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MH 32 8.7% (mh32-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: MH 32 8.7% (mh32-il)
Reynolds number: 1,000,000
Max Cl/Cd: 109.26 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh32-il-1000000.txt
Download as CSV file: xf-mh32-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 32  8.7%                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4198   0.08303   0.08146  -0.0290   1.0000   0.0063
  -8.250  -0.4210   0.07921   0.07767  -0.0307   1.0000   0.0065
  -8.000  -0.4239   0.07554   0.07402  -0.0322   1.0000   0.0065
  -7.750  -0.4324   0.07201   0.07054  -0.0332   1.0000   0.0065
  -7.500  -0.4479   0.06893   0.06752  -0.0334   1.0000   0.0064
  -7.250  -0.4268   0.06021   0.05874  -0.0473   0.9942   0.0066
  -7.000  -0.4047   0.05174   0.05014  -0.0580   0.9877   0.0067
  -6.750  -0.3796   0.04352   0.04169  -0.0664   0.9835   0.0070
  -6.500  -0.3574   0.03723   0.03514  -0.0704   0.9762   0.0073
  -6.250  -0.3339   0.03236   0.02998  -0.0724   0.9693   0.0080
  -6.000  -0.3097   0.03067   0.02810  -0.0717   0.9610   0.0088
  -5.750  -0.2912   0.02807   0.02518  -0.0711   0.9524   0.0089
  -5.500  -0.2741   0.02543   0.02222  -0.0700   0.9435   0.0090
  -5.000  -0.2446   0.01398   0.00944  -0.0658   0.9268   0.0054
  -4.750  -0.2200   0.01261   0.00793  -0.0650   0.9200   0.0046
  -4.500  -0.1964   0.01102   0.00609  -0.0638   0.9137   0.0043
  -4.250  -0.1717   0.00990   0.00478  -0.0630   0.9065   0.0041
  -4.000  -0.1465   0.00914   0.00387  -0.0622   0.9002   0.0041
  -3.750  -0.1202   0.00857   0.00318  -0.0617   0.8932   0.0042
  -3.500  -0.0937   0.00817   0.00266  -0.0613   0.8870   0.0046
  -3.250  -0.0666   0.00774   0.00212  -0.0609   0.8798   0.0066
  -3.000  -0.0401   0.00733   0.00179  -0.0605   0.8732   0.0304
  -2.750  -0.0131   0.00705   0.00160  -0.0603   0.8656   0.0598
  -2.500   0.0133   0.00669   0.00143  -0.0601   0.8585   0.1190
  -2.250   0.0395   0.00624   0.00129  -0.0600   0.8502   0.2133
  -2.000   0.0658   0.00588   0.00119  -0.0598   0.8419   0.2998
  -1.750   0.0923   0.00560   0.00109  -0.0596   0.8330   0.3785
  -1.500   0.1188   0.00531   0.00102  -0.0594   0.8223   0.4602
  -1.250   0.1453   0.00508   0.00097  -0.0591   0.8109   0.5352
  -1.000   0.1717   0.00488   0.00093  -0.0588   0.7992   0.6071
  -0.750   0.1977   0.00469   0.00090  -0.0584   0.7866   0.6797
  -0.500   0.2236   0.00454   0.00088  -0.0578   0.7728   0.7431
  -0.250   0.2490   0.00442   0.00088  -0.0572   0.7575   0.8017
   0.000   0.2737   0.00432   0.00089  -0.0563   0.7410   0.8567
   0.250   0.2977   0.00426   0.00090  -0.0551   0.7232   0.9097
   0.500   0.3274   0.00427   0.00091  -0.0552   0.7031   0.9551
   0.750   0.3666   0.00436   0.00090  -0.0577   0.6808   0.9811
   1.000   0.4058   0.00447   0.00090  -0.0602   0.6566   0.9944
   1.250   0.4391   0.00460   0.00092  -0.0615   0.6319   1.0000
   1.500   0.4640   0.00473   0.00096  -0.0609   0.6098   1.0000
   1.750   0.4889   0.00489   0.00100  -0.0603   0.5874   1.0000
   2.000   0.5143   0.00503   0.00106  -0.0598   0.5649   1.0000
   2.250   0.5397   0.00518   0.00112  -0.0593   0.5427   1.0000
   2.500   0.5652   0.00535   0.00119  -0.0589   0.5195   1.0000
   2.750   0.5910   0.00552   0.00129  -0.0585   0.4955   1.0000
   3.000   0.6167   0.00570   0.00138  -0.0581   0.4711   1.0000
   3.250   0.6424   0.00591   0.00149  -0.0577   0.4455   1.0000
   3.500   0.6681   0.00612   0.00160  -0.0574   0.4196   1.0000
   3.750   0.6938   0.00635   0.00175  -0.0570   0.3947   1.0000
   4.000   0.7194   0.00659   0.00189  -0.0567   0.3671   1.0000
   4.250   0.7448   0.00685   0.00205  -0.0563   0.3390   1.0000
   4.500   0.7702   0.00713   0.00222  -0.0559   0.3109   1.0000
   4.750   0.7956   0.00741   0.00242  -0.0556   0.2853   1.0000
   5.000   0.8201   0.00779   0.00265  -0.0551   0.2493   1.0000
   5.250   0.8450   0.00814   0.00288  -0.0547   0.2211   1.0000
   5.500   0.8698   0.00848   0.00312  -0.0543   0.1952   1.0000
   5.750   0.8947   0.00882   0.00337  -0.0539   0.1715   1.0000
   6.000   0.9193   0.00918   0.00365  -0.0535   0.1492   1.0000
   6.250   0.9435   0.00959   0.00398  -0.0530   0.1261   1.0000
   6.500   0.9675   0.01003   0.00432  -0.0525   0.1030   1.0000
   6.750   0.9906   0.01056   0.00471  -0.0519   0.0770   1.0000
   7.000   1.0129   0.01117   0.00516  -0.0511   0.0503   1.0000
   7.250   1.0351   0.01178   0.00564  -0.0504   0.0306   1.0000
   7.500   1.0580   0.01230   0.00610  -0.0498   0.0196   1.0000
   7.750   1.0809   0.01281   0.00658  -0.0491   0.0132   1.0000
   8.000   1.1027   0.01344   0.00718  -0.0482   0.0057   1.0000
   8.250   1.1232   0.01426   0.00808  -0.0471   0.0029   1.0000
   8.500   1.1455   0.01479   0.00867  -0.0463   0.0025   1.0000
   8.750   1.1667   0.01543   0.00937  -0.0454   0.0021   1.0000
   9.000   1.1844   0.01647   0.01055  -0.0438   0.0016   1.0000
   9.250   1.2037   0.01725   0.01143  -0.0426   0.0014   1.0000
   9.500   1.2220   0.01810   0.01238  -0.0413   0.0013   1.0000
   9.750   1.2386   0.01906   0.01347  -0.0397   0.0012   1.0000
  10.000   1.2533   0.02014   0.01468  -0.0379   0.0011   1.0000
  10.250   1.2664   0.02129   0.01596  -0.0359   0.0010   1.0000
  10.500   1.2775   0.02252   0.01733  -0.0337   0.0010   1.0000
  10.750   1.2844   0.02384   0.01882  -0.0308   0.0010   1.0000
  11.000   1.2865   0.02524   0.02037  -0.0272   0.0010   1.0000
  11.250   1.2873   0.02680   0.02209  -0.0238   0.0010   1.0000
  11.500   1.2853   0.02867   0.02413  -0.0205   0.0010   1.0000
  11.750   1.2817   0.03080   0.02645  -0.0175   0.0010   1.0000
  12.000   1.2763   0.03323   0.02907  -0.0149   0.0010   1.0000
  12.250   1.2693   0.03599   0.03202  -0.0128   0.0010   1.0000
  12.500   1.2587   0.03932   0.03557  -0.0111   0.0010   1.0000
  12.750   1.2504   0.04266   0.03909  -0.0102   0.0010   1.0000
  13.000   1.2329   0.04747   0.04413  -0.0101   0.0010   1.0000
  13.250   1.2156   0.05274   0.04962  -0.0111   0.0010   1.0000
  13.500   1.1969   0.05881   0.05590  -0.0132   0.0011   1.0000
  13.750   1.1870   0.06399   0.06121  -0.0156   0.0011   1.0000
  14.000   1.1635   0.07203   0.06945  -0.0198   0.0011   1.0000
  14.250   1.1511   0.07864   0.07620  -0.0237   0.0011   1.0000
  14.500   1.1342   0.08663   0.08432  -0.0284   0.0011   1.0000
  14.750   1.1154   0.09548   0.09332  -0.0337   0.0011   1.0000
  15.000   1.0951   0.10521   0.10318  -0.0394   0.0011   1.0000
  15.250   1.0793   0.11420   0.11227  -0.0446   0.0011   1.0000
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