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MH 70 11.08% (mh70-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: MH 70 11.08% (mh70-il)
Reynolds number: 500,000
Max Cl/Cd: 87.91 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh70-il-500000-n5.txt
Download as CSV file: xf-mh70-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 70  11.08%                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5376   0.04082   0.03820  -0.0625   0.9116   0.0046
  -8.750  -0.5588   0.03324   0.02997  -0.0631   0.8829   0.0046
  -8.500  -0.5627   0.02772   0.02374  -0.0621   0.8663   0.0046
  -8.250  -0.5518   0.02452   0.02004  -0.0611   0.8539   0.0047
  -8.000  -0.5347   0.02239   0.01749  -0.0602   0.8436   0.0048
  -7.750  -0.5155   0.02059   0.01534  -0.0593   0.8340   0.0048
  -7.500  -0.4947   0.01907   0.01357  -0.0587   0.8250   0.0051
  -7.250  -0.4716   0.01811   0.01243  -0.0581   0.8166   0.0052
  -7.000  -0.4472   0.01733   0.01150  -0.0577   0.8081   0.0054
  -6.750  -0.4227   0.01656   0.01056  -0.0572   0.8003   0.0056
  -6.500  -0.3977   0.01580   0.00966  -0.0568   0.7923   0.0057
  -6.250  -0.3726   0.01510   0.00879  -0.0563   0.7850   0.0060
  -6.000  -0.3470   0.01444   0.00802  -0.0559   0.7773   0.0062
  -5.500  -0.2951   0.01330   0.00663  -0.0551   0.7628   0.0066
  -5.250  -0.2688   0.01284   0.00607  -0.0548   0.7556   0.0069
  -5.000  -0.2423   0.01241   0.00559  -0.0545   0.7487   0.0075
  -4.750  -0.2155   0.01206   0.00518  -0.0543   0.7414   0.0081
  -4.500  -0.1885   0.01171   0.00474  -0.0540   0.7346   0.0087
  -4.250  -0.1614   0.01134   0.00429  -0.0538   0.7272   0.0092
  -4.000  -0.1344   0.01098   0.00386  -0.0535   0.7205   0.0100
  -3.750  -0.1068   0.01069   0.00351  -0.0533   0.7131   0.0115
  -3.500  -0.0795   0.01042   0.00319  -0.0531   0.7061   0.0135
  -3.250  -0.0518   0.01017   0.00292  -0.0529   0.6984   0.0182
  -3.000  -0.0245   0.00993   0.00268  -0.0527   0.6911   0.0280
  -2.750   0.0029   0.00964   0.00247  -0.0526   0.6833   0.0487
  -2.500   0.0299   0.00932   0.00227  -0.0524   0.6754   0.0872
  -2.250   0.0570   0.00898   0.00211  -0.0523   0.6672   0.1412
  -2.000   0.0840   0.00871   0.00198  -0.0522   0.6588   0.1967
  -1.750   0.1115   0.00849   0.00188  -0.0521   0.6498   0.2413
  -1.500   0.1388   0.00829   0.00180  -0.0520   0.6410   0.2952
  -1.250   0.1659   0.00805   0.00173  -0.0519   0.6313   0.3601
  -1.000   0.1932   0.00789   0.00168  -0.0517   0.6218   0.4096
  -0.750   0.2204   0.00775   0.00163  -0.0515   0.6115   0.4606
  -0.500   0.2475   0.00760   0.00160  -0.0513   0.6004   0.5135
  -0.250   0.2743   0.00745   0.00158  -0.0511   0.5891   0.5721
   0.000   0.3007   0.00730   0.00158  -0.0507   0.5775   0.6356
   0.250   0.3265   0.00716   0.00159  -0.0501   0.5649   0.7030
   0.500   0.3516   0.00703   0.00162  -0.0493   0.5519   0.7702
   0.750   0.3762   0.00693   0.00167  -0.0483   0.5388   0.8333
   1.000   0.4009   0.00691   0.00172  -0.0473   0.5247   0.8894
   1.250   0.4304   0.00695   0.00175  -0.0473   0.5103   0.9328
   1.500   0.4663   0.00705   0.00178  -0.0489   0.4948   0.9617
   1.750   0.5033   0.00718   0.00181  -0.0508   0.4783   0.9814
   2.000   0.5403   0.00731   0.00186  -0.0528   0.4613   0.9952
   2.250   0.5705   0.00747   0.00192  -0.0534   0.4458   1.0000
   2.500   0.5957   0.00763   0.00199  -0.0528   0.4306   1.0000
   2.750   0.6211   0.00780   0.00208  -0.0523   0.4154   1.0000
   3.000   0.6466   0.00798   0.00219  -0.0519   0.4000   1.0000
   3.250   0.6722   0.00817   0.00230  -0.0515   0.3845   1.0000
   3.500   0.6979   0.00837   0.00242  -0.0511   0.3691   1.0000
   3.750   0.7236   0.00858   0.00256  -0.0507   0.3530   1.0000
   4.000   0.7494   0.00879   0.00271  -0.0503   0.3387   1.0000
   4.250   0.7750   0.00902   0.00287  -0.0500   0.3235   1.0000
   4.500   0.8007   0.00926   0.00304  -0.0497   0.3086   1.0000
   4.750   0.8263   0.00950   0.00323  -0.0493   0.2945   1.0000
   5.000   0.8518   0.00975   0.00342  -0.0490   0.2802   1.0000
   5.250   0.8774   0.01000   0.00363  -0.0486   0.2679   1.0000
   5.500   0.9028   0.01027   0.00385  -0.0483   0.2554   1.0000
   5.750   0.9279   0.01056   0.00408  -0.0479   0.2425   1.0000
   6.250   0.9782   0.01113   0.00458  -0.0472   0.2192   1.0000
   6.500   1.0031   0.01142   0.00485  -0.0468   0.2087   1.0000
   6.750   1.0277   0.01174   0.00513  -0.0464   0.1986   1.0000
   7.000   1.0522   0.01206   0.00543  -0.0460   0.1882   1.0000
   7.250   1.0767   0.01237   0.00574  -0.0456   0.1788   1.0000
   7.500   1.1006   0.01273   0.00606  -0.0451   0.1696   1.0000
   7.750   1.1243   0.01309   0.00641  -0.0446   0.1603   1.0000
   8.000   1.1481   0.01343   0.00676  -0.0441   0.1520   1.0000
   8.250   1.1710   0.01384   0.00714  -0.0435   0.1439   1.0000
   8.500   1.1941   0.01420   0.00751  -0.0429   0.1360   1.0000
   8.750   1.2165   0.01462   0.00793  -0.0423   0.1283   1.0000
   9.000   1.2384   0.01506   0.00836  -0.0416   0.1205   1.0000
   9.250   1.2601   0.01548   0.00880  -0.0408   0.1138   1.0000
   9.500   1.2807   0.01598   0.00929  -0.0400   0.1066   1.0000
   9.750   1.3015   0.01642   0.00977  -0.0391   0.1005   1.0000
  10.000   1.3203   0.01699   0.01031  -0.0380   0.0934   1.0000
  10.250   1.3398   0.01747   0.01083  -0.0370   0.0878   1.0000
  10.500   1.3565   0.01809   0.01145  -0.0357   0.0813   1.0000
  10.750   1.3735   0.01863   0.01203  -0.0343   0.0760   1.0000
  11.000   1.3859   0.01929   0.01269  -0.0323   0.0709   1.0000
  11.250   1.3991   0.01990   0.01335  -0.0304   0.0667   1.0000
  11.500   1.4099   0.02067   0.01414  -0.0284   0.0620   1.0000
  11.750   1.4209   0.02147   0.01499  -0.0266   0.0578   1.0000
  12.000   1.4308   0.02239   0.01594  -0.0249   0.0534   1.0000
  12.250   1.4400   0.02341   0.01700  -0.0233   0.0497   1.0000
  12.500   1.4492   0.02449   0.01812  -0.0218   0.0460   1.0000
  12.750   1.4563   0.02578   0.01944  -0.0204   0.0427   1.0000
  13.000   1.4651   0.02700   0.02073  -0.0192   0.0399   1.0000
  13.250   1.4714   0.02847   0.02226  -0.0180   0.0371   1.0000
  13.500   1.4775   0.03004   0.02389  -0.0170   0.0348   1.0000
  13.750   1.4835   0.03167   0.02559  -0.0161   0.0325   1.0000
  14.000   1.4874   0.03356   0.02754  -0.0153   0.0304   1.0000
  14.250   1.4907   0.03556   0.02962  -0.0146   0.0287   1.0000
  14.500   1.4944   0.03762   0.03177  -0.0142   0.0269   1.0000
  14.750   1.4956   0.03999   0.03421  -0.0138   0.0254   1.0000
  15.000   1.4944   0.04272   0.03701  -0.0137   0.0239   1.0000
  15.250   1.4955   0.04528   0.03969  -0.0137   0.0227   1.0000
  15.500   1.4942   0.04821   0.04272  -0.0139   0.0215   1.0000
  15.750   1.4908   0.05150   0.04610  -0.0143   0.0204   1.0000
  16.000   1.4852   0.05523   0.04992  -0.0151   0.0195   1.0000
  16.250   1.4823   0.05877   0.05358  -0.0159   0.0186   1.0000
  16.500   1.4771   0.06277   0.05769  -0.0171   0.0178   1.0000
  16.750   1.4693   0.06725   0.06227  -0.0186   0.0166   1.0000
  17.000   1.4598   0.07218   0.06731  -0.0204   0.0160   1.0000
  17.250   1.4502   0.07728   0.07253  -0.0224   0.0156   1.0000
  17.500   1.4410   0.08246   0.07784  -0.0246   0.0149   1.0000
  17.750   1.4307   0.08794   0.08345  -0.0270   0.0144   1.0000
  18.000   1.4178   0.09401   0.08963  -0.0298   0.0137   1.0000
  18.250   1.4042   0.10032   0.09607  -0.0328   0.0135   1.0000
  18.500   1.3893   0.10702   0.10289  -0.0361   0.0131   1.0000
  18.750   1.3736   0.11403   0.11002  -0.0397   0.0127   1.0000
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