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MH 26 10.99% (mh26-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 26 10.99% (mh26-il)
Reynolds number: 50,000
Max Cl/Cd: 31.98 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh26-il-50000-n5.txt
Download as CSV file: xf-mh26-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 26  10.99%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4949   0.10455   0.09765  -0.0422   1.0000   0.0349
  -9.750  -0.4975   0.10120   0.09435  -0.0416   1.0000   0.0344
  -9.500  -0.5039   0.09732   0.09053  -0.0420   1.0000   0.0340
  -9.250  -0.5130   0.09312   0.08639  -0.0428   1.0000   0.0335
  -9.000  -0.5240   0.08924   0.08257  -0.0434   1.0000   0.0331
  -8.750  -0.5395   0.08564   0.07900  -0.0429   1.0000   0.0327
  -8.500  -0.5575   0.08262   0.07600  -0.0410   1.0000   0.0324
  -8.250  -0.5774   0.08001   0.07340  -0.0378   1.0000   0.0321
  -8.000  -0.5956   0.07687   0.07024  -0.0348   1.0000   0.0319
  -7.750  -0.6081   0.07392   0.06723  -0.0319   1.0000   0.0314
  -7.500  -0.6217   0.07046   0.06366  -0.0287   1.0000   0.0311
  -7.250  -0.6306   0.06732   0.06038  -0.0256   1.0000   0.0306
  -7.000  -0.6387   0.06389   0.05677  -0.0222   1.0000   0.0303
  -6.750  -0.6438   0.06053   0.05317  -0.0189   1.0000   0.0300
  -6.500  -0.6459   0.05722   0.04958  -0.0156   1.0000   0.0296
  -6.250  -0.6458   0.05384   0.04587  -0.0122   1.0000   0.0295
  -6.000  -0.6425   0.05065   0.04232  -0.0089   1.0000   0.0293
  -5.750  -0.6362   0.04762   0.03889  -0.0058   1.0000   0.0292
  -5.500  -0.6273   0.04466   0.03550  -0.0028   1.0000   0.0293
  -5.250  -0.6152   0.04194   0.03224  -0.0001   1.0000   0.0294
  -5.000  -0.6002   0.03943   0.02927   0.0023   1.0000   0.0301
  -4.750  -0.5825   0.03727   0.02663   0.0044   1.0000   0.0324
  -4.500  -0.5622   0.03544   0.02428   0.0064   1.0000   0.0346
  -4.250  -0.5413   0.03332   0.02196   0.0077   1.0000   0.0375
  -4.000  -0.5185   0.03166   0.02010   0.0090   1.0000   0.0401
  -3.750  -0.4940   0.03018   0.01838   0.0102   1.0000   0.0437
  -3.500  -0.4704   0.02890   0.01695   0.0112   1.0000   0.0528
  -3.250  -0.4465   0.02774   0.01563   0.0122   1.0000   0.0644
  -3.000  -0.4239   0.02646   0.01443   0.0132   1.0000   0.0970
  -2.750  -0.1597   0.02578   0.01627  -0.0267   1.0000   1.0000
  -2.500  -0.1500   0.02557   0.01581  -0.0241   1.0000   1.0000
  -2.250  -0.1397   0.02541   0.01536  -0.0217   1.0000   1.0000
  -2.000  -0.1290   0.02529   0.01504  -0.0193   1.0000   1.0000
  -1.750  -0.1179   0.02522   0.01476  -0.0169   1.0000   1.0000
  -1.500  -0.1066   0.02518   0.01453  -0.0145   1.0000   1.0000
  -1.250  -0.0951   0.02517   0.01437  -0.0121   1.0000   1.0000
  -1.000  -0.0835   0.02520   0.01424  -0.0098   1.0000   1.0000
  -0.750  -0.0718   0.02526   0.01413  -0.0075   1.0000   1.0000
  -0.500  -0.0600   0.02535   0.01410  -0.0053   1.0000   1.0000
  -0.250  -0.0481   0.02547   0.01411  -0.0031   1.0000   1.0000
   0.000  -0.0233   0.02574   0.01425  -0.0035   0.9962   1.0000
   0.250   0.0137   0.02613   0.01451  -0.0064   0.9881   1.0000
   0.500   0.0504   0.02656   0.01484  -0.0092   0.9798   1.0000
   0.750   0.0878   0.02699   0.01521  -0.0120   0.9713   1.0000
   1.000   0.1215   0.02729   0.01548  -0.0140   0.9613   1.0000
   1.250   0.1556   0.02760   0.01577  -0.0161   0.9513   1.0000
   1.500   0.1917   0.02793   0.01610  -0.0185   0.9416   1.0000
   1.750   0.2278   0.02820   0.01639  -0.0208   0.9314   1.0000
   2.000   0.2597   0.02835   0.01660  -0.0221   0.9193   1.0000
   2.250   0.2916   0.02847   0.01679  -0.0234   0.9069   1.0000
   2.500   0.3236   0.02853   0.01693  -0.0246   0.8940   1.0000
   2.750   0.3550   0.02852   0.01702  -0.0256   0.8804   1.0000
   3.000   0.3866   0.02844   0.01705  -0.0264   0.8662   1.0000
   3.250   0.4188   0.02827   0.01708  -0.0273   0.8515   1.0000
   3.500   0.4433   0.02809   0.01703  -0.0266   0.8338   1.0000
   3.750   0.4715   0.02784   0.01695  -0.0264   0.8162   1.0000
   4.000   0.5050   0.02742   0.01678  -0.0269   0.7993   1.0000
   4.250   0.5329   0.02701   0.01656  -0.0263   0.7797   1.0000
   4.500   0.5642   0.02642   0.01619  -0.0260   0.7596   1.0000
   4.750   0.5936   0.02586   0.01585  -0.0253   0.7361   1.0000
   5.000   0.6270   0.02522   0.01544  -0.0250   0.7086   1.0000
   5.250   0.6693   0.02446   0.01497  -0.0261   0.6735   1.0000
   5.500   0.7114   0.02394   0.01458  -0.0273   0.6246   1.0000
   5.750   0.7500   0.02378   0.01438  -0.0280   0.5629   1.0000
   6.000   0.7713   0.02412   0.01458  -0.0260   0.5019   1.0000
   6.250   0.7847   0.02472   0.01498  -0.0229   0.4443   1.0000
   6.500   0.7933   0.02546   0.01562  -0.0193   0.3908   1.0000
   6.750   0.7995   0.02630   0.01625  -0.0154   0.3418   1.0000
   7.000   0.8041   0.02720   0.01698  -0.0113   0.2956   1.0000
   7.250   0.8087   0.02818   0.01779  -0.0074   0.2534   1.0000
   7.500   0.8135   0.02925   0.01871  -0.0038   0.2141   1.0000
   7.750   0.8190   0.03043   0.01972  -0.0004   0.1799   1.0000
   8.000   0.8257   0.03172   0.02087   0.0027   0.1499   1.0000
   8.250   0.8338   0.03312   0.02219   0.0056   0.1252   1.0000
   8.500   0.8434   0.03456   0.02364   0.0082   0.1032   1.0000
   8.750   0.8564   0.03620   0.02532   0.0104   0.0889   1.0000
   9.000   0.8669   0.03774   0.02694   0.0128   0.0763   1.0000
   9.250   0.8822   0.03958   0.02893   0.0145   0.0667   1.0000
   9.500   0.9023   0.04185   0.03130   0.0154   0.0603   1.0000
   9.750   0.9179   0.04410   0.03402   0.0172   0.0536   1.0000
  10.000   0.9221   0.04582   0.03574   0.0200   0.0488   1.0000
  10.250   0.9341   0.04889   0.03927   0.0220   0.0454   1.0000
  10.500   0.9380   0.05190   0.04271   0.0249   0.0435   1.0000
  10.750   0.9351   0.05491   0.04607   0.0283   0.0420   1.0000
  11.000   0.9280   0.05751   0.04893   0.0318   0.0403   1.0000
  11.250   0.9204   0.05990   0.05146   0.0348   0.0385   1.0000
  11.500   0.9131   0.06267   0.05431   0.0372   0.0371   1.0000
  11.750   0.8985   0.06603   0.05785   0.0397   0.0362   1.0000
  12.000   0.8811   0.06961   0.06168   0.0417   0.0360   1.0000
  12.250   0.8595   0.07376   0.06610   0.0427   0.0357   1.0000
  12.500   0.8402   0.07823   0.07075   0.0427   0.0358   1.0000
  12.750   0.8217   0.08325   0.07592   0.0417   0.0360   1.0000
  13.000   0.8027   0.08884   0.08161   0.0397   0.0363   1.0000
  13.250   0.7409   0.10526   0.09835   0.0289   0.0432   1.0000
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