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NACA M26 AIRFOIL (m26-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA M26 AIRFOIL (m26-il)
Reynolds number: 1,000,000
Max Cl/Cd: 113.71 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m26-il-1000000-n5.txt
Download as CSV file: xf-m26-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M26 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3094   0.10918   0.10604   0.0138   0.4967   0.0040
  -8.250  -0.3036   0.10565   0.10251   0.0120   0.4957   0.0040
  -8.000  -0.2988   0.10177   0.09865   0.0099   0.4947   0.0042
  -7.750  -0.2926   0.09863   0.09551   0.0077   0.4938   0.0044
  -7.500  -0.2849   0.09617   0.09304   0.0058   0.4928   0.0045
  -7.250  -0.2725   0.09344   0.09031   0.0032   0.4917   0.0046
  -7.000  -0.2597   0.09017   0.08703   0.0003   0.4908   0.0047
  -6.750  -0.2454   0.08681   0.08365  -0.0029   0.4898   0.0048
  -6.500  -0.2296   0.08345   0.08026  -0.0060   0.4888   0.0049
  -6.250  -0.2124   0.07995   0.07674  -0.0093   0.4878   0.0052
  -6.000  -0.1938   0.07609   0.07284  -0.0129   0.4868   0.0055
  -5.750  -0.1734   0.07088   0.06758  -0.0175   0.4860   0.0061
  -5.500  -0.1516   0.06777   0.06444  -0.0204   0.4854   0.0064
  -5.250  -0.1291   0.06554   0.06218  -0.0227   0.4846   0.0067
  -5.000  -0.1056   0.06294   0.05953  -0.0252   0.4839   0.0071
  -4.750  -0.0805   0.05941   0.05595  -0.0282   0.4830   0.0077
  -4.500  -0.0526   0.05440   0.05083  -0.0320   0.4821   0.0086
  -4.250  -0.0273   0.05252   0.04890  -0.0337   0.4810   0.0089
  -4.000  -0.0016   0.05067   0.04701  -0.0353   0.4799   0.0094
  -3.750   0.0256   0.04812   0.04438  -0.0373   0.4788   0.0103
  -3.500   0.0563   0.04371   0.03983  -0.0398   0.4780   0.0115
  -3.250   0.0827   0.04226   0.03832  -0.0410   0.4770   0.0118
  -3.000   0.1096   0.04080   0.03679  -0.0421   0.4760   0.0124
  -2.750   0.1378   0.03874   0.03465  -0.0433   0.4750   0.0134
  -2.500   0.1708   0.03462   0.03032  -0.0447   0.4741   0.0150
  -2.250   0.1971   0.03369   0.02934  -0.0454   0.4730   0.0153
  -2.000   0.2241   0.03264   0.02821  -0.0461   0.4716   0.0158
  -1.750   0.2524   0.03110   0.02660  -0.0468   0.4708   0.0165
  -1.500   0.2815   0.02931   0.02470  -0.0474   0.4701   0.0172
  -1.250   0.3113   0.02732   0.02258  -0.0478   0.4693   0.0178
  -1.000   0.3436   0.02454   0.01959  -0.0479   0.4686   0.0196
  -0.750   0.3706   0.02377   0.01877  -0.0483   0.4677   0.0199
  -0.500   0.3985   0.02278   0.01772  -0.0487   0.4666   0.0203
  -0.250   0.4269   0.02170   0.01655  -0.0490   0.4655   0.0207
   0.000   0.4560   0.02035   0.01508  -0.0491   0.4641   0.0208
   0.250   0.4849   0.01918   0.01379  -0.0492   0.4624   0.0212
   0.500   0.5141   0.01775   0.01219  -0.0492   0.4603   0.0212
   0.750   0.5435   0.01607   0.01030  -0.0490   0.4583   0.0212
   1.000   0.5725   0.01459   0.00863  -0.0488   0.4566   0.0220
   1.250   0.6013   0.01309   0.00694  -0.0487   0.4557   0.0230
   1.500   0.6299   0.01221   0.00591  -0.0487   0.4545   0.0233
   1.750   0.6584   0.01162   0.00522  -0.0489   0.4533   0.0234
   2.000   0.6870   0.01119   0.00472  -0.0491   0.4520   0.0236
   2.250   0.7155   0.01094   0.00443  -0.0494   0.4504   0.0240
   2.500   0.7438   0.01056   0.00398  -0.0496   0.4488   0.0240
   2.750   0.7719   0.01024   0.00362  -0.0498   0.4472   0.0240
   3.000   0.7998   0.00999   0.00334  -0.0499   0.4458   0.0240
   3.250   0.8276   0.00982   0.00314  -0.0501   0.4442   0.0241
   3.500   0.8554   0.00970   0.00301  -0.0503   0.4423   0.0243
   3.750   0.8834   0.00961   0.00293  -0.0506   0.4409   0.0246
   4.000   0.9116   0.00955   0.00291  -0.0509   0.4394   0.0249
   4.250   0.9388   0.00934   0.00270  -0.0509   0.4378   0.0267
   4.500   0.9670   0.00930   0.00268  -0.0513   0.4351   0.0277
   4.750   0.9951   0.00931   0.00266  -0.0516   0.4282   0.0284
   5.000   1.0233   0.00930   0.00267  -0.0520   0.4191   0.0290
   5.250   1.0513   0.00936   0.00271  -0.0524   0.4089   0.0300
   5.500   1.0791   0.00949   0.00279  -0.0528   0.3921   0.0310
   5.750   1.1059   0.00987   0.00302  -0.0533   0.3614   0.0313
   6.000   1.1306   0.01074   0.00360  -0.0538   0.3097   0.0317
   6.250   1.1544   0.01168   0.00427  -0.0542   0.2602   0.0324
   6.500   1.1609   0.01532   0.00693  -0.0542   0.0732   0.0331
   6.750   1.1799   0.01645   0.00791  -0.0541   0.0183   0.0440
   7.000   1.2036   0.01681   0.00842  -0.0541   0.0141   0.1347
   7.500   1.2528   0.01652   0.00965  -0.0549   0.0115   0.9895
   7.750   1.3215   0.01761   0.01079  -0.0655   0.0089   1.0000
   8.000   1.3375   0.01820   0.01141  -0.0644   0.0085   1.0000
   8.250   1.3512   0.01888   0.01213  -0.0630   0.0079   1.0000
   8.500   1.3619   0.01976   0.01304  -0.0615   0.0073   1.0000
   8.750   1.3628   0.02117   0.01451  -0.0594   0.0069   1.0000
   9.000   1.3607   0.02283   0.01622  -0.0569   0.0066   1.0000
   9.250   1.3636   0.02480   0.01824  -0.0559   0.0062   1.0000
   9.500   1.3671   0.02696   0.02048  -0.0553   0.0059   1.0000
   9.750   1.3730   0.02895   0.02253  -0.0548   0.0057   1.0000
  10.000   1.3774   0.03112   0.02477  -0.0544   0.0055   1.0000
  10.250   1.3806   0.03343   0.02714  -0.0539   0.0053   1.0000
  10.500   1.3830   0.03582   0.02960  -0.0534   0.0051   1.0000
  10.750   1.3845   0.03830   0.03214  -0.0530   0.0049   1.0000
  11.000   1.3857   0.04081   0.03472  -0.0525   0.0047   1.0000
  11.250   1.3873   0.04327   0.03723  -0.0520   0.0046   1.0000
  11.500   1.3886   0.04576   0.03977  -0.0516   0.0044   1.0000
  11.750   1.3880   0.04849   0.04255  -0.0511   0.0042   1.0000
  12.000   1.3851   0.05157   0.04570  -0.0507   0.0040   1.0000
  12.250   1.3819   0.05473   0.04893  -0.0504   0.0039   1.0000
  12.500   1.3816   0.05764   0.05191  -0.0501   0.0038   1.0000
  12.750   1.3816   0.06052   0.05486  -0.0499   0.0037   1.0000
  13.000   1.3803   0.06361   0.05803  -0.0497   0.0036   1.0000
  13.250   1.3793   0.06669   0.06118  -0.0496   0.0035   1.0000
  13.500   1.3775   0.06993   0.06450  -0.0495   0.0034   1.0000
  13.750   1.3761   0.07310   0.06775  -0.0494   0.0033   1.0000
  14.000   1.3739   0.07644   0.07115  -0.0494   0.0032   1.0000
  14.250   1.3731   0.07962   0.07440  -0.0494   0.0032   1.0000
  14.500   1.3713   0.08300   0.07785  -0.0495   0.0031   1.0000
  14.750   1.3710   0.08612   0.08104  -0.0496   0.0030   1.0000
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