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NACA M18 (nacam18-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA M18 (nacam18-il)
Reynolds number: 100,000
Max Cl/Cd: 50.81 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nacam18-il-100000-n5.txt
Download as CSV file: xf-nacam18-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M18                                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3990   0.11301   0.10827  -0.0212   1.0000   0.0698
  -9.250  -0.4033   0.10946   0.10478  -0.0263   1.0000   0.0700
  -9.000  -0.4061   0.10551   0.10089  -0.0312   1.0000   0.0702
  -8.750  -0.3998   0.10069   0.09614  -0.0325   1.0000   0.0705
  -8.500  -0.3816   0.09668   0.09214  -0.0297   1.0000   0.0714
  -8.250  -0.3713   0.09323   0.08872  -0.0301   1.0000   0.0722
  -8.000  -0.3593   0.08951   0.08500  -0.0329   0.9540   0.0732
  -7.750  -0.3489   0.08596   0.08140  -0.0357   0.9235   0.0750
  -7.500  -0.3463   0.08279   0.07816  -0.0374   0.8984   0.0770
  -7.250  -0.3455   0.07950   0.07478  -0.0397   0.8784   0.0795
  -7.000  -0.3529   0.07614   0.07104  -0.0467   0.8593   0.0830
  -6.750  -0.3515   0.06596   0.06062  -0.0483   0.8487   0.0596
  -6.500  -0.3375   0.06395   0.05863  -0.0466   0.8358   0.0574
  -6.000  -0.3253   0.05173   0.04551  -0.0481   0.8152   0.0497
  -5.750  -0.3124   0.04830   0.04183  -0.0476   0.8044   0.0500
  -5.500  -0.2948   0.04730   0.04085  -0.0468   0.7942   0.0512
  -5.250  -0.2783   0.04489   0.03822  -0.0460   0.7850   0.0518
  -4.750  -0.2466   0.03675   0.02884  -0.0435   0.7684   0.0497
  -4.500  -0.2266   0.03443   0.02618  -0.0425   0.7596   0.0497
  -4.250  -0.2055   0.03227   0.02363  -0.0415   0.7520   0.0497
  -4.000  -0.1829   0.03034   0.02130  -0.0406   0.7437   0.0498
  -3.750  -0.1596   0.02864   0.01928  -0.0398   0.7363   0.0501
  -3.500  -0.1351   0.02746   0.01795  -0.0394   0.7286   0.0511
  -3.250  -0.1101   0.02656   0.01691  -0.0389   0.7210   0.0525
  -3.000  -0.0843   0.02555   0.01567  -0.0384   0.7141   0.0538
  -2.750  -0.0577   0.02443   0.01430  -0.0380   0.7066   0.0546
  -2.500  -0.0308   0.02341   0.01301  -0.0375   0.7006   0.0553
  -2.250  -0.0032   0.02252   0.01195  -0.0373   0.6928   0.0561
  -2.000   0.0241   0.02173   0.01097  -0.0370   0.6867   0.0572
  -1.750   0.0516   0.02106   0.01018  -0.0367   0.6797   0.0585
  -1.500   0.0784   0.02043   0.00950  -0.0364   0.6730   0.0602
  -1.250   0.1048   0.02000   0.00907  -0.0361   0.6671   0.0633
  -1.000   0.1316   0.01962   0.00868  -0.0359   0.6599   0.0672
  -0.750   0.1579   0.01921   0.00815  -0.0354   0.6541   0.0705
  -0.500   0.1839   0.01881   0.00780  -0.0350   0.6474   0.0751
  -0.250   0.2104   0.01852   0.00744  -0.0346   0.6409   0.0829
   0.000   0.2372   0.01819   0.00713  -0.0342   0.6356   0.0991
   0.250   0.2641   0.01789   0.00705  -0.0342   0.6283   0.1393
   0.500   0.2906   0.01753   0.00690  -0.0340   0.6225   0.2163
   1.000   0.4602   0.01625   0.00740  -0.0561   0.6069   1.0000
   1.250   0.4852   0.01633   0.00735  -0.0557   0.6011   1.0000
   1.500   0.5103   0.01644   0.00738  -0.0554   0.5940   1.0000
   1.750   0.5351   0.01653   0.00733  -0.0549   0.5884   1.0000
   2.000   0.5600   0.01667   0.00742  -0.0546   0.5815   1.0000
   2.250   0.5847   0.01678   0.00746  -0.0541   0.5751   1.0000
   2.500   0.6093   0.01689   0.00747  -0.0536   0.5696   1.0000
   2.750   0.6337   0.01707   0.00765  -0.0533   0.5622   1.0000
   3.000   0.6582   0.01718   0.00768  -0.0528   0.5565   1.0000
   3.250   0.6824   0.01736   0.00785  -0.0523   0.5497   1.0000
   3.500   0.7065   0.01752   0.00799  -0.0518   0.5432   1.0000
   3.750   0.7308   0.01765   0.00806  -0.0513   0.5377   1.0000
   4.000   0.7544   0.01788   0.00833  -0.0508   0.5301   1.0000
   4.250   0.7785   0.01802   0.00842  -0.0503   0.5244   1.0000
   4.500   0.8019   0.01825   0.00869  -0.0497   0.5174   1.0000
   4.750   0.8255   0.01844   0.00888  -0.0492   0.5109   1.0000
   5.000   0.8491   0.01863   0.00907  -0.0486   0.5050   1.0000
   5.250   0.8720   0.01889   0.00939  -0.0480   0.4977   1.0000
   5.500   0.8958   0.01905   0.00952  -0.0474   0.4923   1.0000
   5.750   0.9181   0.01937   0.00994  -0.0468   0.4850   1.0000
   6.000   0.9412   0.01959   0.01018  -0.0461   0.4789   1.0000
   6.250   0.9639   0.01986   0.01049  -0.0455   0.4727   1.0000
   6.500   0.9860   0.02018   0.01090  -0.0448   0.4658   1.0000
   6.750   1.0096   0.02039   0.01110  -0.0442   0.4607   1.0000
   7.000   1.0304   0.02081   0.01166  -0.0434   0.4535   1.0000
   7.250   1.0529   0.02109   0.01198  -0.0427   0.4474   1.0000
   7.500   1.0744   0.02145   0.01243  -0.0420   0.4410   1.0000
   7.750   1.0954   0.02181   0.01289  -0.0411   0.4338   1.0000
   8.000   1.1177   0.02210   0.01321  -0.0404   0.4276   1.0000
   8.250   1.1369   0.02254   0.01379  -0.0394   0.4192   1.0000
   8.500   1.1584   0.02280   0.01410  -0.0385   0.4119   1.0000
   8.750   1.1765   0.02325   0.01471  -0.0373   0.4030   1.0000
   9.000   1.1967   0.02359   0.01510  -0.0363   0.3954   1.0000
   9.250   1.2140   0.02404   0.01571  -0.0350   0.3862   1.0000
   9.500   1.2317   0.02446   0.01624  -0.0338   0.3775   1.0000
   9.750   1.2486   0.02476   0.01658  -0.0323   0.3662   1.0000
  10.000   1.2594   0.02520   0.01709  -0.0300   0.3499   1.0000
  10.250   1.2661   0.02577   0.01774  -0.0273   0.3297   1.0000
  10.500   1.2703   0.02647   0.01843  -0.0244   0.3087   1.0000
  10.750   1.2722   0.02737   0.01932  -0.0213   0.2892   1.0000
  11.000   1.2702   0.02846   0.02042  -0.0178   0.2717   1.0000
  11.250   1.2677   0.02986   0.02182  -0.0150   0.2535   1.0000
  11.500   1.2641   0.03161   0.02356  -0.0127   0.2342   1.0000
  11.750   1.2588   0.03378   0.02569  -0.0108   0.2133   1.0000
  12.000   1.2511   0.03642   0.02828  -0.0093   0.1886   1.0000
  12.250   1.2395   0.03966   0.03141  -0.0082   0.1608   1.0000
  12.500   1.2244   0.04351   0.03512  -0.0073   0.1374   1.0000
  12.750   1.2091   0.04760   0.03912  -0.0068   0.1202   1.0000
  13.000   1.1950   0.05176   0.04322  -0.0065   0.1056   1.0000
  13.250   1.1824   0.05590   0.04738  -0.0064   0.0907   1.0000
  13.500   1.1701   0.06014   0.05162  -0.0065   0.0767   1.0000
  13.750   1.1571   0.06466   0.05612  -0.0068   0.0674   1.0000
  14.000   1.1454   0.06919   0.06066  -0.0074   0.0607   1.0000
  14.250   1.1348   0.07372   0.06521  -0.0080   0.0559   1.0000
  14.500   1.1258   0.07817   0.06971  -0.0087   0.0518   1.0000
  14.750   1.1155   0.08286   0.07442  -0.0095   0.0490   1.0000
  15.000   1.1109   0.08682   0.07848  -0.0102   0.0459   1.0000
  15.250   1.1060   0.09085   0.08260  -0.0110   0.0435   1.0000
  15.500   1.1009   0.09492   0.08672  -0.0118   0.0417   1.0000
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