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NACA M14 AIRFOIL (m14-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA M14 AIRFOIL (m14-il)
Reynolds number: 1,000,000
Max Cl/Cd: 113.67 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m14-il-1000000-n5.txt
Download as CSV file: xf-m14-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4820   0.10426   0.10270  -0.0044   1.0000   0.0068
  -9.500  -0.4879   0.09807   0.09653  -0.0073   1.0000   0.0075
  -9.250  -0.4915   0.09276   0.09123  -0.0103   1.0000   0.0079
  -9.000  -0.4862   0.08966   0.08814  -0.0122   1.0000   0.0081
  -8.750  -0.4813   0.08652   0.08501  -0.0143   1.0000   0.0082
  -8.500  -0.4759   0.08309   0.08160  -0.0174   0.9815   0.0084
  -8.250  -0.4676   0.07910   0.07752  -0.0221   0.9254   0.0087
  -8.000  -0.4617   0.07477   0.07304  -0.0262   0.8894   0.0091
  -7.750  -0.4635   0.06340   0.06150  -0.0374   0.8632   0.0106
  -7.500  -0.4465   0.06051   0.05848  -0.0400   0.8421   0.0109
  -7.250  -0.4280   0.05787   0.05573  -0.0422   0.8229   0.0111
  -6.750  -0.3999   0.03871   0.03592  -0.0534   0.7939   0.0144
  -6.500  -0.3763   0.03745   0.03454  -0.0538   0.7792   0.0146
  -6.250  -0.3524   0.03613   0.03310  -0.0543   0.7660   0.0149
  -6.000  -0.3393   0.02343   0.01962  -0.0555   0.7574   0.0177
  -5.750  -0.3071   0.02915   0.02564  -0.0555   0.7433   0.0165
  -5.500  -0.2951   0.01703   0.01225  -0.0550   0.7359   0.0194
  -5.250  -0.2686   0.01657   0.01168  -0.0550   0.7257   0.0197
  -5.000  -0.2418   0.01612   0.01111  -0.0550   0.7155   0.0199
  -4.750  -0.2150   0.01553   0.01039  -0.0550   0.7058   0.0202
  -4.500  -0.1881   0.01491   0.00963  -0.0549   0.6968   0.0205
  -4.250  -0.1609   0.01436   0.00894  -0.0549   0.6875   0.0209
  -4.000  -0.1335   0.01392   0.00839  -0.0549   0.6786   0.0214
  -3.750  -0.1062   0.01336   0.00769  -0.0549   0.6698   0.0219
  -3.500  -0.0787   0.01278   0.00697  -0.0549   0.6607   0.0223
  -3.250  -0.0511   0.01226   0.00633  -0.0549   0.6520   0.0227
  -3.000  -0.0234   0.01179   0.00574  -0.0548   0.6426   0.0230
  -2.750   0.0044   0.01135   0.00518  -0.0548   0.6335   0.0233
  -2.500   0.0322   0.01095   0.00468  -0.0548   0.6237   0.0235
  -2.250   0.0600   0.01057   0.00422  -0.0548   0.6135   0.0236
  -2.000   0.0878   0.01023   0.00380  -0.0548   0.6041   0.0238
  -1.750   0.1156   0.00992   0.00342  -0.0548   0.5950   0.0239
  -1.500   0.1436   0.00969   0.00314  -0.0549   0.5861   0.0242
  -1.250   0.1716   0.00948   0.00288  -0.0549   0.5779   0.0244
  -1.000   0.1994   0.00923   0.00257  -0.0549   0.5694   0.0245
  -0.750   0.2274   0.00901   0.00231  -0.0550   0.5616   0.0246
  -0.500   0.2553   0.00884   0.00210  -0.0550   0.5534   0.0247
  -0.250   0.2834   0.00870   0.00193  -0.0551   0.5460   0.0249
   0.000   0.3115   0.00862   0.00180  -0.0551   0.5377   0.0251
   0.250   0.3397   0.00853   0.00171  -0.0552   0.5304   0.0253
   0.500   0.3676   0.00833   0.00144  -0.0553   0.5229   0.0266
   0.750   0.3958   0.00823   0.00133  -0.0554   0.5155   0.0276
   1.000   0.4239   0.00820   0.00128  -0.0554   0.5075   0.0284
   1.250   0.4522   0.00817   0.00124  -0.0556   0.5006   0.0290
   1.750   0.5087   0.00816   0.00121  -0.0558   0.4855   0.0301
   2.000   0.5368   0.00818   0.00121  -0.0559   0.4775   0.0306
   2.250   0.5650   0.00819   0.00122  -0.0560   0.4701   0.0317
   2.500   0.5931   0.00823   0.00125  -0.0562   0.4626   0.0327
   2.750   0.6213   0.00826   0.00128  -0.0563   0.4543   0.0336
   3.250   0.6770   0.00814   0.00146  -0.0566   0.4375   0.1799
   3.500   0.7091   0.00642   0.00167  -0.0581   0.4291   1.0000
   3.750   0.7359   0.00655   0.00175  -0.0580   0.4173   1.0000
   4.000   0.7627   0.00671   0.00185  -0.0578   0.4025   1.0000
   4.250   0.7889   0.00696   0.00198  -0.0577   0.3761   1.0000
   4.500   0.8147   0.00727   0.00214  -0.0575   0.3440   1.0000
   4.750   0.8407   0.00757   0.00232  -0.0573   0.3161   1.0000
   5.000   0.8665   0.00790   0.00253  -0.0571   0.2866   1.0000
   5.250   0.8921   0.00826   0.00275  -0.0570   0.2562   1.0000
   5.500   0.9143   0.00911   0.00321  -0.0564   0.1773   1.0000
   5.750   0.9372   0.00986   0.00368  -0.0559   0.1215   1.0000
   6.000   0.9585   0.01080   0.00427  -0.0553   0.0542   1.0000
   6.250   0.9827   0.01131   0.00467  -0.0549   0.0315   1.0000
   6.500   1.0072   0.01177   0.00505  -0.0545   0.0176   1.0000
   6.750   1.0324   0.01209   0.00538  -0.0543   0.0147   1.0000
   7.000   1.0573   0.01247   0.00576  -0.0539   0.0119   1.0000
   7.250   1.0824   0.01279   0.00610  -0.0537   0.0109   1.0000
   7.500   1.1072   0.01313   0.00647  -0.0534   0.0100   1.0000
   7.750   1.1315   0.01352   0.00688  -0.0530   0.0091   1.0000
   8.000   1.1550   0.01399   0.00739  -0.0525   0.0082   1.0000
   8.250   1.1786   0.01444   0.00787  -0.0520   0.0077   1.0000
   8.500   1.2023   0.01484   0.00830  -0.0516   0.0072   1.0000
   8.750   1.2255   0.01527   0.00877  -0.0511   0.0067   1.0000
   9.000   1.2481   0.01573   0.00927  -0.0506   0.0063   1.0000
   9.250   1.2700   0.01626   0.00983  -0.0499   0.0059   1.0000
   9.500   1.2899   0.01695   0.01058  -0.0490   0.0055   1.0000
   9.750   1.3101   0.01758   0.01126  -0.0481   0.0053   1.0000
  10.000   1.3302   0.01817   0.01191  -0.0472   0.0051   1.0000
  10.250   1.3492   0.01882   0.01263  -0.0462   0.0049   1.0000
  10.500   1.3673   0.01950   0.01338  -0.0450   0.0047   1.0000
  10.750   1.3842   0.02023   0.01417  -0.0437   0.0045   1.0000
  11.000   1.4001   0.02097   0.01498  -0.0423   0.0044   1.0000
  11.250   1.4147   0.02170   0.01577  -0.0407   0.0042   1.0000
  11.500   1.4257   0.02247   0.01660  -0.0386   0.0040   1.0000
  11.750   1.4358   0.02336   0.01754  -0.0365   0.0039   1.0000
  12.000   1.4435   0.02450   0.01875  -0.0344   0.0037   1.0000
  12.250   1.4467   0.02610   0.02045  -0.0322   0.0036   1.0000
  12.500   1.4522   0.02767   0.02213  -0.0307   0.0035   1.0000
  12.750   1.4590   0.02923   0.02379  -0.0295   0.0035   1.0000
  13.000   1.4652   0.03097   0.02563  -0.0285   0.0034   1.0000
  13.250   1.4702   0.03291   0.02767  -0.0276   0.0034   1.0000
  13.500   1.4743   0.03505   0.02991  -0.0270   0.0033   1.0000
  13.750   1.4769   0.03740   0.03238  -0.0265   0.0032   1.0000
  14.000   1.4789   0.03991   0.03499  -0.0261   0.0032   1.0000
  14.250   1.4795   0.04264   0.03783  -0.0259   0.0031   1.0000
  14.500   1.4790   0.04554   0.04085  -0.0258   0.0031   1.0000
  14.750   1.4780   0.04858   0.04400  -0.0259   0.0030   1.0000
  15.000   1.4750   0.05190   0.04743  -0.0260   0.0030   1.0000
  15.250   1.4709   0.05543   0.05108  -0.0263   0.0029   1.0000
  15.500   1.4664   0.05910   0.05488  -0.0268   0.0029   1.0000
  15.750   1.4608   0.06302   0.05891  -0.0275   0.0029   1.0000
  16.000   1.4549   0.06713   0.06313  -0.0283   0.0028   1.0000
  16.250   1.4477   0.07155   0.06768  -0.0294   0.0028   1.0000
  16.500   1.4400   0.07615   0.07239  -0.0307   0.0028   1.0000
  16.750   1.4318   0.08094   0.07730  -0.0321   0.0027   1.0000
  17.000   1.4219   0.08614   0.08261  -0.0338   0.0027   1.0000
  17.250   1.4121   0.09142   0.08801  -0.0356   0.0027   1.0000
  17.500   1.4010   0.09701   0.09372  -0.0376   0.0027   1.0000
  17.750   1.3886   0.10297   0.09980  -0.0399   0.0027   1.0000
  18.000   1.3767   0.10898   0.10594  -0.0424   0.0026   1.0000
  18.250   1.3638   0.11524   0.11231  -0.0450   0.0026   1.0000
  18.500   1.3493   0.12196   0.11916  -0.0480   0.0026   1.0000
  18.750   1.3357   0.12871   0.12602  -0.0512   0.0026   1.0000
  19.000   1.3207   0.13591   0.13335  -0.0547   0.0026   1.0000
  19.250   1.3056   0.14326   0.14082  -0.0585   0.0026   1.0000
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