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NACA M13 AIRFOIL (m13-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA M13 AIRFOIL (m13-il)
Reynolds number: 1,000,000
Max Cl/Cd: 86.34 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m13-il-1000000-n5.txt
Download as CSV file: xf-m13-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4800   0.09682   0.09534   0.0043   1.0000   0.0033
  -8.000  -0.4766   0.09298   0.09152   0.0021   1.0000   0.0034
  -7.750  -0.4740   0.08910   0.08767  -0.0004   1.0000   0.0035
  -7.500  -0.4651   0.08416   0.08272  -0.0058   0.9725   0.0038
  -7.250  -0.4557   0.07844   0.07684  -0.0116   0.9035   0.0040
  -7.000  -0.4454   0.07170   0.06996  -0.0181   0.8736   0.0042
  -6.750  -0.4305   0.06394   0.06205  -0.0258   0.8504   0.0045
  -6.500  -0.4107   0.05981   0.05777  -0.0297   0.8264   0.0048
  -6.250  -0.3892   0.05517   0.05298  -0.0338   0.8049   0.0051
  -6.000  -0.3655   0.04787   0.04546  -0.0394   0.7876   0.0057
  -5.750  -0.3402   0.03496   0.03201  -0.0461   0.7756   0.0067
  -5.500  -0.3149   0.03140   0.02823  -0.0472   0.7604   0.0076
  -5.250  -0.2966   0.01498   0.01040  -0.0487   0.7527   0.0095
  -4.750  -0.2423   0.01376   0.00887  -0.0487   0.7262   0.0128
  -4.500  -0.2160   0.01185   0.00649  -0.0487   0.7152   0.0151
  -4.250  -0.1878   0.01225   0.00689  -0.0487   0.7043   0.0157
  -4.000  -0.1598   0.01248   0.00711  -0.0488   0.6939   0.0166
  -3.750  -0.1319   0.01235   0.00689  -0.0489   0.6840   0.0177
  -3.500  -0.1040   0.01210   0.00652  -0.0489   0.6748   0.0190
  -3.250  -0.0762   0.01181   0.00610  -0.0489   0.6660   0.0202
  -3.000  -0.0481   0.01162   0.00582  -0.0490   0.6575   0.0211
  -2.750  -0.0201   0.01146   0.00556  -0.0490   0.6489   0.0217
  -2.500   0.0080   0.01140   0.00542  -0.0491   0.6401   0.0222
  -2.250   0.0362   0.01147   0.00541  -0.0492   0.6326   0.0225
  -2.000   0.0633   0.01005   0.00382  -0.0492   0.6247   0.0241
  -1.750   0.0912   0.00970   0.00341  -0.0493   0.6167   0.0248
  -1.250   0.1471   0.00917   0.00277  -0.0494   0.6007   0.0256
  -1.000   0.1751   0.00895   0.00249  -0.0495   0.5929   0.0259
  -0.750   0.2031   0.00874   0.00224  -0.0495   0.5843   0.0260
  -0.500   0.2312   0.00857   0.00202  -0.0496   0.5760   0.0262
  -0.250   0.2593   0.00843   0.00184  -0.0497   0.5675   0.0266
   0.000   0.2874   0.00830   0.00167  -0.0498   0.5590   0.0266
   0.250   0.3155   0.00819   0.00151  -0.0498   0.5497   0.0263
   0.500   0.3437   0.00810   0.00139  -0.0499   0.5401   0.0261
   0.750   0.3719   0.00803   0.00129  -0.0500   0.5310   0.0259
   1.000   0.4000   0.00799   0.00122  -0.0501   0.5206   0.0258
   1.250   0.4282   0.00796   0.00116  -0.0503   0.5100   0.0257
   1.500   0.4563   0.00795   0.00112  -0.0504   0.4989   0.0256
   1.750   0.4844   0.00797   0.00111  -0.0505   0.4866   0.0256
   2.000   0.5124   0.00800   0.00110  -0.0506   0.4736   0.0256
   2.250   0.5405   0.00804   0.00111  -0.0507   0.4622   0.0258
   2.500   0.5685   0.00807   0.00113  -0.0508   0.4527   0.0262
   2.750   0.5966   0.00809   0.00116  -0.0509   0.4448   0.0272
   3.000   0.6246   0.00814   0.00120  -0.0511   0.4360   0.0301
   3.250   0.6527   0.00816   0.00129  -0.0512   0.4281   0.0574
   3.750   0.7085   0.00830   0.00150  -0.0515   0.4103   0.0711
   4.000   0.7355   0.00857   0.00163  -0.0515   0.3708   0.0739
   4.250   0.7624   0.00883   0.00180  -0.0516   0.3340   0.0785
   4.500   0.7877   0.00949   0.00210  -0.0516   0.2510   0.0836
   4.750   0.8114   0.01046   0.00260  -0.0515   0.1445   0.0904
   5.000   0.8343   0.01161   0.00327  -0.0512   0.0338   0.0965
   5.500   0.8832   0.01054   0.00400  -0.0507   0.0126   1.0000
   5.750   0.9097   0.01083   0.00431  -0.0506   0.0105   1.0000
   6.000   0.9356   0.01124   0.00473  -0.0505   0.0080   1.0000
   6.250   0.9619   0.01154   0.00508  -0.0504   0.0074   1.0000
   6.500   0.9879   0.01189   0.00546  -0.0502   0.0066   1.0000
   6.750   1.0135   0.01228   0.00587  -0.0501   0.0059   1.0000
   7.000   1.0381   0.01286   0.00649  -0.0498   0.0051   1.0000
   7.250   1.0635   0.01324   0.00691  -0.0496   0.0047   1.0000
   7.500   1.0882   0.01371   0.00746  -0.0493   0.0043   1.0000
   7.750   1.1125   0.01423   0.00803  -0.0490   0.0040   1.0000
   8.000   1.1365   0.01476   0.00860  -0.0486   0.0037   1.0000
   8.250   1.1600   0.01532   0.00922  -0.0482   0.0035   1.0000
   8.500   1.1819   0.01610   0.01006  -0.0476   0.0033   1.0000
   8.750   1.2019   0.01712   0.01119  -0.0467   0.0031   1.0000
   9.000   1.2232   0.01789   0.01205  -0.0460   0.0029   1.0000
   9.250   1.2432   0.01879   0.01305  -0.0451   0.0028   1.0000
   9.500   1.2621   0.01979   0.01419  -0.0441   0.0027   1.0000
   9.750   1.2807   0.02076   0.01528  -0.0431   0.0025   1.0000
  10.000   1.2990   0.02171   0.01632  -0.0420   0.0024   1.0000
  10.250   1.3173   0.02259   0.01729  -0.0411   0.0023   1.0000
  10.500   1.3348   0.02349   0.01827  -0.0400   0.0022   1.0000
  10.750   1.3509   0.02449   0.01937  -0.0388   0.0021   1.0000
  11.000   1.3652   0.02561   0.02059  -0.0375   0.0020   1.0000
  11.250   1.3769   0.02688   0.02198  -0.0358   0.0020   1.0000
  11.500   1.3842   0.02826   0.02350  -0.0335   0.0019   1.0000
  11.750   1.3860   0.02998   0.02537  -0.0307   0.0019   1.0000
  12.000   1.3851   0.03217   0.02777  -0.0283   0.0018   1.0000
  12.250   1.3785   0.03523   0.03107  -0.0262   0.0018   1.0000
  12.500   1.3704   0.03872   0.03480  -0.0246   0.0017   1.0000
  12.750   1.3658   0.04195   0.03824  -0.0239   0.0017   1.0000
  13.000   1.3617   0.04528   0.04176  -0.0237   0.0017   1.0000
  13.250   1.3531   0.04939   0.04607  -0.0238   0.0017   1.0000
  13.500   1.3418   0.05405   0.05094  -0.0245   0.0017   1.0000
  13.750   1.3273   0.05940   0.05650  -0.0258   0.0017   1.0000
  14.000   1.3112   0.06521   0.06250  -0.0276   0.0017   1.0000
  14.250   1.2920   0.07186   0.06933  -0.0302   0.0017   1.0000
  14.500   1.2717   0.07898   0.07663  -0.0332   0.0017   1.0000
  14.750   1.2497   0.08698   0.08480  -0.0370   0.0017   1.0000
  15.000   1.2261   0.09587   0.09385  -0.0416   0.0017   1.0000
  15.250   1.2026   0.10537   0.10350  -0.0467   0.0017   1.0000
  15.500   1.1792   0.11551   0.11377  -0.0522   0.0017   1.0000
  15.750   1.1512   0.12752   0.12590  -0.0587   0.0017   1.0000
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