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NACA M20 AIRFOIL (m20-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA M20 AIRFOIL (m20-il)
Reynolds number: 100,000
Max Cl/Cd: 56.31 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m20-il-100000-n5.txt
Download as CSV file: xf-m20-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M20 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3218   0.10931   0.10493  -0.0091   0.8487   0.0327
  -8.250  -0.3160   0.10633   0.10191  -0.0098   0.8348   0.0334
  -8.000  -0.3100   0.10340   0.09894  -0.0108   0.8222   0.0343
  -7.750  -0.3038   0.10054   0.09604  -0.0120   0.8109   0.0358
  -7.500  -0.2978   0.09778   0.09324  -0.0136   0.8008   0.0377
  -7.250  -0.2917   0.09534   0.09077  -0.0166   0.7903   0.0398
  -7.000  -0.2793   0.09362   0.08898  -0.0232   0.7808   0.0413
  -6.750  -0.2636   0.09149   0.08674  -0.0291   0.7723   0.0417
  -6.500  -0.2450   0.08875   0.08389  -0.0340   0.7637   0.0419
  -6.250  -0.2266   0.08570   0.08067  -0.0374   0.7565   0.0420
  -6.000  -0.2239   0.07923   0.07429  -0.0345   0.7489   0.0430
  -5.750  -0.2149   0.07552   0.07055  -0.0329   0.7420   0.0449
  -5.500  -0.1986   0.07249   0.06746  -0.0345   0.7342   0.0476
  -5.250  -0.1789   0.06952   0.06436  -0.0372   0.7275   0.0504
  -5.000  -0.1393   0.06825   0.06275  -0.0452   0.7198   0.0543
  -4.500  -0.1077   0.06022   0.05458  -0.0464   0.7069   0.0565
  -4.250  -0.0903   0.05739   0.05169  -0.0466   0.7001   0.0597
  -4.000  -0.0651   0.05491   0.04901  -0.0485   0.6940   0.0637
  -3.750  -0.0181   0.05499   0.04849  -0.0533   0.6867   0.0676
  -3.500  -0.0046   0.05003   0.04356  -0.0532   0.6815   0.0688
  -3.250   0.0123   0.04705   0.04059  -0.0531   0.6745   0.0716
  -3.000   0.0478   0.04657   0.03968  -0.0549   0.6683   0.0813
  -2.750   0.0763   0.04423   0.03705  -0.0559   0.6623   0.0825
  -2.500   0.0961   0.04091   0.03372  -0.0561   0.6560   0.0839
  -2.250   0.1193   0.03870   0.03136  -0.0561   0.6510   0.0858
  -2.000   0.1460   0.03687   0.02937  -0.0567   0.6440   0.0884
  -1.750   0.1790   0.03598   0.02801  -0.0573   0.6384   0.0976
  -1.500   0.2100   0.03250   0.02413  -0.0572   0.6333   0.0692
  -1.250   0.2363   0.03056   0.02206  -0.0574   0.6270   0.0614
  -1.000   0.2696   0.02850   0.01930  -0.0568   0.6223   0.0544
  -0.750   0.2968   0.02697   0.01759  -0.0570   0.6162   0.0536
  -0.500   0.3246   0.02566   0.01604  -0.0570   0.6105   0.0530
   0.000   0.3812   0.02348   0.01333  -0.0568   0.5995   0.0529
   0.250   0.4097   0.02272   0.01226  -0.0566   0.5943   0.0549
   0.500   0.4371   0.02191   0.01133  -0.0566   0.5893   0.0567
   0.750   0.4654   0.02123   0.01050  -0.0566   0.5832   0.0568
   1.000   0.4932   0.02062   0.00974  -0.0564   0.5785   0.0570
   1.250   0.5211   0.02013   0.00918  -0.0564   0.5735   0.0576
   1.500   0.5488   0.01974   0.00876  -0.0564   0.5677   0.0585
   1.750   0.5769   0.01937   0.00831  -0.0562   0.5631   0.0599
   2.000   0.6051   0.01916   0.00804  -0.0563   0.5579   0.0620
   2.250   0.6320   0.01903   0.00785  -0.0562   0.5526   0.0649
   2.500   0.6585   0.01890   0.00763  -0.0559   0.5483   0.0694
   2.750   0.6851   0.01891   0.00766  -0.0558   0.5433   0.0825
   3.000   0.7115   0.01887   0.00770  -0.0556   0.5380   0.1121
   3.250   0.7675   0.01730   0.00777  -0.0618   0.5333   1.0000
   3.500   0.7930   0.01756   0.00794  -0.0615   0.5286   1.0000
   3.750   0.8184   0.01783   0.00817  -0.0612   0.5233   1.0000
   4.000   0.8439   0.01804   0.00831  -0.0608   0.5192   1.0000
   4.250   0.8693   0.01831   0.00854  -0.0605   0.5150   1.0000
   4.500   0.8944   0.01866   0.00893  -0.0603   0.5099   1.0000
   4.750   0.9197   0.01892   0.00919  -0.0600   0.5056   1.0000
   5.250   0.9699   0.01958   0.00994  -0.0595   0.4967   1.0000
   5.500   0.9949   0.01992   0.01033  -0.0592   0.4922   1.0000
   5.750   1.0204   0.02017   0.01061  -0.0589   0.4886   1.0000
   6.000   1.0448   0.02061   0.01117  -0.0587   0.4838   1.0000
   6.250   1.0692   0.02104   0.01173  -0.0584   0.4790   1.0000
   6.500   1.0943   0.02134   0.01213  -0.0581   0.4750   1.0000
   6.750   1.1190   0.02171   0.01262  -0.0578   0.4705   1.0000
   7.000   1.1424   0.02211   0.01320  -0.0574   0.4635   1.0000
   7.250   1.1658   0.02181   0.01294  -0.0565   0.4477   1.0000
   7.500   1.1883   0.02148   0.01262  -0.0553   0.4275   1.0000
   7.750   1.2085   0.02158   0.01283  -0.0543   0.4039   1.0000
   8.000   1.2281   0.02181   0.01314  -0.0533   0.3777   1.0000
   8.250   1.2440   0.02233   0.01360  -0.0519   0.3327   1.0000
   8.500   1.2475   0.02394   0.01464  -0.0494   0.2395   1.0000
   8.750   1.2308   0.02741   0.01732  -0.0458   0.1409   1.0000
   9.000   1.2070   0.03104   0.02046  -0.0418   0.0653   1.0000
   9.250   1.1944   0.03420   0.02350  -0.0397   0.0433   1.0000
   9.500   1.1903   0.03700   0.02637  -0.0386   0.0382   1.0000
   9.750   1.1891   0.03969   0.02919  -0.0378   0.0354   1.0000
  10.000   1.1877   0.04250   0.03216  -0.0371   0.0331   1.0000
  10.250   1.1845   0.04559   0.03540  -0.0366   0.0311   1.0000
  10.500   1.1787   0.04903   0.03898  -0.0362   0.0295   1.0000
  10.750   1.1708   0.05282   0.04291  -0.0360   0.0282   1.0000
  11.000   1.1675   0.05612   0.04637  -0.0358   0.0275   1.0000
  11.250   1.1638   0.05952   0.04993  -0.0356   0.0269   1.0000
  11.500   1.1598   0.06296   0.05353  -0.0355   0.0263   1.0000
  11.750   1.1562   0.06636   0.05707  -0.0353   0.0258   1.0000
  12.000   1.1538   0.06962   0.06047  -0.0351   0.0251   1.0000
  12.250   1.1533   0.07261   0.06358  -0.0348   0.0242   1.0000
  12.500   1.1547   0.07530   0.06639  -0.0344   0.0231   1.0000
  12.750   1.1580   0.07761   0.06874  -0.0337   0.0219   1.0000
  13.000   1.1645   0.07920   0.07033  -0.0324   0.0209   1.0000
  13.250   1.1811   0.07893   0.06998  -0.0292   0.0200   1.0000
  13.500   1.2132   0.07711   0.06807  -0.0242   0.0192   1.0000
  13.750   1.2275   0.07855   0.06967  -0.0228   0.0188   1.0000
  14.000   1.2366   0.08069   0.07202  -0.0220   0.0182   1.0000
  14.250   1.2434   0.08317   0.07475  -0.0215   0.0175   1.0000
  14.500   1.2489   0.08589   0.07769  -0.0211   0.0169   1.0000
  14.750   1.2538   0.08882   0.08083  -0.0206   0.0164   1.0000
  15.000   1.2560   0.09218   0.08443  -0.0205   0.0163   1.0000
  15.250   1.2543   0.09605   0.08854  -0.0208   0.0161   1.0000
  15.500   1.2498   0.10035   0.09309  -0.0215   0.0160   1.0000
  15.750   1.2430   0.10506   0.09803  -0.0227   0.0160   1.0000
  16.000   1.2342   0.11015   0.10337  -0.0243   0.0160   1.0000
  16.250   1.2238   0.11562   0.10908  -0.0264   0.0160   1.0000
  16.500   1.2123   0.12149   0.11518  -0.0290   0.0160   1.0000
  16.750   1.1998   0.12777   0.12168  -0.0321   0.0161   1.0000
  17.000   1.1864   0.13451   0.12863  -0.0357   0.0161   1.0000
  17.250   1.1724   0.14174   0.13606  -0.0398   0.0162   1.0000
  17.500   1.1578   0.14950   0.14401  -0.0445   0.0164   1.0000
  17.750   1.1428   0.15790   0.15258  -0.0498   0.0165   1.0000
  18.000   1.1274   0.16705   0.16189  -0.0558   0.0167   1.0000
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