0.07848   0.07355  -0.0088   0.6888   0.0319
  -5.000  -0.2212   0.07628   0.07116  -0.0135   0.6830   0.0324
  -4.750  -0.1568   0.05478   0.04988  -0.0200   0.6647   0.0331
  -4.250  -0.1654   0.06393   0.05857  -0.0179   0.6673   0.0345
  -4.000  -0.1452   0.06063   0.05517  -0.0190   0.6620   0.0362
  -3.750  -0.1202   0.05770   0.05210  -0.0209   0.6562   0.0386
  -3.500  -0.0724   0.05759   0.05150  -0.0252   0.6513   0.0443
  -3.250  -0.0575   0.05249   0.04642  -0.0257   0.6459   0.0460
  -3.000  -0.0377   0.04942   0.04327  -0.0260   0.6405   0.0494
  -2.750   0.0025   0.04888   0.04227  -0.0281   0.6362   0.0570
  -2.500   0.0265   0.04517   0.03847  -0.0291   0.6303   0.0590
  -2.250   0.0464   0.04252   0.03575  -0.0292   0.6252   0.0657
  -2.000   0.0841   0.04150   0.03423  -0.0304   0.6209   0.0719
  -1.750   0.1054   0.03843   0.03115  -0.0308   0.6150   0.0746
  -1.500   0.1330   0.03671   0.02920  -0.0312   0.6102   0.0806
  -1.250   0.1608   0.03496   0.02722  -0.0316   0.6057   0.0895
  -1.000   0.1955   0.03462   0.02646  -0.0321   0.5999   0.0994
  -0.750   0.2194   0.03208   0.02384  -0.0323   0.5955   0.1017
  -0.500   0.2468   0.03061   0.02217  -0.0324   0.5909   0.1052
   0.000   0.3145   0.02680   0.01743  -0.0318   0.5813   0.0561
   0.250   0.3432   0.02564   0.01595  -0.0317   0.5771   0.0589
   0.500   0.3706   0.02487   0.01517  -0.0322   0.5712   0.0626
   0.750   0.4016   0.02399   0.01378  -0.0317   0.5669   0.0577
   1.000   0.4295   0.02296   0.01258  -0.0317   0.5628   0.0566
   1.250   0.4583   0.02221   0.01172  -0.0320   0.5571   0.0556
   1.500   0.4866   0.02152   0.01088  -0.0319   0.5526   0.0547
   1.750   0.5149   0.02093   0.01014  -0.0318   0.5487   0.0540
   2.000   0.5438   0.02049   0.00965  -0.0322   0.5430   0.0534
   2.250   0.5732   0.02007   0.00913  -0.0324   0.5384   0.0531
   2.500   0.6026   0.01970   0.00863  -0.0325   0.5346   0.0532
   2.750   0.6302   0.01954   0.00846  -0.0327   0.5288   0.0536
   3.000   0.6564   0.01939   0.00824  -0.0324   0.5244   0.0545
   3.250   0.6823   0.01927   0.00799  -0.0319   0.5208   0.0560
   3.500   0.7093   0.01936   0.00811  -0.0321   0.5150   0.0587
   3.750   0.7359   0.01941   0.00818  -0.0320   0.5104   0.0652
   4.000   0.7623   0.01940   0.00819  -0.0317   0.5069   0.0894
   4.500   0.8507   0.01855   0.00901  -0.0396   0.4955   1.0000
   4.750   0.8759   0.01874   0.00914  -0.0391   0.4921   1.0000
   5.000   0.9018   0.01916   0.00968  -0.0392   0.4865   1.0000
   5.250   0.9272   0.01945   0.01004  -0.0390   0.4818   1.0000
   5.500   0.9524   0.01966   0.01030  -0.0386   0.4781   1.0000
   5.750   0.9776   0.01983   0.01062  -0.0384   0.4680   1.0000
   6.000   1.0021   0.01934   0.01008  -0.0375   0.4493   1.0000
   6.250   1.0272   0.01951   0.01042  -0.0373   0.4374   1.0000
   6.500   1.0513   0.01927   0.01020  -0.0367   0.4026   1.0000
   6.750   1.0752   0.01950   0.01047  -0.0364   0.3670   1.0000
   7.000   1.0881   0.02154   0.01149  -0.0364   0.2080   1.0000
   7.250   1.0825   0.02632   0.01511  -0.0361   0.0342   1.0000
   7.500   1.0963   0.02781   0.01672  -0.0352   0.0290   1.0000
   7.750   1.1077   0.02940   0.01852  -0.0344   0.0256   1.0000
   8.000   1.1131   0.03147   0.02079  -0.0334   0.0230   1.0000
   8.500   1.1100   0.03653   0.02628  -0.0316   0.0215   1.0000
   8.750   1.1078   0.03927   0.02921  -0.0309   0.0212   1.0000
   9.000   1.1050   0.04223   0.03234  -0.0305   0.0209   1.0000
   9.250   1.1017   0.04532   0.03558  -0.0301   0.0206   1.0000
   9.500   1.0986   0.04840   0.03882  -0.0297   0.0202   1.0000
   9.750   1.0967   0.05134   0.04188  -0.0292   0.0197   1.0000
  10.000   1.0965   0.05399   0.04464  -0.0286   0.0189   1.0000
  10.250   1.0987   0.05623   0.04696  -0.0275   0.0179   1.0000
  10.500   1.1049   0.05783   0.04861  -0.0259   0.0170   1.0000
  10.750   1.1182   0.05848   0.04925  -0.0232   0.0166   1.0000
  11.000   1.1395   0.05856   0.04939  -0.0199   0.0162   1.0000
  11.250   1.1667   0.05875   0.04963  -0.0164   0.0159   1.0000
  11.500   1.1933   0.05976   0.05077  -0.0136   0.0157   1.0000
  11.750   1.2121   0.06171   0.05287  -0.0118   0.0149   1.0000
  12.000   1.2239   0.06440   0.05572  -0.0106   0.0141   1.0000
  12.250   1.2344   0.06772   0.05923  -0.0094   0.0135   1.0000
  12.500   1.2391   0.07125   0.06300  -0.0086   0.0133   1.0000
  12.750   1.2386   0.07472   0.06673  -0.0083   0.0134   1.0000
  13.000   1.2351   0.07836   0.07062  -0.0081   0.0135   1.0000
  13.250   1.2293   0.08220   0.07472  -0.0083   0.0136   1.0000
  13.500   1.2213   0.08631   0.07908  -0.0088   0.0137   1.0000
  13.750   1.2114   0.09070   0.08372  -0.0096   0.0139   1.0000
  14.000   1.1998   0.09539   0.08866  -0.0108   0.0141   1.0000
  14.250   1.1869   0.10042   0.09392  -0.0124   0.0143   1.0000
  14.500   1.1709   0.10595   0.09970  -0.0146   0.0145   1.0000
  14.750   1.1546   0.11198   0.10597  -0.0174   0.0147   1.0000
  15.000   1.1384   0.11848   0.11269  -0.0207   0.0149   1.0000
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