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NACA M14 AIRFOIL (m14-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA M14 AIRFOIL (m14-il)
Reynolds number: 1,000,000
Max Cl/Cd: 121.88 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m14-il-1000000.txt
Download as CSV file: xf-m14-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4335   0.09011   0.08860  -0.0156   1.0000   0.0149
  -8.000  -0.4318   0.08605   0.08455  -0.0187   1.0000   0.0149
  -7.750  -0.4322   0.08031   0.07883  -0.0228   1.0000   0.0153
  -7.500  -0.4209   0.07779   0.07631  -0.0242   1.0000   0.0155
  -7.250  -0.4089   0.07500   0.07351  -0.0265   1.0000   0.0157
  -7.000  -0.3931   0.07173   0.07023  -0.0300   0.9950   0.0162
  -6.750  -0.3678   0.06763   0.06608  -0.0362   0.9710   0.0174
  -6.500  -0.3393   0.06088   0.05915  -0.0450   0.9362   0.0191
  -6.250  -0.3230   0.05623   0.05432  -0.0476   0.9078   0.0192
  -6.000  -0.3048   0.05129   0.04919  -0.0500   0.8845   0.0192
  -5.750  -0.2937   0.04414   0.04180  -0.0528   0.8647   0.0199
  -5.500  -0.2736   0.04278   0.04033  -0.0531   0.8456   0.0203
  -5.250  -0.2521   0.04132   0.03874  -0.0535   0.8278   0.0210
  -5.000  -0.2287   0.03901   0.03626  -0.0543   0.8117   0.0225
  -4.750  -0.1964   0.03519   0.03215  -0.0550   0.7976   0.0247
  -4.500  -0.1728   0.03060   0.02722  -0.0553   0.7848   0.0248
  -4.250  -0.1569   0.02303   0.01909  -0.0556   0.7738   0.0260
  -4.000  -0.1319   0.02212   0.01807  -0.0556   0.7611   0.0265
  -3.500  -0.0803   0.01985   0.01546  -0.0555   0.7378   0.0283
  -3.250  -0.0534   0.01864   0.01405  -0.0553   0.7273   0.0302
  -3.000  -0.0239   0.01940   0.01467  -0.0551   0.7165   0.0322
  -2.750   0.0011   0.01605   0.01081  -0.0547   0.7069   0.0329
  -2.500  -0.5844   0.45761   0.45506   0.1219   0.7866   0.0262
  -1.750   0.1109   0.01153   0.00563  -0.0542   0.6682   0.0310
  -1.500   0.1387   0.01079   0.00475  -0.0541   0.6592   0.0308
  -1.250   0.1666   0.01015   0.00402  -0.0540   0.6501   0.0306
  -1.000   0.1944   0.00963   0.00342  -0.0540   0.6414   0.0306
  -0.750   0.2223   0.00929   0.00302  -0.0539   0.6323   0.0310
  -0.500   0.2503   0.00902   0.00271  -0.0539   0.6234   0.0315
  -0.250   0.2782   0.00883   0.00247  -0.0539   0.6149   0.0318
   0.000   0.3063   0.00865   0.00226  -0.0539   0.6059   0.0321
   0.250   0.3343   0.00849   0.00207  -0.0539   0.5974   0.0323
   0.500   0.3623   0.00833   0.00188  -0.0540   0.5888   0.0324
   0.750   0.3903   0.00811   0.00162  -0.0540   0.5807   0.0330
   1.250   0.4467   0.00790   0.00133  -0.0541   0.5637   0.0351
   1.500   0.4749   0.00786   0.00126  -0.0542   0.5558   0.0376
   1.750   0.5032   0.00783   0.00122  -0.0543   0.5476   0.0404
   2.000   0.5314   0.00782   0.00122  -0.0543   0.5396   0.0490
   2.250   0.5590   0.00753   0.00130  -0.0545   0.5311   0.2191
   2.500   0.5979   0.00576   0.00147  -0.0575   0.5230   1.0000
   2.750   0.6244   0.00585   0.00150  -0.0572   0.5148   1.0000
   3.000   0.6512   0.00592   0.00155  -0.0570   0.5066   1.0000
   3.250   0.6779   0.00602   0.00161  -0.0568   0.4981   1.0000
   3.500   0.7049   0.00610   0.00168  -0.0567   0.4896   1.0000
   3.750   0.7318   0.00621   0.00175  -0.0565   0.4798   1.0000
   4.000   0.7587   0.00633   0.00183  -0.0564   0.4674   1.0000
   4.250   0.7855   0.00647   0.00192  -0.0563   0.4490   1.0000
   4.500   0.8119   0.00668   0.00202  -0.0561   0.4255   1.0000
   4.750   0.8385   0.00688   0.00214  -0.0560   0.4024   1.0000
   5.000   0.8650   0.00711   0.00229  -0.0559   0.3815   1.0000
   5.250   0.8910   0.00740   0.00247  -0.0557   0.3540   1.0000
   5.500   0.9172   0.00767   0.00266  -0.0556   0.3294   1.0000
   5.750   0.9426   0.00805   0.00289  -0.0554   0.2971   1.0000
   6.000   0.9672   0.00856   0.00319  -0.0551   0.2507   1.0000
   6.250   0.9862   0.00984   0.00390  -0.0542   0.1427   1.0000
   6.500   1.0039   0.01129   0.00480  -0.0531   0.0431   1.0000
   6.750   1.0271   0.01194   0.00532  -0.0525   0.0224   1.0000
   7.000   1.0515   0.01240   0.00579  -0.0520   0.0183   1.0000
   7.250   1.0762   0.01278   0.00622  -0.0517   0.0168   1.0000
   7.500   1.1001   0.01327   0.00672  -0.0512   0.0153   1.0000
   7.750   1.1218   0.01401   0.00755  -0.0504   0.0138   1.0000
   8.000   1.1457   0.01443   0.00801  -0.0499   0.0133   1.0000
   8.250   1.1690   0.01490   0.00852  -0.0494   0.0126   1.0000
   8.500   1.1917   0.01541   0.00907  -0.0488   0.0118   1.0000
   8.750   1.2132   0.01602   0.00972  -0.0480   0.0112   1.0000
   9.000   1.2307   0.01701   0.01079  -0.0467   0.0105   1.0000
   9.250   1.2446   0.01829   0.01217  -0.0449   0.0100   1.0000
   9.500   1.2646   0.01890   0.01285  -0.0439   0.0098   1.0000
   9.750   1.2827   0.01965   0.01367  -0.0427   0.0095   1.0000
  10.000   1.2991   0.02050   0.01459  -0.0413   0.0092   1.0000
  10.250   1.3141   0.02141   0.01557  -0.0397   0.0089   1.0000
  10.500   1.3280   0.02231   0.01654  -0.0380   0.0086   1.0000
  10.750   1.3400   0.02313   0.01741  -0.0360   0.0083   1.0000
  11.000   1.3504   0.02400   0.01834  -0.0339   0.0080   1.0000
  11.250   1.3593   0.02507   0.01945  -0.0318   0.0078   1.0000
  11.500   1.3621   0.02674   0.02121  -0.0294   0.0075   1.0000
  11.750   1.3536   0.02981   0.02442  -0.0261   0.0072   1.0000
  12.000   1.3608   0.03142   0.02615  -0.0247   0.0071   1.0000
  12.250   1.3695   0.03291   0.02774  -0.0237   0.0070   1.0000
  12.500   1.3764   0.03466   0.02960  -0.0226   0.0069   1.0000
  12.750   1.3817   0.03665   0.03170  -0.0216   0.0068   1.0000
  13.000   1.3856   0.03884   0.03402  -0.0207   0.0067   1.0000
  13.250   1.3884   0.04120   0.03652  -0.0199   0.0066   1.0000
  13.500   1.3896   0.04379   0.03924  -0.0192   0.0065   1.0000
  13.750   1.3893   0.04661   0.04220  -0.0187   0.0064   1.0000
  14.000   1.3876   0.04966   0.04540  -0.0183   0.0063   1.0000
  14.250   1.3844   0.05294   0.04882  -0.0182   0.0062   1.0000
  14.500   1.3796   0.05651   0.05254  -0.0183   0.0061   1.0000
  14.750   1.3729   0.06039   0.05657  -0.0186   0.0061   1.0000
  15.000   1.3644   0.06464   0.06098  -0.0193   0.0060   1.0000
  15.250   1.3550   0.06919   0.06567  -0.0203   0.0060   1.0000
  15.500   1.3444   0.07408   0.07071  -0.0216   0.0059   1.0000
  15.750   1.3308   0.07971   0.07651  -0.0234   0.0059   1.0000
  16.000   1.3163   0.08572   0.08268  -0.0257   0.0059   1.0000
  16.250   1.3017   0.09197   0.08908  -0.0283   0.0058   1.0000
  16.500   1.2833   0.09923   0.09651  -0.0315   0.0058   1.0000
  16.750   1.2622   0.10735   0.10480  -0.0353   0.0058   1.0000
  17.000   1.2410   0.11583   0.11345  -0.0397   0.0058   1.0000
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