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NACA M13 AIRFOIL (m13-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA M13 AIRFOIL (m13-il)
Reynolds number: 500,000
Max Cl/Cd: 94.96 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m13-il-500000-n5.txt
Download as CSV file: xf-m13-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M13 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4686   0.09868   0.09658   0.0033   1.0000   0.0064
  -8.000  -0.4645   0.09493   0.09286   0.0012   1.0000   0.0064
  -7.750  -0.4607   0.09130   0.08925  -0.0009   1.0000   0.0064
  -7.500  -0.4562   0.08749   0.08546  -0.0039   1.0000   0.0063
  -7.250  -0.4472   0.08309   0.08108  -0.0082   1.0000   0.0063
  -7.000  -0.4359   0.07839   0.07638  -0.0129   1.0000   0.0064
  -6.750  -0.4225   0.07317   0.07115  -0.0182   1.0000   0.0064
  -6.250  -0.3771   0.06220   0.06005  -0.0312   0.9441   0.0069
  -6.000  -0.3554   0.05848   0.05616  -0.0347   0.9087   0.0072
  -5.750  -0.3349   0.05516   0.05268  -0.0372   0.8818   0.0078
  -5.500  -0.3116   0.05028   0.04760  -0.0407   0.8598   0.0087
  -5.250  -0.2849   0.04199   0.03897  -0.0455   0.8421   0.0096
  -5.000  -0.2593   0.03722   0.03391  -0.0476   0.8245   0.0103
  -4.750  -0.2324   0.01972   0.01515  -0.0505   0.8148   0.0147
  -4.500  -0.2059   0.02049   0.01588  -0.0504   0.7971   0.0153
  -4.250  -0.1793   0.02132   0.01667  -0.0504   0.7804   0.0157
  -4.000  -0.1529   0.02124   0.01646  -0.0504   0.7655   0.0167
  -3.750  -0.1261   0.01887   0.01372  -0.0503   0.7526   0.0194
  -3.500  -0.0986   0.01663   0.01094  -0.0501   0.7406   0.0216
  -3.250  -0.0707   0.01665   0.01074  -0.0500   0.7284   0.0225
  -3.000  -0.0444   0.01441   0.00815  -0.0502   0.7181   0.0240
  -2.750  -0.0170   0.01369   0.00725  -0.0502   0.7078   0.0249
  -2.500   0.0105   0.01316   0.00658  -0.0502   0.6974   0.0262
  -2.250   0.0383   0.01252   0.00575  -0.0502   0.6879   0.0272
  -2.000   0.0660   0.01197   0.00504  -0.0501   0.6790   0.0281
  -1.750   0.0938   0.01153   0.00447  -0.0501   0.6694   0.0288
  -1.500   0.1216   0.01114   0.00397  -0.0501   0.6606   0.0292
  -1.000   0.1771   0.01052   0.00317  -0.0500   0.6434   0.0298
  -0.750   0.2049   0.01031   0.00289  -0.0500   0.6347   0.0303
  -0.500   0.2328   0.01011   0.00264  -0.0500   0.6258   0.0306
  -0.250   0.2606   0.00986   0.00235  -0.0501   0.6177   0.0304
   0.000   0.2884   0.00968   0.00212  -0.0501   0.6089   0.0303
   0.250   0.3164   0.00952   0.00192  -0.0501   0.5999   0.0302
   0.500   0.3443   0.00940   0.00177  -0.0502   0.5914   0.0300
   0.750   0.3723   0.00931   0.00165  -0.0502   0.5822   0.0300
   1.000   0.4003   0.00924   0.00156  -0.0503   0.5730   0.0300
   1.250   0.4283   0.00921   0.00149  -0.0503   0.5637   0.0300
   1.500   0.4563   0.00918   0.00145  -0.0504   0.5538   0.0301
   1.750   0.4843   0.00918   0.00142  -0.0505   0.5437   0.0303
   2.000   0.5122   0.00919   0.00141  -0.0505   0.5336   0.0305
   2.250   0.5401   0.00923   0.00141  -0.0506   0.5224   0.0310
   2.500   0.5680   0.00926   0.00144  -0.0507   0.5102   0.0332
   2.750   0.5958   0.00927   0.00153  -0.0507   0.4981   0.0620
   3.000   0.6236   0.00935   0.00163  -0.0508   0.4869   0.0722
   3.250   0.6513   0.00942   0.00171  -0.0509   0.4769   0.0773
   3.500   0.6790   0.00949   0.00183  -0.0510   0.4672   0.0830
   3.750   0.7068   0.00955   0.00195  -0.0511   0.4581   0.0924
   4.000   0.7316   0.00781   0.00218  -0.0509   0.4494   1.0000
   4.250   0.7587   0.00799   0.00234  -0.0509   0.4320   1.0000
   4.500   0.7853   0.00828   0.00251  -0.0508   0.3987   1.0000
   4.750   0.8113   0.00866   0.00271  -0.0507   0.3538   1.0000
   5.000   0.8352   0.00949   0.00308  -0.0505   0.2588   1.0000
   5.250   0.8551   0.01115   0.00395  -0.0502   0.1005   1.0000
   5.500   0.8775   0.01229   0.00469  -0.0498   0.0229   1.0000
   5.750   0.9030   0.01275   0.00515  -0.0495   0.0152   1.0000
   6.000   0.9285   0.01323   0.00573  -0.0492   0.0126   1.0000
   6.250   0.9539   0.01367   0.00624  -0.0490   0.0110   1.0000
   6.500   0.9787   0.01416   0.00680  -0.0487   0.0094   1.0000
   6.750   1.0015   0.01504   0.00777  -0.0481   0.0081   1.0000
   7.000   1.0247   0.01578   0.00862  -0.0476   0.0076   1.0000
   7.250   1.0473   0.01656   0.00949  -0.0470   0.0071   1.0000
   7.500   1.0693   0.01738   0.01040  -0.0463   0.0065   1.0000
   7.750   1.0918   0.01805   0.01115  -0.0457   0.0059   1.0000
   8.000   1.1136   0.01876   0.01189  -0.0452   0.0054   1.0000
   8.250   1.1299   0.02028   0.01351  -0.0438   0.0050   1.0000
   8.500   1.1491   0.02135   0.01471  -0.0427   0.0048   1.0000
   8.750   1.1669   0.02260   0.01611  -0.0415   0.0046   1.0000
   9.000   1.1837   0.02405   0.01771  -0.0401   0.0044   1.0000
   9.250   1.1996   0.02568   0.01950  -0.0386   0.0042   1.0000
   9.500   1.2148   0.02746   0.02147  -0.0371   0.0040   1.0000
   9.750   1.2290   0.02943   0.02367  -0.0356   0.0038   1.0000
  10.000   1.2416   0.03161   0.02608  -0.0339   0.0037   1.0000
  10.250   1.2522   0.03384   0.02854  -0.0321   0.0036   1.0000
  10.500   1.2614   0.03569   0.03058  -0.0304   0.0035   1.0000
  10.750   1.2680   0.03725   0.03230  -0.0285   0.0034   1.0000
  11.000   1.2695   0.03885   0.03403  -0.0260   0.0033   1.0000
  11.250   1.2668   0.04120   0.03656  -0.0238   0.0032   1.0000
  11.500   1.2557   0.04487   0.04048  -0.0219   0.0031   1.0000
  11.750   1.2462   0.04863   0.04452  -0.0208   0.0031   1.0000
  12.000   1.2356   0.05283   0.04899  -0.0204   0.0030   1.0000
  12.250   1.2206   0.05787   0.05430  -0.0208   0.0030   1.0000
  12.500   1.2039   0.06344   0.06010  -0.0222   0.0030   1.0000
  12.750   1.1867   0.06939   0.06624  -0.0243   0.0030   1.0000
  13.000   1.1682   0.07600   0.07305  -0.0271   0.0030   1.0000
  13.250   1.1497   0.08297   0.08019  -0.0306   0.0030   1.0000
  13.500   1.1312   0.09043   0.08780  -0.0347   0.0030   1.0000
  13.750   1.1128   0.09837   0.09586  -0.0393   0.0030   1.0000
  14.000   1.0950   0.10694   0.10456  -0.0444   0.0030   1.0000
  14.250   1.0778   0.11608   0.11379  -0.0499   0.0031   1.0000
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