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MH 116 9.84% (mh116-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 116 9.84% (mh116-il)
Reynolds number: 50,000
Max Cl/Cd: 39.39 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh116-il-50000-n5.txt
Download as CSV file: xf-mh116-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 116  9.84%                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3442   0.09962   0.09305  -0.0434   1.0000   0.0403
  -8.250  -0.3477   0.09707   0.09060  -0.0422   1.0000   0.0398
  -8.000  -0.3542   0.09478   0.08842  -0.0408   1.0000   0.0393
  -7.750  -0.3640   0.09264   0.08640  -0.0390   1.0000   0.0389
  -7.500  -0.3764   0.09077   0.08465  -0.0369   1.0000   0.0385
  -7.250  -0.3895   0.08891   0.08292  -0.0349   1.0000   0.0381
  -7.000  -0.4005   0.08646   0.08057  -0.0341   1.0000   0.0377
  -6.750  -0.4099   0.08371   0.07792  -0.0339   1.0000   0.0373
  -6.500  -0.4177   0.08048   0.07476  -0.0344   1.0000   0.0370
  -6.250  -0.4224   0.07699   0.07132  -0.0356   1.0000   0.0364
  -6.000  -0.4105   0.07118   0.06546  -0.0419   0.9957   0.0359
  -5.750  -0.3869   0.06363   0.05773  -0.0512   0.9883   0.0353
  -5.500  -0.3593   0.05603   0.04978  -0.0602   0.9818   0.0349
  -5.250  -0.3313   0.04952   0.04277  -0.0670   0.9751   0.0358
  -5.000  -0.2962   0.04348   0.03598  -0.0734   0.9701   0.0380
  -4.750  -0.2623   0.03853   0.02990  -0.0773   0.9646   0.0410
  -4.500  -0.2306   0.03560   0.02670  -0.0798   0.9597   0.0440
  -4.250  -0.1945   0.03306   0.02358  -0.0821   0.9555   0.0505
  -4.000  -0.1646   0.03122   0.02143  -0.0831   0.9494   0.0597
  -3.750  -0.1297   0.02963   0.01951  -0.0848   0.9447   0.0757
  -3.500  -0.0981   0.02827   0.01796  -0.0856   0.9392   0.0959
  -3.250  -0.0666   0.02729   0.01684  -0.0866   0.9333   0.1243
  -3.000  -0.0298   0.02651   0.01602  -0.0887   0.9290   0.1666
  -2.750  -0.0026   0.02595   0.01545  -0.0890   0.9217   0.2087
  -2.500   0.0327   0.02541   0.01496  -0.0908   0.9167   0.2645
  -2.250   0.0611   0.02501   0.01468  -0.0913   0.9098   0.3249
  -2.000   0.0933   0.02459   0.01440  -0.0924   0.9042   0.4039
  -1.750   0.1215   0.02419   0.01431  -0.0925   0.8980   0.4982
  -1.500   0.1458   0.02379   0.01430  -0.0914   0.8914   0.6157
  -1.250   0.1665   0.02333   0.01426  -0.0888   0.8854   0.7763
  -0.750   0.2383   0.02334   0.01376  -0.0920   0.8724   1.0000
  -0.250   0.3009   0.02385   0.01370  -0.0940   0.8587   1.0000
   0.250   0.3607   0.02440   0.01383  -0.0954   0.8444   1.0000
   0.500   0.3867   0.02473   0.01401  -0.0954   0.8359   1.0000
   0.750   0.4179   0.02499   0.01412  -0.0962   0.8292   1.0000
   1.000   0.4465   0.02529   0.01430  -0.0966   0.8214   1.0000
   1.250   0.4742   0.02561   0.01453  -0.0968   0.8135   1.0000
   1.500   0.5063   0.02582   0.01468  -0.0976   0.8066   1.0000
   1.750   0.5308   0.02620   0.01501  -0.0973   0.7975   1.0000
   2.000   0.5661   0.02629   0.01506  -0.0984   0.7915   1.0000
   2.250   0.5884   0.02672   0.01547  -0.0977   0.7812   1.0000
   2.500   0.6188   0.02691   0.01565  -0.0981   0.7736   1.0000
   2.750   0.6477   0.02711   0.01589  -0.0982   0.7650   1.0000
   3.000   0.6716   0.02747   0.01627  -0.0976   0.7547   1.0000
   3.250   0.7066   0.02743   0.01627  -0.0984   0.7478   1.0000
   3.500   0.7312   0.02771   0.01661  -0.0978   0.7371   1.0000
   3.750   0.7551   0.02802   0.01704  -0.0971   0.7261   1.0000
   4.000   0.7829   0.02816   0.01727  -0.0968   0.7159   1.0000
   4.250   0.8182   0.02795   0.01716  -0.0973   0.7076   1.0000
   4.750   0.8670   0.02833   0.01782  -0.0955   0.6827   1.0000
   5.000   0.8930   0.02840   0.01803  -0.0947   0.6698   1.0000
   5.250   0.9197   0.02840   0.01818  -0.0940   0.6564   1.0000
   5.500   0.9468   0.02834   0.01827  -0.0931   0.6422   1.0000
   5.750   0.9743   0.02820   0.01835  -0.0923   0.6270   1.0000
   6.000   1.0030   0.02796   0.01828  -0.0914   0.6107   1.0000
   6.250   1.0234   0.02810   0.01859  -0.0897   0.5911   1.0000
   6.500   1.0482   0.02798   0.01863  -0.0883   0.5706   1.0000
   6.750   1.0686   0.02808   0.01888  -0.0864   0.5472   1.0000
   7.000   1.0899   0.02813   0.01913  -0.0846   0.5217   1.0000
   7.250   1.1092   0.02831   0.01941  -0.0826   0.4932   1.0000
   7.500   1.1269   0.02861   0.01978  -0.0804   0.4618   1.0000
   7.750   1.1435   0.02903   0.02018  -0.0781   0.4280   1.0000
   8.000   1.1553   0.02974   0.02088  -0.0754   0.3930   1.0000
   8.250   1.1651   0.03063   0.02166  -0.0725   0.3583   1.0000
   8.500   1.1720   0.03179   0.02276  -0.0696   0.3244   1.0000
   8.750   1.1776   0.03314   0.02409  -0.0667   0.2927   1.0000
   9.000   1.1820   0.03468   0.02555  -0.0640   0.2632   1.0000
   9.250   1.1857   0.03637   0.02719  -0.0615   0.2360   1.0000
   9.500   1.1888   0.03822   0.02900  -0.0592   0.2104   1.0000
   9.750   1.1919   0.04019   0.03095  -0.0571   0.1876   1.0000
  10.000   1.1936   0.04233   0.03303  -0.0551   0.1671   1.0000
  10.250   1.1961   0.04459   0.03532  -0.0533   0.1472   1.0000
  10.500   1.1971   0.04702   0.03775  -0.0517   0.1295   1.0000
  10.750   1.1976   0.04961   0.04032  -0.0503   0.1141   1.0000
  11.000   1.1973   0.05237   0.04308  -0.0491   0.1001   1.0000
  11.250   1.1976   0.05526   0.04602  -0.0480   0.0875   1.0000
  11.500   1.1980   0.05825   0.04913  -0.0471   0.0763   1.0000
  11.750   1.2011   0.06131   0.05235  -0.0460   0.0667   1.0000
  12.000   1.2017   0.06455   0.05577  -0.0453   0.0594   1.0000
  12.250   1.2010   0.06791   0.05927  -0.0449   0.0532   1.0000
  12.500   1.2058   0.07130   0.06287  -0.0440   0.0482   1.0000
  12.750   1.2054   0.07510   0.06695  -0.0438   0.0439   1.0000
  13.000   1.2018   0.07886   0.07073  -0.0440   0.0408   1.0000
  13.250   1.1978   0.08339   0.07554  -0.0444   0.0382   1.0000
  13.500   1.1912   0.08851   0.08104  -0.0451   0.0364   1.0000
  13.750   1.1821   0.09405   0.08690  -0.0465   0.0353   1.0000
  14.000   1.1704   0.10010   0.09322  -0.0486   0.0346   1.0000
  14.250   1.1563   0.10678   0.10017  -0.0515   0.0342   1.0000
  14.500   1.1403   0.11429   0.10792  -0.0553   0.0342   1.0000
  14.750   1.1219   0.12291   0.11676  -0.0602   0.0346   1.0000
  15.000   1.1014   0.13285   0.12691  -0.0664   0.0354   1.0000
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