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MH 32 8.7% (mh32-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MH 32 8.7% (mh32-il)
Reynolds number: 50,000
Max Cl/Cd: 35.2 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh32-il-50000.txt
Download as CSV file: xf-mh32-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4293   0.10315   0.09665  -0.0181   1.0000   0.2241
  -8.000  -0.4143   0.09879   0.09230  -0.0169   1.0000   0.2364
  -7.750  -0.4112   0.09572   0.08932  -0.0163   1.0000   0.2499
  -7.500  -0.4060   0.09250   0.08616  -0.0155   1.0000   0.2626
  -7.250  -0.3317   0.08026   0.07442  -0.0168   1.0000   0.2942
  -7.000  -0.3400   0.07796   0.07224  -0.0156   1.0000   0.3066
  -6.750  -0.3388   0.07455   0.06892  -0.0139   1.0000   0.3201
  -6.500  -0.3363   0.07117   0.06562  -0.0120   1.0000   0.3332
  -6.250  -0.4088   0.07902   0.07314  -0.0077   1.0000   0.3381
  -6.000  -0.4072   0.07623   0.07045  -0.0056   1.0000   0.3545
  -4.750  -0.3891   0.04437   0.03696  -0.0406   1.0000   0.1126
  -4.500  -0.3706   0.04006   0.03214  -0.0405   1.0000   0.1054
  -4.250  -0.3484   0.03640   0.02772  -0.0401   1.0000   0.1000
  -4.000  -0.3261   0.03323   0.02399  -0.0392   1.0000   0.0990
  -3.750  -0.3018   0.03061   0.02070  -0.0383   1.0000   0.1014
  -3.500  -0.2796   0.02850   0.01847  -0.0374   1.0000   0.1129
  -3.250  -0.2548   0.02625   0.01599  -0.0362   1.0000   0.1244
  -3.000  -0.2310   0.02450   0.01419  -0.0350   1.0000   0.1519
  -2.750  -0.2058   0.02258   0.01242  -0.0338   1.0000   0.2000
  -2.500  -0.1823   0.01956   0.01096  -0.0323   1.0000   0.4273
  -2.250  -0.1452   0.01725   0.01041  -0.0288   1.0000   1.0000
  -2.000  -0.1255   0.01725   0.00976  -0.0284   1.0000   1.0000
  -1.750  -0.1056   0.01735   0.00930  -0.0279   1.0000   1.0000
  -1.500  -0.0856   0.01751   0.00903  -0.0273   1.0000   1.0000
  -1.250  -0.0657   0.01771   0.00888  -0.0267   1.0000   1.0000
  -1.000  -0.0459   0.01795   0.00881  -0.0261   1.0000   1.0000
  -0.750  -0.0263   0.01824   0.00883  -0.0256   1.0000   1.0000
  -0.500  -0.0068   0.01858   0.00891  -0.0251   1.0000   1.0000
  -0.250   0.0124   0.01896   0.00904  -0.0246   1.0000   1.0000
   0.000   0.0313   0.01938   0.00929  -0.0242   1.0000   1.0000
   0.250   0.0498   0.01986   0.00960  -0.0238   1.0000   1.0000
   0.500   0.0681   0.02039   0.00999  -0.0234   1.0000   1.0000
   0.750   0.0860   0.02098   0.01045  -0.0231   1.0000   1.0000
   1.000   0.1035   0.02163   0.01097  -0.0229   1.0000   1.0000
   1.250   0.1207   0.02234   0.01159  -0.0228   1.0000   1.0000
   1.500   0.1578   0.02346   0.01265  -0.0265   0.9904   1.0000
   1.750   0.2136   0.02487   0.01400  -0.0334   0.9712   1.0000
   2.000   0.2645   0.02606   0.01516  -0.0391   0.9512   1.0000
   2.250   0.3155   0.02710   0.01623  -0.0445   0.9305   1.0000
   2.500   0.3612   0.02795   0.01714  -0.0486   0.9090   1.0000
   2.750   0.4134   0.02866   0.01796  -0.0534   0.8881   1.0000
   3.000   0.4525   0.02923   0.01862  -0.0557   0.8653   1.0000
   3.250   0.5013   0.02959   0.01913  -0.0592   0.8439   1.0000
   3.500   0.5486   0.02973   0.01951  -0.0620   0.8215   1.0000
   3.750   0.5914   0.02977   0.01973  -0.0637   0.7982   1.0000
   4.000   0.6414   0.02928   0.01947  -0.0656   0.7767   1.0000
   4.250   0.6835   0.02874   0.01921  -0.0658   0.7530   1.0000
   4.500   0.7200   0.02823   0.01890  -0.0651   0.7277   1.0000
   4.750   0.7566   0.02754   0.01842  -0.0640   0.7013   1.0000
   5.000   0.7920   0.02679   0.01785  -0.0624   0.6731   1.0000
   5.250   0.8266   0.02603   0.01728  -0.0604   0.6429   1.0000
   5.500   0.8518   0.02597   0.01732  -0.0580   0.6077   1.0000
   5.750   0.8792   0.02583   0.01720  -0.0556   0.5714   1.0000
   6.000   0.9044   0.02594   0.01728  -0.0532   0.5325   1.0000
   6.250   0.9268   0.02633   0.01762  -0.0508   0.4914   1.0000
   6.500   0.9473   0.02694   0.01828  -0.0483   0.4487   1.0000
   6.750   0.9667   0.02772   0.01899  -0.0459   0.4049   1.0000
   7.000   0.9852   0.02866   0.01981  -0.0435   0.3607   1.0000
   7.250   1.0032   0.02979   0.02075  -0.0411   0.3168   1.0000
   7.500   1.0202   0.03120   0.02192  -0.0389   0.2739   1.0000
   7.750   1.0354   0.03295   0.02353  -0.0366   0.2326   1.0000
   8.000   1.0487   0.03478   0.02527  -0.0342   0.1950   1.0000
   8.250   1.0642   0.03724   0.02767  -0.0322   0.1642   1.0000
   8.500   1.0809   0.03994   0.03028  -0.0305   0.1392   1.0000
   8.750   1.0964   0.04357   0.03430  -0.0285   0.1242   1.0000
   9.000   1.1058   0.04647   0.03750  -0.0263   0.1093   1.0000
   9.250   1.1207   0.05060   0.04185  -0.0248   0.0999   1.0000
   9.500   1.1187   0.05494   0.04694  -0.0219   0.0965   1.0000
   9.750   1.1282   0.05843   0.05041  -0.0205   0.0871   1.0000
  10.000   1.1173   0.06261   0.05518  -0.0178   0.0855   1.0000
  10.250   1.1041   0.06701   0.05999  -0.0155   0.0847   1.0000
  10.500   1.0881   0.07142   0.06469  -0.0136   0.0849   1.0000
  10.750   1.0677   0.07569   0.06917  -0.0119   0.0852   1.0000
  11.000   1.0481   0.08033   0.07396  -0.0114   0.0860   1.0000
  11.250   1.0283   0.08554   0.07929  -0.0121   0.0867   1.0000
  11.500   1.0118   0.09131   0.08513  -0.0137   0.0874   1.0000
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