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NACA M18 AIRFOIL (m18-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA M18 AIRFOIL (m18-il)
Reynolds number: 200,000
Max Cl/Cd: 72.25 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m18-il-200000-n5.txt
Download as CSV file: xf-m18-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3897   0.08994   0.08635  -0.0231   0.8465   0.0437
  -8.250  -0.3872   0.08684   0.08319  -0.0245   0.8285   0.0446
  -8.000  -0.3879   0.08311   0.07940  -0.0273   0.8124   0.0453
  -7.500  -0.3994   0.07112   0.06713  -0.0362   0.7873   0.0409
  -7.250  -0.3912   0.06835   0.06428  -0.0359   0.7755   0.0395
  -7.000  -0.3863   0.06364   0.05941  -0.0374   0.7658   0.0377
  -6.750  -0.3820   0.05724   0.05275  -0.0395   0.7565   0.0363
  -6.250  -0.3725   0.04082   0.03525  -0.0399   0.7416   0.0346
  -6.000  -0.3597   0.03695   0.03097  -0.0388   0.7338   0.0346
  -5.750  -0.3448   0.03336   0.02694  -0.0376   0.7252   0.0346
  -5.250  -0.3069   0.02876   0.02173  -0.0357   0.7093   0.0354
  -5.000  -0.2846   0.02743   0.02017  -0.0351   0.7018   0.0360
  -4.750  -0.2614   0.02588   0.01836  -0.0345   0.6938   0.0364
  -4.500  -0.2382   0.02409   0.01618  -0.0336   0.6869   0.0365
  -4.250  -0.2134   0.02266   0.01445  -0.0331   0.6800   0.0368
  -4.000  -0.1878   0.02148   0.01300  -0.0326   0.6730   0.0371
  -3.750  -0.1616   0.02048   0.01175  -0.0322   0.6665   0.0375
  -3.500  -0.1348   0.01958   0.01066  -0.0320   0.6593   0.0379
  -3.250  -0.1079   0.01881   0.00969  -0.0317   0.6530   0.0384
  -3.000  -0.0804   0.01811   0.00885  -0.0315   0.6462   0.0389
  -2.750  -0.0531   0.01756   0.00817  -0.0313   0.6398   0.0399
  -2.500  -0.0257   0.01708   0.00756  -0.0311   0.6340   0.0410
  -2.250   0.0018   0.01661   0.00700  -0.0310   0.6271   0.0416
  -2.000   0.0285   0.01604   0.00637  -0.0307   0.6210   0.0423
  -1.750   0.0553   0.01558   0.00592  -0.0305   0.6144   0.0432
  -1.500   0.0821   0.01523   0.00555  -0.0303   0.6077   0.0441
  -1.250   0.1088   0.01495   0.00522  -0.0300   0.6021   0.0453
  -1.000   0.1358   0.01468   0.00495  -0.0298   0.5954   0.0468
  -0.750   0.1626   0.01447   0.00467  -0.0295   0.5893   0.0486
  -0.500   0.1894   0.01425   0.00445  -0.0293   0.5831   0.0514
  -0.250   0.2163   0.01408   0.00429  -0.0291   0.5761   0.0562
   0.000   0.2429   0.01391   0.00411  -0.0288   0.5702   0.0634
   0.250   0.2697   0.01371   0.00399  -0.0286   0.5630   0.0803
   0.500   0.2959   0.01352   0.00389  -0.0283   0.5570   0.1139
   0.750   0.3221   0.01334   0.00384  -0.0281   0.5510   0.1603
   1.000   0.3467   0.01300   0.00382  -0.0276   0.5445   0.2565
   1.500   0.4746   0.01205   0.00472  -0.0416   0.5291   0.9839
   1.750   0.5462   0.01218   0.00469  -0.0510   0.5219   0.9988
   2.000   0.5764   0.01223   0.00470  -0.0516   0.5156   1.0000
   2.250   0.6022   0.01229   0.00468  -0.0513   0.5099   1.0000
   2.500   0.6279   0.01236   0.00470  -0.0511   0.5044   1.0000
   2.750   0.6536   0.01243   0.00474  -0.0508   0.4985   1.0000
   3.000   0.6791   0.01253   0.00477  -0.0504   0.4935   1.0000
   3.250   0.7044   0.01263   0.00484  -0.0501   0.4884   1.0000
   3.500   0.7296   0.01273   0.00493  -0.0497   0.4828   1.0000
   3.750   0.7545   0.01285   0.00499  -0.0493   0.4774   1.0000
   4.000   0.7794   0.01296   0.00511  -0.0488   0.4705   1.0000
   4.250   0.8040   0.01309   0.00520  -0.0483   0.4638   1.0000
   4.500   0.8285   0.01324   0.00532  -0.0479   0.4585   1.0000
   4.750   0.8532   0.01339   0.00550  -0.0474   0.4535   1.0000
   5.000   0.8777   0.01355   0.00567  -0.0469   0.4490   1.0000
   5.250   0.9019   0.01374   0.00582  -0.0464   0.4449   1.0000
   5.500   0.9262   0.01391   0.00606  -0.0459   0.4400   1.0000
   5.750   0.9502   0.01409   0.00628  -0.0453   0.4350   1.0000
   6.000   0.9740   0.01429   0.00647  -0.0447   0.4305   1.0000
   6.250   0.9977   0.01450   0.00673  -0.0441   0.4254   1.0000
   6.500   1.0212   0.01469   0.00699  -0.0434   0.4197   1.0000
   6.750   1.0444   0.01492   0.00722  -0.0428   0.4146   1.0000
   7.000   1.0675   0.01514   0.00751  -0.0421   0.4091   1.0000
   7.250   1.0903   0.01536   0.00781  -0.0413   0.4026   1.0000
   7.500   1.1127   0.01561   0.00805  -0.0405   0.3967   1.0000
   7.750   1.1351   0.01583   0.00841  -0.0397   0.3900   1.0000
   8.000   1.1573   0.01609   0.00874  -0.0389   0.3843   1.0000
   8.250   1.1791   0.01636   0.00908  -0.0380   0.3781   1.0000
   8.500   1.1993   0.01660   0.00936  -0.0368   0.3667   1.0000
   8.750   1.2175   0.01687   0.00965  -0.0354   0.3483   1.0000
   9.000   1.2342   0.01722   0.01000  -0.0337   0.3242   1.0000
   9.250   1.2494   0.01769   0.01042  -0.0319   0.2993   1.0000
   9.500   1.2615   0.01833   0.01096  -0.0297   0.2740   1.0000
   9.750   1.2699   0.01915   0.01166  -0.0270   0.2477   1.0000
  10.000   1.2764   0.02006   0.01247  -0.0241   0.2240   1.0000
  10.250   1.2788   0.02112   0.01345  -0.0207   0.2008   1.0000
  10.500   1.2764   0.02227   0.01451  -0.0167   0.1741   1.0000
  10.750   1.2672   0.02394   0.01601  -0.0125   0.1435   1.0000
  11.000   1.2592   0.02601   0.01795  -0.0095   0.1205   1.0000
  11.250   1.2548   0.02819   0.02006  -0.0074   0.1032   1.0000
  11.500   1.2518   0.03048   0.02231  -0.0058   0.0819   1.0000
  11.750   1.2441   0.03336   0.02508  -0.0045   0.0617   1.0000
  12.000   1.2386   0.03622   0.02790  -0.0035   0.0506   1.0000
  12.250   1.2355   0.03899   0.03069  -0.0029   0.0436   1.0000
  12.500   1.2325   0.04183   0.03359  -0.0023   0.0387   1.0000
  12.750   1.2300   0.04469   0.03651  -0.0019   0.0351   1.0000
  13.000   1.2272   0.04764   0.03954  -0.0016   0.0325   1.0000
  13.250   1.2254   0.05052   0.04251  -0.0014   0.0304   1.0000
  13.500   1.2221   0.05364   0.04569  -0.0013   0.0287   1.0000
  13.750   1.2172   0.05706   0.04918  -0.0014   0.0275   1.0000
  14.000   1.2157   0.06017   0.05241  -0.0015   0.0264   1.0000
  14.250   1.2135   0.06346   0.05581  -0.0018   0.0254   1.0000
  14.500   1.2110   0.06685   0.05930  -0.0022   0.0245   1.0000
  14.750   1.2077   0.07039   0.06293  -0.0026   0.0237   1.0000
  15.000   1.2031   0.07418   0.06679  -0.0032   0.0230   1.0000
  15.250   1.1987   0.07800   0.07069  -0.0039   0.0223   1.0000
  15.500   1.1973   0.08143   0.07423  -0.0045   0.0217   1.0000
  15.750   1.1957   0.08495   0.07785  -0.0051   0.0210   1.0000
  16.000   1.1941   0.08848   0.08148  -0.0059   0.0204   1.0000
  16.250   1.1923   0.09208   0.08516  -0.0066   0.0198   1.0000
  16.500   1.1905   0.09566   0.08881  -0.0074   0.0194   1.0000
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