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NACA M18 (nacam18-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA M18 (nacam18-il)
Reynolds number: 500,000
Max Cl/Cd: 102.61 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nacam18-il-500000.txt
Download as CSV file: xf-nacam18-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4115   0.10518   0.10307  -0.0101   1.0000   0.0293
  -9.250  -0.4057   0.10195   0.09981  -0.0118   0.9339   0.0298
  -9.000  -0.4065   0.09913   0.09687  -0.0118   0.8950   0.0304
  -8.750  -0.3344   0.08140   0.07893  -0.0288   0.8164   0.0334
  -8.500  -0.3300   0.07819   0.07567  -0.0279   0.8031   0.0337
  -8.250  -0.3257   0.07524   0.07266  -0.0279   0.7908   0.0339
  -8.000  -0.4379   0.07668   0.07405  -0.0326   0.8179   0.0334
  -7.750  -0.4327   0.07379   0.07109  -0.0321   0.8042   0.0337
  -7.500  -0.4245   0.07121   0.06843  -0.0322   0.7910   0.0340
  -7.250  -0.4151   0.06858   0.06571  -0.0326   0.7785   0.0343
  -7.000  -0.4046   0.06578   0.06283  -0.0333   0.7664   0.0347
  -6.750  -0.3934   0.06281   0.05976  -0.0342   0.7556   0.0353
  -6.500  -0.3814   0.05955   0.05636  -0.0353   0.7456   0.0361
  -6.250  -0.3415   0.03665   0.03319  -0.0409   0.7212   0.0399
  -6.000  -0.3280   0.03440   0.03086  -0.0403   0.7132   0.0403
  -5.750  -0.3122   0.03247   0.02887  -0.0398   0.7053   0.0408
  -5.500  -0.2962   0.03036   0.02666  -0.0393   0.6982   0.0415
  -5.250  -0.2799   0.02787   0.02405  -0.0389   0.6918   0.0427
  -5.000  -0.2741   0.02083   0.01634  -0.0372   0.6874   0.0475
  -4.750  -0.2546   0.01923   0.01468  -0.0367   0.6811   0.0480
  -4.500  -0.2341   0.01786   0.01324  -0.0362   0.6747   0.0487
  -4.250  -0.2131   0.01651   0.01180  -0.0357   0.6686   0.0497
  -4.000  -0.1922   0.01506   0.01016  -0.0349   0.6632   0.0516
  -3.750  -0.1746   0.01235   0.00694  -0.0333   0.6584   0.0569
  -3.500  -0.1662   0.01918   0.01230  -0.0292   0.6622   0.0396
  -3.250  -0.1400   0.01751   0.01048  -0.0289   0.6562   0.0390
  -3.000  -0.1132   0.01634   0.00912  -0.0286   0.6504   0.0388
  -2.750  -0.0858   0.01549   0.00809  -0.0283   0.6451   0.0389
  -2.500  -0.0579   0.01487   0.00737  -0.0282   0.6394   0.0391
  -2.250  -0.0302   0.01419   0.00657  -0.0280   0.6337   0.0396
  -2.000  -0.0029   0.01336   0.00565  -0.0278   0.6285   0.0401
  -1.750   0.0245   0.01275   0.00503  -0.0276   0.6230   0.0406
  -1.500   0.0517   0.01233   0.00458  -0.0274   0.6177   0.0414
  -1.250   0.0788   0.01203   0.00424  -0.0272   0.6125   0.0422
  -1.000   0.1063   0.01172   0.00395  -0.0271   0.6068   0.0431
  -0.750   0.1335   0.01147   0.00367  -0.0269   0.6014   0.0442
  -0.500   0.1608   0.01130   0.00344  -0.0267   0.5963   0.0454
  -0.250   0.1884   0.01109   0.00324  -0.0266   0.5906   0.0470
   0.000   0.2154   0.01083   0.00299  -0.0264   0.5850   0.0502
   0.250   0.2429   0.01073   0.00285  -0.0263   0.5798   0.0537
   0.500   0.2705   0.01054   0.00272  -0.0263   0.5739   0.0616
   0.750   0.2970   0.01025   0.00261  -0.0260   0.5682   0.1129
   1.000   0.3232   0.01000   0.00259  -0.0258   0.5628   0.1922
   1.250   0.3417   0.00889   0.00251  -0.0245   0.5572   0.5324
   1.500   0.3729   0.00804   0.00290  -0.0244   0.5513   0.9483
   1.750   0.4189   0.00840   0.00320  -0.0279   0.5447   0.9713
   2.000   0.4794   0.00874   0.00346  -0.0348   0.5370   0.9831
   2.250   0.5545   0.00903   0.00365  -0.0450   0.5289   0.9941
   2.500   0.6134   0.00905   0.00360  -0.0519   0.5205   1.0000
   2.750   0.6397   0.00908   0.00358  -0.0519   0.5141   1.0000
   3.000   0.6660   0.00909   0.00357  -0.0518   0.5072   1.0000
   3.500   0.7184   0.00917   0.00359  -0.0516   0.4944   1.0000
   3.750   0.7445   0.00923   0.00361  -0.0515   0.4880   1.0000
   4.000   0.7706   0.00930   0.00366  -0.0514   0.4818   1.0000
   4.250   0.7966   0.00935   0.00370  -0.0514   0.4755   1.0000
   4.750   0.8484   0.00951   0.00384  -0.0512   0.4635   1.0000
   5.000   0.8740   0.00961   0.00391  -0.0510   0.4567   1.0000
   5.250   0.8996   0.00971   0.00400  -0.0509   0.4498   1.0000
   5.500   0.9251   0.00980   0.00410  -0.0507   0.4429   1.0000
   5.750   0.9501   0.00995   0.00422  -0.0505   0.4368   1.0000
   6.000   0.9752   0.01004   0.00435  -0.0503   0.4301   1.0000
   6.250   0.9996   0.01021   0.00448  -0.0500   0.4236   1.0000
   6.500   1.0244   0.01031   0.00464  -0.0497   0.4169   1.0000
   6.750   1.0486   0.01047   0.00480  -0.0494   0.4100   1.0000
   7.000   1.0728   0.01062   0.00497  -0.0490   0.4030   1.0000
   7.250   1.0965   0.01079   0.00514  -0.0486   0.3940   1.0000
   7.500   1.1202   0.01094   0.00532  -0.0482   0.3842   1.0000
   7.750   1.1431   0.01114   0.00550  -0.0477   0.3718   1.0000
   8.000   1.1655   0.01137   0.00570  -0.0471   0.3583   1.0000
   8.250   1.1874   0.01163   0.00594  -0.0464   0.3453   1.0000
   8.500   1.2093   0.01188   0.00619  -0.0458   0.3316   1.0000
   8.750   1.2304   0.01218   0.00647  -0.0450   0.3166   1.0000
   9.000   1.2503   0.01255   0.00681  -0.0440   0.2993   1.0000
   9.250   1.2694   0.01297   0.00717  -0.0430   0.2799   1.0000
   9.500   1.2860   0.01352   0.00763  -0.0415   0.2568   1.0000
   9.750   1.3006   0.01417   0.00817  -0.0398   0.2306   1.0000
  10.000   1.3102   0.01508   0.00889  -0.0374   0.1960   1.0000
  10.250   1.3079   0.01657   0.01002  -0.0332   0.1382   1.0000
  10.500   1.3020   0.01805   0.01126  -0.0284   0.1030   1.0000
  10.750   1.2883   0.01950   0.01252  -0.0224   0.0691   1.0000
  11.000   1.2761   0.02134   0.01421  -0.0177   0.0469   1.0000
  11.250   1.2747   0.02308   0.01593  -0.0153   0.0373   1.0000
  11.500   1.2770   0.02482   0.01769  -0.0137   0.0328   1.0000
  11.750   1.2813   0.02655   0.01947  -0.0126   0.0301   1.0000
  12.000   1.2820   0.02875   0.02172  -0.0115   0.0281   1.0000
  12.250   1.2882   0.03054   0.02361  -0.0109   0.0268   1.0000
  12.500   1.2923   0.03260   0.02574  -0.0104   0.0256   1.0000
  12.750   1.2936   0.03499   0.02819  -0.0099   0.0245   1.0000
  13.000   1.2894   0.03800   0.03128  -0.0095   0.0236   1.0000
  13.250   1.2892   0.04066   0.03402  -0.0092   0.0230   1.0000
  13.500   1.2911   0.04312   0.03658  -0.0090   0.0223   1.0000
  13.750   1.2911   0.04582   0.03937  -0.0088   0.0217   1.0000
  14.000   1.2898   0.04867   0.04230  -0.0087   0.0212   1.0000
  14.250   1.2878   0.05169   0.04538  -0.0087   0.0207   1.0000
  14.500   1.2849   0.05490   0.04867  -0.0088   0.0203   1.0000
  14.750   1.2799   0.05841   0.05224  -0.0090   0.0199   1.0000
  15.000   1.2724   0.06226   0.05616  -0.0092   0.0195   1.0000
  15.250   1.2662   0.06598   0.05995  -0.0094   0.0191   1.0000
  15.500   1.2671   0.06894   0.06300  -0.0097   0.0189   1.0000
  15.750   1.2674   0.07202   0.06616  -0.0101   0.0185   1.0000
  16.000   1.2679   0.07508   0.06931  -0.0106   0.0182   1.0000
  16.250   1.2683   0.07820   0.07251  -0.0111   0.0178   1.0000
  16.500   1.2686   0.08132   0.07569  -0.0116   0.0174   1.0000
  16.750   1.2692   0.08442   0.07886  -0.0122   0.0170   1.0000
  17.000   1.2696   0.08758   0.08206  -0.0128   0.0167   1.0000
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