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NACA M18 AIRFOIL (m18-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA M18 AIRFOIL (m18-il)
Reynolds number: 100,000
Max Cl/Cd: 50.37 at α=9°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m18-il-100000-n5.txt
Download as CSV file: xf-m18-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M18 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3981   0.11395   0.10920  -0.0205   1.0000   0.0696
  -9.500  -0.4032   0.11052   0.10583  -0.0256   1.0000   0.0699
  -9.250  -0.4060   0.10664   0.10201  -0.0304   1.0000   0.0701
  -9.000  -0.4050   0.10214   0.09758  -0.0336   1.0000   0.0703
  -8.750  -0.3839   0.09774   0.09318  -0.0297   1.0000   0.0712
  -8.500  -0.3728   0.09426   0.08974  -0.0298   1.0000   0.0720
  -8.250  -0.3650   0.09083   0.08635  -0.0316   0.9830   0.0728
  -8.000  -0.3519   0.08704   0.08254  -0.0351   0.9416   0.0744
  -7.750  -0.3458   0.08360   0.07903  -0.0378   0.9132   0.0766
  -7.500  -0.3449   0.08034   0.07568  -0.0400   0.8901   0.0790
  -7.250  -0.3535   0.07695   0.07194  -0.0471   0.8687   0.0829
  -7.000  -0.3514   0.06700   0.06170  -0.0489   0.8563   0.0589
  -6.750  -0.3421   0.06442   0.05913  -0.0476   0.8424   0.0603
  -6.250  -0.3294   0.05225   0.04608  -0.0484   0.8192   0.0498
  -6.000  -0.3154   0.04987   0.04361  -0.0477   0.8074   0.0503
  -5.750  -0.2992   0.04840   0.04206  -0.0468   0.7968   0.0513
  -5.500  -0.2828   0.04607   0.03953  -0.0462   0.7863   0.0520
  -5.250  -0.2674   0.04233   0.03538  -0.0453   0.7772   0.0516
  -4.750  -0.2331   0.03491   0.02673  -0.0425   0.7602   0.0497
  -4.500  -0.2125   0.03273   0.02416  -0.0414   0.7521   0.0497
  -4.250  -0.1901   0.03074   0.02178  -0.0405   0.7435   0.0498
  -4.000  -0.1672   0.02901   0.01974  -0.0397   0.7357   0.0501
  -3.750  -0.1429   0.02777   0.01835  -0.0393   0.7272   0.0510
  -3.500  -0.1182   0.02684   0.01726  -0.0388   0.7196   0.0524
  -3.250  -0.0925   0.02582   0.01601  -0.0384   0.7115   0.0537
  -3.000  -0.0662   0.02467   0.01459  -0.0378   0.7041   0.0545
  -2.750  -0.0392   0.02360   0.01328  -0.0374   0.6966   0.0552
  -2.500  -0.0120   0.02267   0.01213  -0.0371   0.6891   0.0560
  -2.250   0.0154   0.02185   0.01113  -0.0368   0.6821   0.0570
  -2.000   0.0428   0.02114   0.01028  -0.0365   0.6742   0.0582
  -1.750   0.0697   0.02049   0.00951  -0.0361   0.6678   0.0597
  -1.500   0.0963   0.02003   0.00911  -0.0359   0.6597   0.0626
  -1.250   0.1228   0.01963   0.00864  -0.0355   0.6535   0.0663
  -1.000   0.1494   0.01924   0.00817  -0.0352   0.6459   0.0697
  -0.750   0.1752   0.01879   0.00773  -0.0346   0.6390   0.0737
  -0.500   0.2016   0.01848   0.00739  -0.0342   0.6321   0.0804
  -0.250   0.2283   0.01817   0.00709  -0.0339   0.6248   0.0928
   0.000   0.2552   0.01785   0.00685  -0.0335   0.6191   0.1242
   0.250   0.2820   0.01755   0.00679  -0.0335   0.6115   0.1861
   0.750   0.4518   0.01614   0.00728  -0.0556   0.5948   1.0000
   1.000   0.4768   0.01622   0.00720  -0.0551   0.5888   1.0000
   1.250   0.5020   0.01633   0.00721  -0.0547   0.5823   1.0000
   1.500   0.5270   0.01645   0.00724  -0.0543   0.5758   1.0000
   1.750   0.5518   0.01655   0.00719  -0.0537   0.5707   1.0000
   2.000   0.5766   0.01671   0.00734  -0.0534   0.5635   1.0000
   2.250   0.6013   0.01684   0.00738  -0.0529   0.5577   1.0000
   2.500   0.6260   0.01699   0.00746  -0.0524   0.5525   1.0000
   2.750   0.6505   0.01718   0.00765  -0.0519   0.5462   1.0000
   3.000   0.6750   0.01733   0.00772  -0.0513   0.5410   1.0000
   3.250   0.6993   0.01752   0.00790  -0.0508   0.5355   1.0000
   3.500   0.7233   0.01774   0.00812  -0.0503   0.5296   1.0000
   3.750   0.7476   0.01791   0.00824  -0.0497   0.5248   1.0000
   4.000   0.7715   0.01814   0.00849  -0.0491   0.5193   1.0000
   4.250   0.7951   0.01838   0.00875  -0.0485   0.5134   1.0000
   4.500   0.8192   0.01854   0.00886  -0.0479   0.5085   1.0000
   4.750   0.8423   0.01881   0.00920  -0.0472   0.5019   1.0000
   5.000   0.8657   0.01902   0.00941  -0.0465   0.4958   1.0000
   5.250   0.8894   0.01920   0.00956  -0.0458   0.4906   1.0000
   5.500   0.9117   0.01952   0.01000  -0.0450   0.4839   1.0000
   5.750   0.9352   0.01975   0.01023  -0.0443   0.4788   1.0000
   6.000   0.9583   0.02003   0.01054  -0.0436   0.4739   1.0000
   6.250   0.9802   0.02040   0.01102  -0.0428   0.4681   1.0000
   6.500   1.0034   0.02067   0.01133  -0.0420   0.4631   1.0000
   6.750   1.0261   0.02099   0.01170  -0.0413   0.4581   1.0000
   7.000   1.0472   0.02140   0.01224  -0.0403   0.4519   1.0000
   7.250   1.0701   0.02168   0.01258  -0.0396   0.4469   1.0000
   7.500   1.0917   0.02207   0.01306  -0.0387   0.4414   1.0000
   7.750   1.1122   0.02246   0.01357  -0.0376   0.4344   1.0000
   8.000   1.1359   0.02265   0.01375  -0.0369   0.4286   1.0000
   8.250   1.1534   0.02316   0.01448  -0.0355   0.4201   1.0000
   8.500   1.1759   0.02338   0.01473  -0.0346   0.4135   1.0000
   8.750   1.1928   0.02389   0.01543  -0.0331   0.4050   1.0000
   9.000   1.2143   0.02411   0.01569  -0.0320   0.3974   1.0000
   9.250   1.2295   0.02465   0.01645  -0.0303   0.3880   1.0000
   9.500   1.2474   0.02494   0.01683  -0.0288   0.3784   1.0000
   9.750   1.2605   0.02524   0.01722  -0.0266   0.3637   1.0000
  10.000   1.2684   0.02570   0.01778  -0.0239   0.3442   1.0000
  10.250   1.2740   0.02623   0.01834  -0.0209   0.3220   1.0000
  10.500   1.2768   0.02704   0.01916  -0.0178   0.2992   1.0000
  10.750   1.2750   0.02803   0.02010  -0.0141   0.2785   1.0000
  11.000   1.2708   0.02936   0.02138  -0.0107   0.2592   1.0000
  11.250   1.2659   0.03111   0.02308  -0.0080   0.2392   1.0000
  11.500   1.2596   0.03328   0.02521  -0.0059   0.2195   1.0000
  11.750   1.2517   0.03589   0.02777  -0.0042   0.1992   1.0000
  12.000   1.2423   0.03892   0.03076  -0.0030   0.1748   1.0000
  12.250   1.2290   0.04255   0.03431  -0.0022   0.1496   1.0000
  12.500   1.2128   0.04670   0.03834  -0.0017   0.1307   1.0000
  12.750   1.1978   0.05093   0.04250  -0.0014   0.1154   1.0000
  13.000   1.1841   0.05517   0.04673  -0.0014   0.1014   1.0000
  13.250   1.1721   0.05934   0.05090  -0.0014   0.0864   1.0000
  13.500   1.1599   0.06369   0.05523  -0.0017   0.0737   1.0000
  13.750   1.1482   0.06817   0.05969  -0.0022   0.0652   1.0000
  14.000   1.1370   0.07271   0.06421  -0.0028   0.0592   1.0000
  14.250   1.1288   0.07699   0.06854  -0.0034   0.0543   1.0000
  14.500   1.1203   0.08138   0.07295  -0.0041   0.0506   1.0000
  14.750   1.1129   0.08567   0.07728  -0.0049   0.0476   1.0000
  15.000   1.1090   0.08951   0.08123  -0.0056   0.0447   1.0000
  15.250   1.1048   0.09344   0.08522  -0.0063   0.0426   1.0000
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