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MH 32 8.7% (mh32-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: MH 32 8.7% (mh32-il)
Reynolds number: 500,000
Max Cl/Cd: 84 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh32-il-500000-n5.txt
Download as CSV file: xf-mh32-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3475   0.08404   0.08190  -0.0272   1.0000   0.0047
  -9.000  -0.3487   0.07960   0.07748  -0.0286   1.0000   0.0045
  -8.750  -0.4233   0.08532   0.08306  -0.0282   1.0000   0.0047
  -8.500  -0.4236   0.08161   0.07939  -0.0298   1.0000   0.0046
  -8.250  -0.4273   0.07752   0.07533  -0.0316   1.0000   0.0044
  -8.000  -0.4316   0.07380   0.07166  -0.0331   1.0000   0.0043
  -7.750  -0.4430   0.07025   0.06817  -0.0340   1.0000   0.0042
  -7.500  -0.4492   0.06560   0.06356  -0.0380   0.9989   0.0042
  -7.250  -0.4316   0.05592   0.05378  -0.0514   0.9873   0.0040
  -7.000  -0.4113   0.04642   0.04403  -0.0613   0.9794   0.0037
  -6.750  -0.4073   0.02807   0.02467  -0.0677   0.9651   0.0029
  -6.500  -0.3867   0.02349   0.01950  -0.0682   0.9568   0.0027
  -6.250  -0.3650   0.02094   0.01653  -0.0678   0.9485   0.0027
  -6.000  -0.3420   0.01871   0.01389  -0.0673   0.9418   0.0027
  -5.750  -0.3194   0.01699   0.01185  -0.0666   0.9340   0.0026
  -5.250  -0.2722   0.01391   0.00820  -0.0650   0.9209   0.0027
  -5.000  -0.2480   0.01276   0.00683  -0.0642   0.9149   0.0028
  -4.750  -0.2232   0.01187   0.00579  -0.0636   0.9080   0.0029
  -4.500  -0.1979   0.01120   0.00500  -0.0630   0.9017   0.0030
  -4.250  -0.1720   0.01068   0.00435  -0.0626   0.8948   0.0034
  -4.000  -0.1458   0.01026   0.00383  -0.0621   0.8881   0.0038
  -3.750  -0.1193   0.00990   0.00337  -0.0618   0.8806   0.0047
  -3.500  -0.0928   0.00954   0.00293  -0.0613   0.8734   0.0066
  -3.250  -0.0663   0.00921   0.00261  -0.0610   0.8649   0.0154
  -3.000  -0.0401   0.00880   0.00234  -0.0607   0.8570   0.0463
  -2.750  -0.0139   0.00843   0.00210  -0.0605   0.8486   0.0906
  -2.500   0.0127   0.00811   0.00191  -0.0603   0.8399   0.1395
  -2.250   0.0392   0.00783   0.00175  -0.0600   0.8311   0.1912
  -2.000   0.0656   0.00752   0.00162  -0.0598   0.8213   0.2574
  -1.500   0.1186   0.00701   0.00140  -0.0594   0.8000   0.3855
  -1.250   0.1449   0.00678   0.00133  -0.0591   0.7878   0.4555
  -1.000   0.1710   0.00657   0.00127  -0.0587   0.7741   0.5232
  -0.750   0.1969   0.00639   0.00122  -0.0583   0.7581   0.5881
  -0.500   0.2224   0.00624   0.00118  -0.0577   0.7400   0.6515
  -0.250   0.2475   0.00612   0.00117  -0.0570   0.7213   0.7123
   0.000   0.2723   0.00602   0.00117  -0.0562   0.7016   0.7701
   0.250   0.2965   0.00595   0.00118  -0.0551   0.6817   0.8253
   0.500   0.3206   0.00592   0.00120  -0.0540   0.6608   0.8785
   0.750   0.3492   0.00595   0.00122  -0.0539   0.6397   0.9292
   1.000   0.3878   0.00605   0.00123  -0.0562   0.6162   0.9674
   1.250   0.4259   0.00617   0.00124  -0.0585   0.5928   0.9924
   1.500   0.4560   0.00632   0.00129  -0.0591   0.5707   1.0000
   1.750   0.4810   0.00649   0.00134  -0.0585   0.5486   1.0000
   2.000   0.5063   0.00665   0.00141  -0.0580   0.5265   1.0000
   2.250   0.5316   0.00684   0.00149  -0.0576   0.5035   1.0000
   2.500   0.5570   0.00703   0.00158  -0.0571   0.4794   1.0000
   2.750   0.5824   0.00723   0.00171  -0.0567   0.4553   1.0000
   3.000   0.6079   0.00745   0.00182  -0.0563   0.4319   1.0000
   3.250   0.6332   0.00768   0.00196  -0.0559   0.4072   1.0000
   3.750   0.6839   0.00817   0.00229  -0.0551   0.3580   1.0000
   4.000   0.7091   0.00845   0.00247  -0.0547   0.3311   1.0000
   4.250   0.7342   0.00874   0.00266  -0.0543   0.3053   1.0000
   4.500   0.7591   0.00905   0.00288  -0.0538   0.2796   1.0000
   4.750   0.7841   0.00937   0.00311  -0.0534   0.2555   1.0000
   5.000   0.8088   0.00971   0.00339  -0.0530   0.2312   1.0000
   5.250   0.8337   0.01003   0.00365  -0.0526   0.2100   1.0000
   5.500   0.8579   0.01043   0.00395  -0.0521   0.1834   1.0000
   6.000   0.9050   0.01138   0.00465  -0.0510   0.1265   1.0000
   6.250   0.9291   0.01177   0.00504  -0.0505   0.1092   1.0000
   6.500   0.9530   0.01220   0.00542  -0.0500   0.0923   1.0000
   7.000   0.9992   0.01320   0.00631  -0.0487   0.0591   1.0000
   7.250   1.0215   0.01378   0.00682  -0.0480   0.0428   1.0000
   7.500   1.0427   0.01446   0.00741  -0.0472   0.0264   1.0000
   7.750   1.0643   0.01509   0.00800  -0.0464   0.0171   1.0000
   8.000   1.0859   0.01570   0.00862  -0.0455   0.0120   1.0000
   8.250   1.1069   0.01636   0.00933  -0.0446   0.0071   1.0000
   8.500   1.1271   0.01709   0.01009  -0.0436   0.0042   1.0000
   8.750   1.1467   0.01787   0.01093  -0.0424   0.0028   1.0000
   9.000   1.1666   0.01855   0.01170  -0.0414   0.0022   1.0000
   9.250   1.1852   0.01935   0.01258  -0.0402   0.0018   1.0000
   9.500   1.2012   0.02040   0.01377  -0.0386   0.0015   1.0000
   9.750   1.2182   0.02127   0.01476  -0.0372   0.0015   1.0000
  10.000   1.2340   0.02218   0.01580  -0.0356   0.0014   1.0000
  10.250   1.2484   0.02314   0.01689  -0.0339   0.0012   1.0000
  10.500   1.2607   0.02417   0.01805  -0.0319   0.0012   1.0000
  10.750   1.2686   0.02530   0.01931  -0.0293   0.0011   1.0000
  11.000   1.2763   0.02639   0.02057  -0.0267   0.0010   1.0000
  11.250   1.2825   0.02763   0.02194  -0.0242   0.0009   1.0000
  11.500   1.2875   0.02899   0.02343  -0.0219   0.0008   1.0000
  11.750   1.2905   0.03057   0.02516  -0.0196   0.0008   1.0000
  12.000   1.2929   0.03226   0.02699  -0.0176   0.0008   1.0000
  12.250   1.2935   0.03420   0.02908  -0.0158   0.0007   1.0000
  12.500   1.2907   0.03658   0.03162  -0.0141   0.0007   1.0000
  12.750   1.2883   0.03909   0.03431  -0.0129   0.0007   1.0000
  13.000   1.2807   0.04234   0.03773  -0.0122   0.0007   1.0000
  13.250   1.2686   0.04643   0.04202  -0.0122   0.0006   1.0000
  13.500   1.2558   0.05103   0.04682  -0.0130   0.0006   1.0000
  13.750   1.2540   0.05449   0.05042  -0.0140   0.0006   1.0000
  14.000   1.2302   0.06157   0.05773  -0.0168   0.0006   1.0000
  14.250   1.2264   0.06598   0.06227  -0.0189   0.0006   1.0000
  14.500   1.2124   0.07241   0.06887  -0.0222   0.0006   1.0000
  14.750   1.1961   0.07971   0.07633  -0.0262   0.0006   1.0000
  15.000   1.1747   0.08847   0.08527  -0.0311   0.0006   1.0000
  15.250   1.1633   0.09550   0.09243  -0.0350   0.0006   1.0000
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