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NACA M14 AIRFOIL (m14-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA M14 AIRFOIL (m14-il)
Reynolds number: 100,000
Max Cl/Cd: 57.43 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m14-il-100000-n5.txt
Download as CSV file: xf-m14-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3945   0.09275   0.08806  -0.0195   1.0000   0.0509
  -7.500  -0.3918   0.08962   0.08499  -0.0215   1.0000   0.0526
  -7.250  -0.3865   0.08624   0.08164  -0.0253   1.0000   0.0549
  -7.000  -0.3779   0.08321   0.07856  -0.0361   1.0000   0.0575
  -6.500  -0.3650   0.07519   0.07066  -0.0341   1.0000   0.0605
  -6.250  -0.3571   0.07239   0.06787  -0.0339   1.0000   0.0630
  -6.000  -0.3503   0.06952   0.06501  -0.0347   1.0000   0.0655
  -5.750  -0.3263   0.06705   0.06216  -0.0431   0.9955   0.0709
  -5.500  -0.3002   0.06095   0.05598  -0.0475   0.9858   0.0719
  -5.250  -0.2796   0.05725   0.05239  -0.0480   0.9765   0.0754
  -5.000  -0.2444   0.05379   0.04867  -0.0533   0.9643   0.0834
  -4.750  -0.2068   0.04603   0.04037  -0.0585   0.9520   0.0562
  -4.500  -0.1775   0.04226   0.03640  -0.0610   0.9396   0.0542
  -4.250  -0.1452   0.03867   0.03240  -0.0634   0.9272   0.0552
  -4.000  -0.1152   0.03538   0.02878  -0.0650   0.9148   0.0535
  -3.750  -0.0852   0.03219   0.02518  -0.0661   0.9027   0.0518
  -3.500  -0.0556   0.02934   0.02185  -0.0666   0.8906   0.0507
  -3.250  -0.0275   0.02704   0.01911  -0.0667   0.8776   0.0502
  -3.000  -0.0002   0.02556   0.01728  -0.0666   0.8645   0.0521
  -2.750   0.0272   0.02410   0.01545  -0.0663   0.8518   0.0534
  -2.500   0.0546   0.02266   0.01365  -0.0659   0.8397   0.0530
  -2.250   0.0819   0.02143   0.01207  -0.0655   0.8279   0.0527
  -2.000   0.1093   0.02037   0.01074  -0.0650   0.8167   0.0527
  -1.750   0.1365   0.01948   0.00963  -0.0645   0.8051   0.0529
  -1.500   0.1637   0.01871   0.00869  -0.0641   0.7934   0.0534
  -1.250   0.1906   0.01805   0.00789  -0.0636   0.7824   0.0542
  -1.000   0.2173   0.01748   0.00721  -0.0631   0.7721   0.0551
  -0.750   0.2438   0.01701   0.00665  -0.0626   0.7611   0.0563
  -0.500   0.2699   0.01660   0.00621  -0.0622   0.7501   0.0595
  -0.250   0.2961   0.01631   0.00589  -0.0617   0.7398   0.0639
   0.000   0.3225   0.01605   0.00554  -0.0611   0.7299   0.0671
   0.250   0.3494   0.01587   0.00526  -0.0608   0.7189   0.0704
   0.500   0.3765   0.01567   0.00503  -0.0604   0.7087   0.0773
   0.750   0.4034   0.01547   0.00483  -0.0600   0.6994   0.1001
   1.000   0.4281   0.01454   0.00483  -0.0599   0.6887   0.4037
   1.500   0.5012   0.01346   0.00473  -0.0627   0.6690   1.0000
   1.750   0.5271   0.01361   0.00478  -0.0623   0.6585   1.0000
   2.000   0.5530   0.01377   0.00484  -0.0618   0.6488   1.0000
   2.250   0.5789   0.01392   0.00488  -0.0613   0.6400   1.0000
   2.500   0.6048   0.01409   0.00503  -0.0610   0.6296   1.0000
   2.750   0.6308   0.01427   0.00515  -0.0606   0.6201   1.0000
   3.000   0.6568   0.01444   0.00526  -0.0602   0.6113   1.0000
   3.250   0.6827   0.01464   0.00548  -0.0598   0.6010   1.0000
   3.500   0.7087   0.01484   0.00566  -0.0595   0.5917   1.0000
   3.750   0.7347   0.01504   0.00584  -0.0591   0.5825   1.0000
   4.000   0.7606   0.01526   0.00611  -0.0587   0.5723   1.0000
   4.250   0.7865   0.01549   0.00637  -0.0584   0.5632   1.0000
   4.500   0.8124   0.01572   0.00664  -0.0580   0.5536   1.0000
   4.750   0.8381   0.01598   0.00697  -0.0576   0.5434   1.0000
   5.000   0.8639   0.01623   0.00729  -0.0572   0.5341   1.0000
   5.250   0.8895   0.01650   0.00764  -0.0569   0.5243   1.0000
   5.500   0.9150   0.01679   0.00805  -0.0565   0.5138   1.0000
   5.750   0.9405   0.01709   0.00846  -0.0561   0.5040   1.0000
   6.000   0.9658   0.01736   0.00882  -0.0556   0.4929   1.0000
   6.250   0.9903   0.01762   0.00918  -0.0549   0.4782   1.0000
   6.500   1.0137   0.01785   0.00955  -0.0541   0.4572   1.0000
   6.750   1.0344   0.01801   0.00967  -0.0527   0.4200   1.0000
   7.000   1.0523   0.01844   0.00990  -0.0511   0.3624   1.0000
   7.250   1.0698   0.01919   0.01044  -0.0496   0.3030   1.0000
   7.500   1.0789   0.02090   0.01144  -0.0475   0.1818   1.0000
   7.750   1.0812   0.02361   0.01331  -0.0448   0.0716   1.0000
   8.000   1.0908   0.02546   0.01501  -0.0427   0.0482   1.0000
   8.250   1.1021   0.02698   0.01662  -0.0407   0.0395   1.0000
   8.500   1.1130   0.02840   0.01817  -0.0387   0.0349   1.0000
   8.750   1.1202   0.03004   0.01993  -0.0363   0.0325   1.0000
   9.000   1.1284   0.03148   0.02155  -0.0340   0.0304   1.0000
   9.250   1.1336   0.03294   0.02314  -0.0315   0.0282   1.0000
   9.500   1.1371   0.03457   0.02484  -0.0291   0.0264   1.0000
   9.750   1.1376   0.03663   0.02694  -0.0267   0.0252   1.0000
  10.000   1.1432   0.03854   0.02895  -0.0248   0.0245   1.0000
  10.250   1.1521   0.04038   0.03092  -0.0230   0.0237   1.0000
  10.500   1.1637   0.04226   0.03297  -0.0214   0.0229   1.0000
  10.750   1.1761   0.04418   0.03505  -0.0200   0.0218   1.0000
  11.000   1.1868   0.04618   0.03722  -0.0187   0.0206   1.0000
  11.250   1.1957   0.04831   0.03950  -0.0175   0.0196   1.0000
  11.500   1.2045   0.05066   0.04201  -0.0163   0.0189   1.0000
  11.750   1.2126   0.05330   0.04483  -0.0152   0.0184   1.0000
  12.000   1.2182   0.05623   0.04797  -0.0141   0.0181   1.0000
  12.250   1.2206   0.05954   0.05150  -0.0131   0.0178   1.0000
  12.500   1.2192   0.06318   0.05538  -0.0122   0.0176   1.0000
  12.750   1.2139   0.06716   0.05967  -0.0117   0.0175   1.0000
  13.000   1.2053   0.07138   0.06415  -0.0115   0.0174   1.0000
  13.250   1.1940   0.07595   0.06898  -0.0119   0.0173   1.0000
  13.500   1.1808   0.08079   0.07406  -0.0127   0.0173   1.0000
  13.750   1.1662   0.08595   0.07946  -0.0141   0.0173   1.0000
  14.000   1.1505   0.09143   0.08517  -0.0160   0.0172   1.0000
  14.250   1.1342   0.09726   0.09121  -0.0186   0.0173   1.0000
  14.500   1.1177   0.10341   0.09756  -0.0217   0.0173   1.0000
  14.750   1.1005   0.11015   0.10451  -0.0255   0.0174   1.0000
  15.000   1.0829   0.11768   0.11224  -0.0301   0.0175   1.0000
  15.250   1.0622   0.12685   0.12158  -0.0362   0.0178   1.0000
  15.500   1.0299   0.14098   0.13596  -0.0459   0.0185   1.0000
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