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MH 122 9.32% (mh122-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 122 9.32% (mh122-il)
Reynolds number: 100,000
Max Cl/Cd: 61.08 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh122-il-100000.txt
Download as CSV file: xf-mh122-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 122  9.32%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4660   0.10446   0.10014  -0.0328   1.0000   0.0727
  -7.750  -0.4847   0.10303   0.09880  -0.0315   1.0000   0.0728
  -7.500  -0.5037   0.10072   0.09658  -0.0329   1.0000   0.0730
  -7.250  -0.4795   0.09584   0.09161  -0.0261   1.0000   0.0760
  -7.000  -0.4862   0.09382   0.08964  -0.0237   1.0000   0.0777
  -6.750  -0.4948   0.09153   0.08740  -0.0226   1.0000   0.0793
  -6.500  -0.5029   0.08851   0.08444  -0.0234   1.0000   0.0819
  -6.000  -0.5144   0.07723   0.07302  -0.0407   1.0000   0.0871
  -5.750  -0.5085   0.07558   0.07155  -0.0332   1.0000   0.0899
  -5.500  -0.5023   0.07215   0.06809  -0.0342   1.0000   0.0948
  -5.250  -0.4922   0.06597   0.06170  -0.0418   1.0000   0.1022
  -5.000  -0.4816   0.06327   0.05902  -0.0409   1.0000   0.1077
  -4.750  -0.4658   0.05866   0.05426  -0.0447   1.0000   0.1183
  -4.500  -0.4478   0.05481   0.05026  -0.0473   1.0000   0.1319
  -3.750  -0.3210   0.03550   0.02832  -0.0611   1.0000   0.0447
  -3.500  -0.2898   0.03194   0.02431  -0.0623   1.0000   0.0397
  -3.250  -0.2594   0.02962   0.02148  -0.0628   1.0000   0.0395
  -3.000  -0.2313   0.02812   0.01959  -0.0629   1.0000   0.0431
  -2.750  -0.2032   0.02664   0.01777  -0.0628   1.0000   0.0444
  -2.500  -0.1749   0.02526   0.01612  -0.0623   1.0000   0.0462
  -2.250  -0.1463   0.02355   0.01442  -0.0624   1.0000   0.0506
  -2.000  -0.1176   0.02260   0.01350  -0.0627   1.0000   0.0722
  -1.750  -0.0815   0.01983   0.01322  -0.0640   1.0000   0.6215
  -1.500  -0.0661   0.02010   0.01354  -0.0610   1.0000   0.6887
  -1.250  -0.0507   0.02031   0.01375  -0.0582   1.0000   0.7383
  -1.000  -0.0393   0.02043   0.01395  -0.0543   1.0000   0.7911
  -0.750  -0.0287   0.02043   0.01401  -0.0504   1.0000   0.8409
  -0.500  -0.0140   0.02033   0.01394  -0.0479   1.0000   0.8902
  -0.250   0.0093   0.01994   0.01347  -0.0487   1.0000   1.0000
   0.000   0.0443   0.02043   0.01367  -0.0521   1.0000   1.0000
   0.250   0.0825   0.02113   0.01410  -0.0557   0.9966   1.0000
   0.500   0.1257   0.02198   0.01472  -0.0600   0.9892   1.0000
   0.750   0.1694   0.02297   0.01548  -0.0641   0.9829   1.0000
   1.000   0.2040   0.02351   0.01590  -0.0665   0.9747   1.0000
   1.250   0.2426   0.02427   0.01655  -0.0695   0.9674   1.0000
   1.500   0.2787   0.02489   0.01709  -0.0720   0.9596   1.0000
   1.750   0.3116   0.02544   0.01758  -0.0738   0.9508   1.0000
   2.000   0.3515   0.02614   0.01825  -0.0768   0.9433   1.0000
   2.250   0.3853   0.02664   0.01873  -0.0787   0.9339   1.0000
   2.500   0.4176   0.02712   0.01925  -0.0802   0.9240   1.0000
   2.750   0.4550   0.02763   0.01978  -0.0825   0.9145   1.0000
   3.000   0.4981   0.02810   0.02030  -0.0857   0.9059   1.0000
   3.250   0.5310   0.02841   0.02068  -0.0870   0.8942   1.0000
   3.500   0.5669   0.02866   0.02102  -0.0887   0.8823   1.0000
   3.750   0.6053   0.02877   0.02132  -0.0906   0.8699   1.0000
   4.000   0.6473   0.02865   0.02136  -0.0927   0.8569   1.0000
   4.250   0.6958   0.02806   0.02096  -0.0954   0.8426   1.0000
   4.500   0.7560   0.02659   0.01982  -0.0989   0.8273   1.0000
   4.750   0.8204   0.02445   0.01801  -0.1025   0.8125   1.0000
   5.000   0.8612   0.02291   0.01676  -0.1025   0.7930   1.0000
   5.250   0.9233   0.01992   0.01426  -0.1046   0.7702   1.0000
   5.500   0.9540   0.01822   0.01282  -0.1021   0.7313   1.0000
   5.750   1.0029   0.01642   0.01026  -0.1010   0.5105   1.0000
   6.000   0.9939   0.01901   0.01122  -0.0943   0.2852   1.0000
   6.250   0.9939   0.02141   0.01269  -0.0898   0.1832   1.0000
   6.500   1.0031   0.02331   0.01417  -0.0868   0.1395   1.0000
   6.750   1.0205   0.02541   0.01601  -0.0851   0.1119   1.0000
   7.000   1.0415   0.02713   0.01768  -0.0840   0.0888   1.0000
   7.250   1.0779   0.03018   0.02067  -0.0852   0.0715   1.0000
   7.500   1.1067   0.03277   0.02344  -0.0851   0.0572   1.0000
   7.750   1.1317   0.03565   0.02663  -0.0845   0.0460   1.0000
   8.000   1.1579   0.03899   0.03034  -0.0835   0.0401   1.0000
   8.250   1.1766   0.04407   0.03576  -0.0824   0.0363   1.0000
   8.500   1.1856   0.04642   0.03878  -0.0788   0.0334   1.0000
   8.750   1.1928   0.05043   0.04333  -0.0755   0.0325   1.0000
   9.000   1.1944   0.05488   0.04829  -0.0719   0.0329   1.0000
   9.250   1.1914   0.05936   0.05320  -0.0681   0.0336   1.0000
   9.500   1.1844   0.06380   0.05800  -0.0643   0.0343   1.0000
   9.750   1.1743   0.06809   0.06256  -0.0607   0.0350   1.0000
  10.000   1.1614   0.07242   0.06709  -0.0572   0.0357   1.0000
  10.250   1.0612   0.07048   0.06573  -0.0454   0.0356   1.0000
  10.500   1.0528   0.07842   0.07373  -0.0448   0.0369   1.0000
  10.750   1.0336   0.08115   0.07669  -0.0424   0.0373   1.0000
  11.000   1.0062   0.08508   0.08090  -0.0412   0.0379   1.0000
  11.250   0.9724   0.09070   0.08676  -0.0417   0.0383   1.0000
  11.500   0.9335   0.09762   0.09391  -0.0446   0.0388   1.0000
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