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NACA M14 AIRFOIL (m14-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA M14 AIRFOIL (m14-il)
Reynolds number: 500,000
Max Cl/Cd: 98.13 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m14-il-500000-n5.txt
Download as CSV file: xf-m14-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M14 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4506   0.10241   0.10022  -0.0073   1.0000   0.0098
  -9.000  -0.4510   0.09748   0.09530  -0.0097   1.0000   0.0102
  -8.750  -0.4563   0.09136   0.08922  -0.0131   1.0000   0.0106
  -8.500  -0.4504   0.08857   0.08644  -0.0148   1.0000   0.0108
  -8.250  -0.4438   0.08602   0.08389  -0.0166   1.0000   0.0110
  -8.000  -0.4382   0.08333   0.08124  -0.0186   1.0000   0.0113
  -7.750  -0.4305   0.08005   0.07796  -0.0219   1.0000   0.0117
  -7.500  -0.4191   0.07568   0.07359  -0.0270   0.9871   0.0123
  -7.250  -0.4008   0.06915   0.06699  -0.0355   0.9525   0.0131
  -7.000  -0.3893   0.05873   0.05636  -0.0455   0.9199   0.0143
  -6.750  -0.3716   0.05687   0.05438  -0.0466   0.8951   0.0147
  -6.500  -0.3532   0.05509   0.05248  -0.0475   0.8734   0.0151
  -6.250  -0.3339   0.05219   0.04943  -0.0493   0.8537   0.0159
  -6.000  -0.3137   0.04731   0.04433  -0.0521   0.8365   0.0169
  -5.750  -0.2933   0.03632   0.03280  -0.0563   0.8229   0.0193
  -5.500  -0.2706   0.03526   0.03160  -0.0565   0.8074   0.0198
  -5.250  -0.2474   0.03363   0.02980  -0.0568   0.7933   0.0202
  -5.000  -0.2238   0.03110   0.02703  -0.0571   0.7805   0.0210
  -4.750  -0.1998   0.02785   0.02346  -0.0573   0.7687   0.0221
  -4.500  -0.1759   0.02363   0.01876  -0.0571   0.7581   0.0234
  -4.250  -0.1512   0.02069   0.01535  -0.0567   0.7474   0.0241
  -4.000  -0.1251   0.01917   0.01350  -0.0565   0.7370   0.0247
  -3.750  -0.0980   0.01868   0.01277  -0.0563   0.7267   0.0252
  -3.500  -0.0724   0.01669   0.01038  -0.0562   0.7170   0.0258
  -3.250  -0.0460   0.01522   0.00865  -0.0561   0.7076   0.0263
  -3.000  -0.0191   0.01435   0.00760  -0.0560   0.6983   0.0267
  -2.750   0.0083   0.01367   0.00678  -0.0559   0.6888   0.0270
  -2.500   0.0358   0.01309   0.00608  -0.0559   0.6796   0.0273
  -2.250   0.0632   0.01259   0.00545  -0.0558   0.6703   0.0276
  -2.000   0.0909   0.01213   0.00489  -0.0557   0.6608   0.0278
  -1.750   0.1185   0.01179   0.00447  -0.0557   0.6513   0.0284
  -1.500   0.1461   0.01144   0.00405  -0.0556   0.6415   0.0288
  -1.250   0.1737   0.01107   0.00360  -0.0556   0.6319   0.0289
  -1.000   0.2013   0.01075   0.00321  -0.0555   0.6228   0.0290
  -0.750   0.2289   0.01048   0.00288  -0.0554   0.6135   0.0292
  -0.500   0.2566   0.01024   0.00260  -0.0554   0.6050   0.0296
   0.000   0.3121   0.00988   0.00217  -0.0554   0.5878   0.0307
   0.250   0.3399   0.00976   0.00201  -0.0554   0.5795   0.0315
   0.500   0.3678   0.00966   0.00188  -0.0554   0.5711   0.0323
   0.750   0.3957   0.00960   0.00179  -0.0554   0.5631   0.0330
   1.000   0.4236   0.00955   0.00171  -0.0555   0.5545   0.0336
   1.250   0.4516   0.00952   0.00166  -0.0555   0.5468   0.0341
   1.500   0.4796   0.00951   0.00163  -0.0556   0.5388   0.0348
   1.750   0.5076   0.00950   0.00159  -0.0556   0.5306   0.0374
   2.250   0.5635   0.00952   0.00161  -0.0557   0.5148   0.0431
   2.500   0.5908   0.00934   0.00171  -0.0558   0.5070   0.1607
   3.000   0.6539   0.00759   0.00195  -0.0580   0.4901   1.0000
   3.250   0.6807   0.00769   0.00204  -0.0578   0.4820   1.0000
   3.500   0.7076   0.00780   0.00212  -0.0576   0.4737   1.0000
   3.750   0.7343   0.00793   0.00222  -0.0575   0.4647   1.0000
   4.000   0.7613   0.00805   0.00234  -0.0574   0.4562   1.0000
   4.250   0.7881   0.00819   0.00247  -0.0573   0.4475   1.0000
   4.500   0.8148   0.00835   0.00260  -0.0571   0.4349   1.0000
   4.750   0.8410   0.00857   0.00275  -0.0569   0.4123   1.0000
   5.000   0.8665   0.00887   0.00293  -0.0567   0.3816   1.0000
   5.250   0.8920   0.00919   0.00314  -0.0564   0.3544   1.0000
   5.500   0.9167   0.00961   0.00340  -0.0561   0.3196   1.0000
   5.750   0.9412   0.01007   0.00371  -0.0558   0.2818   1.0000
   6.000   0.9643   0.01071   0.00410  -0.0553   0.2291   1.0000
   6.250   0.9831   0.01193   0.00483  -0.0544   0.1371   1.0000
   6.500   1.0018   0.01313   0.00562  -0.0535   0.0621   1.0000
   6.750   1.0234   0.01390   0.00625  -0.0528   0.0321   1.0000
   7.000   1.0462   0.01450   0.00679  -0.0522   0.0199   1.0000
   7.250   1.0697   0.01498   0.00730  -0.0517   0.0163   1.0000
   7.500   1.0931   0.01545   0.00783  -0.0511   0.0146   1.0000
   7.750   1.1154   0.01603   0.00844  -0.0505   0.0129   1.0000
   8.000   1.1364   0.01674   0.00924  -0.0496   0.0114   1.0000
   8.250   1.1584   0.01729   0.00986  -0.0489   0.0107   1.0000
   8.500   1.1793   0.01792   0.01057  -0.0480   0.0101   1.0000
   8.750   1.1993   0.01861   0.01132  -0.0471   0.0094   1.0000
   9.000   1.2183   0.01934   0.01212  -0.0460   0.0089   1.0000
   9.250   1.2356   0.02019   0.01305  -0.0448   0.0084   1.0000
   9.500   1.2480   0.02140   0.01434  -0.0429   0.0078   1.0000
   9.750   1.2651   0.02214   0.01516  -0.0416   0.0075   1.0000
  10.000   1.2795   0.02303   0.01614  -0.0400   0.0072   1.0000
  10.250   1.2899   0.02404   0.01725  -0.0378   0.0069   1.0000
  10.500   1.2979   0.02511   0.01841  -0.0354   0.0066   1.0000
  10.750   1.3055   0.02631   0.01971  -0.0332   0.0064   1.0000
  11.000   1.3128   0.02764   0.02113  -0.0313   0.0062   1.0000
  11.250   1.3199   0.02910   0.02269  -0.0297   0.0061   1.0000
  11.500   1.3265   0.03069   0.02437  -0.0284   0.0059   1.0000
  11.750   1.3321   0.03247   0.02625  -0.0272   0.0058   1.0000
  12.000   1.3358   0.03453   0.02840  -0.0261   0.0056   1.0000
  12.250   1.3365   0.03701   0.03099  -0.0251   0.0055   1.0000
  12.500   1.3354   0.03976   0.03387  -0.0240   0.0054   1.0000
  12.750   1.3390   0.04210   0.03634  -0.0234   0.0053   1.0000
  13.000   1.3417   0.04456   0.03895  -0.0229   0.0052   1.0000
  13.250   1.3436   0.04719   0.04172  -0.0225   0.0051   1.0000
  13.500   1.3441   0.05001   0.04470  -0.0222   0.0050   1.0000
  13.750   1.3436   0.05301   0.04786  -0.0221   0.0048   1.0000
  14.000   1.3422   0.05619   0.05120  -0.0221   0.0047   1.0000
  14.250   1.3394   0.05961   0.05476  -0.0223   0.0046   1.0000
  14.500   1.3353   0.06326   0.05857  -0.0228   0.0045   1.0000
  14.750   1.3302   0.06717   0.06263  -0.0234   0.0044   1.0000
  15.000   1.3234   0.07146   0.06707  -0.0243   0.0043   1.0000
  15.250   1.3154   0.07609   0.07187  -0.0255   0.0043   1.0000
  15.500   1.3067   0.08102   0.07696  -0.0270   0.0042   1.0000
  15.750   1.2967   0.08631   0.08240  -0.0288   0.0042   1.0000
  16.000   1.2857   0.09195   0.08820  -0.0309   0.0042   1.0000
  16.250   1.2733   0.09806   0.09448  -0.0334   0.0042   1.0000
  16.500   1.2599   0.10457   0.10115  -0.0363   0.0041   1.0000
  16.750   1.2454   0.11148   0.10821  -0.0395   0.0041   1.0000
  17.000   1.2291   0.11905   0.11595  -0.0432   0.0041   1.0000
  17.250   1.2121   0.12709   0.12415  -0.0473   0.0041   1.0000
  17.500   1.1930   0.13597   0.13320  -0.0521   0.0041   1.0000
  17.750   1.1707   0.14614   0.14354  -0.0578   0.0041   1.0000
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