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NACA M21 AIRFOIL (m21-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA M21 AIRFOIL (m21-il)
Reynolds number: 200,000
Max Cl/Cd: 73.67 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m21-il-200000-n5.txt
Download as CSV file: xf-m21-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2675   0.09443   0.09014  -0.0284   0.6949   0.0424
  -8.000  -0.2680   0.09099   0.08667  -0.0326   0.6889   0.0425
  -7.750  -0.2635   0.08740   0.08302  -0.0363   0.6836   0.0426
  -7.250  -0.2449   0.07966   0.07511  -0.0434   0.6729   0.0427
  -7.000  -0.2342   0.07669   0.07215  -0.0410   0.6674   0.0433
  -6.750  -0.2211   0.07433   0.06976  -0.0406   0.6620   0.0441
  -6.500  -0.2075   0.07158   0.06695  -0.0420   0.6563   0.0450
  -6.250  -0.1932   0.06851   0.06379  -0.0440   0.6513   0.0456
  -6.000  -0.1776   0.06334   0.05841  -0.0483   0.6474   0.0419
  -5.750  -0.1618   0.06039   0.05541  -0.0491   0.6420   0.0409
  -5.500  -0.1430   0.05694   0.05179  -0.0511   0.6373   0.0415
  -5.250  -0.1238   0.05370   0.04836  -0.0525   0.6330   0.0415
  -5.000  -0.1042   0.05075   0.04529  -0.0533   0.6280   0.0409
  -4.750  -0.0835   0.04771   0.04208  -0.0541   0.6230   0.0405
  -4.500  -0.0621   0.04472   0.03889  -0.0547   0.6187   0.0403
  -4.250  -0.0399   0.04182   0.03574  -0.0551   0.6147   0.0403
  -4.000  -0.0164   0.03877   0.03246  -0.0554   0.6098   0.0412
  -3.750   0.0070   0.03551   0.02890  -0.0553   0.6052   0.0418
  -3.500   0.0302   0.03250   0.02555  -0.0549   0.6012   0.0419
  -3.250   0.0536   0.02908   0.02173  -0.0543   0.5972   0.0423
  -3.000   0.0773   0.02570   0.01790  -0.0536   0.5927   0.0430
  -2.750   0.1032   0.02509   0.01718  -0.0535   0.5879   0.0437
  -2.500   0.1294   0.02463   0.01659  -0.0534   0.5837   0.0447
  -2.250   0.1560   0.02353   0.01533  -0.0533   0.5789   0.0461
  -2.000   0.1828   0.02177   0.01323  -0.0529   0.5743   0.0472
  -1.750   0.2101   0.01997   0.01101  -0.0525   0.5701   0.0489
  -1.500   0.2380   0.01865   0.00931  -0.0523   0.5662   0.0505
  -1.250   0.2657   0.01838   0.00906  -0.0524   0.5611   0.0518
  -1.000   0.2934   0.01820   0.00884  -0.0525   0.5564   0.0537
  -0.750   0.3213   0.01778   0.00826  -0.0524   0.5523   0.0562
  -0.500   0.3497   0.01719   0.00747  -0.0524   0.5479   0.0587
  -0.250   0.3775   0.01680   0.00709  -0.0525   0.5431   0.0607
   0.000   0.4052   0.01663   0.00689  -0.0525   0.5387   0.0630
   0.250   0.4329   0.01649   0.00664  -0.0524   0.5349   0.0667
   0.500   0.4608   0.01626   0.00637  -0.0525   0.5301   0.0701
   0.750   0.4881   0.01602   0.00617  -0.0525   0.5254   0.0729
   1.000   0.5155   0.01592   0.00605  -0.0524   0.5214   0.0770
   1.250   0.5428   0.01581   0.00587  -0.0524   0.5175   0.0808
   1.500   0.5697   0.01560   0.00571  -0.0523   0.5126   0.0839
   1.750   0.5965   0.01549   0.00564  -0.0522   0.5081   0.0881
   2.000   0.6233   0.01541   0.00552  -0.0521   0.5043   0.0919
   2.250   0.6501   0.01536   0.00546  -0.0520   0.5002   0.0950
   2.500   0.6763   0.01524   0.00542  -0.0518   0.4954   0.0996
   2.750   0.7028   0.01520   0.00540  -0.0517   0.4910   0.1045
   3.000   0.7293   0.01521   0.00535  -0.0515   0.4874   0.1086
   3.250   0.7555   0.01520   0.00539  -0.0514   0.4831   0.1140
   3.500   0.7819   0.01522   0.00546  -0.0513   0.4784   0.1223
   3.750   0.8081   0.01524   0.00550  -0.0511   0.4742   0.1345
   4.000   0.8336   0.01519   0.00560  -0.0508   0.4705   0.2077
   4.500   0.9720   0.01435   0.00637  -0.0691   0.4589   1.0000
   5.000   1.0205   0.01471   0.00669  -0.0681   0.4504   1.0000
   5.250   1.0445   0.01490   0.00689  -0.0676   0.4460   1.0000
   5.500   1.0683   0.01509   0.00706  -0.0670   0.4422   1.0000
   5.750   1.0921   0.01530   0.00724  -0.0665   0.4383   1.0000
   6.000   1.1155   0.01552   0.00753  -0.0659   0.4335   1.0000
   6.250   1.1387   0.01574   0.00777  -0.0653   0.4290   1.0000
   6.500   1.1619   0.01597   0.00798  -0.0646   0.4254   1.0000
   6.750   1.1849   0.01622   0.00827  -0.0640   0.4214   1.0000
   7.000   1.2074   0.01648   0.00861  -0.0633   0.4167   1.0000
   7.250   1.2299   0.01673   0.00889  -0.0626   0.4124   1.0000
   7.500   1.2524   0.01700   0.00914  -0.0619   0.4088   1.0000
   7.750   1.2742   0.01730   0.00955  -0.0611   0.4045   1.0000
   8.000   1.2956   0.01759   0.00993  -0.0603   0.4000   1.0000
   8.250   1.3169   0.01788   0.01024  -0.0594   0.3954   1.0000
   8.500   1.3371   0.01819   0.01060  -0.0584   0.3894   1.0000
   8.750   1.3560   0.01849   0.01097  -0.0572   0.3817   1.0000
   9.000   1.3741   0.01881   0.01133  -0.0559   0.3740   1.0000
   9.250   1.3911   0.01917   0.01174  -0.0544   0.3655   1.0000
   9.500   1.4070   0.01956   0.01218  -0.0528   0.3571   1.0000
   9.750   1.4215   0.02000   0.01266  -0.0509   0.3485   1.0000
  10.000   1.4346   0.02049   0.01322  -0.0490   0.3392   1.0000
  10.250   1.4443   0.02106   0.01382  -0.0465   0.3290   1.0000
  10.500   1.4498   0.02174   0.01453  -0.0435   0.3183   1.0000
  10.750   1.4527   0.02258   0.01541  -0.0404   0.3065   1.0000
  11.000   1.4553   0.02366   0.01651  -0.0378   0.2938   1.0000
  11.250   1.4552   0.02510   0.01797  -0.0353   0.2776   1.0000
  11.500   1.4515   0.02702   0.01985  -0.0331   0.2582   1.0000
  11.750   1.4437   0.02952   0.02227  -0.0311   0.2340   1.0000
  12.000   1.4289   0.03286   0.02549  -0.0293   0.2056   1.0000
  12.250   1.4099   0.03683   0.02932  -0.0277   0.1774   1.0000
  12.500   1.3891   0.04119   0.03356  -0.0264   0.1508   1.0000
  12.750   1.3641   0.04618   0.03839  -0.0252   0.1214   1.0000
  13.000   1.3362   0.05168   0.04373  -0.0244   0.0917   1.0000
  13.250   1.3103   0.05731   0.04922  -0.0240   0.0652   1.0000
  13.500   1.2894   0.06263   0.05443  -0.0239   0.0450   1.0000
  13.750   1.2772   0.06709   0.05889  -0.0239   0.0356   1.0000
  14.000   1.2694   0.07110   0.06294  -0.0240   0.0310   1.0000
  14.250   1.2630   0.07505   0.06695  -0.0242   0.0282   1.0000
  14.500   1.2588   0.07876   0.07075  -0.0245   0.0263   1.0000
  14.750   1.2546   0.08252   0.07461  -0.0249   0.0248   1.0000
  15.000   1.2495   0.08646   0.07863  -0.0253   0.0236   1.0000
  15.250   1.2432   0.09062   0.08287  -0.0259   0.0226   1.0000
  15.500   1.2401   0.09439   0.08676  -0.0264   0.0218   1.0000
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