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MH 45 9.85% (mh45-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MH 45 9.85% (mh45-il)
Reynolds number: 50,000
Max Cl/Cd: 27.9 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh45-il-50000.txt
Download as CSV file: xf-mh45-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 45  9.85%                                    
  
 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  -0.5105   0.10241   0.09640   0.0181   1.0000   0.2679
  -8.000  -0.5021   0.09800   0.09205   0.0174   1.0000   0.2732
  -7.750  -0.5180   0.09625   0.09045   0.0148   1.0000   0.2843
  -7.500  -0.4970   0.09067   0.08487   0.0150   1.0000   0.2874
  -7.250  -0.4904   0.08678   0.08104   0.0140   1.0000   0.2922
  -7.000  -0.5531   0.06644   0.06050  -0.0199   1.0000   0.1287
  -6.750  -0.5493   0.05876   0.05244  -0.0241   1.0000   0.1115
  -6.500  -0.5378   0.05345   0.04695  -0.0254   1.0000   0.1063
  -6.250  -0.5301   0.04710   0.03976  -0.0272   1.0000   0.0983
  -6.000  -0.5132   0.04278   0.03509  -0.0272   1.0000   0.0961
  -5.750  -0.4952   0.03879   0.03062  -0.0269   1.0000   0.0945
  -5.500  -0.4755   0.03530   0.02662  -0.0262   1.0000   0.0948
  -5.250  -0.4554   0.03253   0.02324  -0.0251   1.0000   0.0987
  -5.000  -0.4361   0.03020   0.02087  -0.0239   1.0000   0.1057
  -4.750  -0.4168   0.02809   0.01831  -0.0220   1.0000   0.1130
  -4.500  -0.4001   0.02631   0.01656  -0.0201   1.0000   0.1282
  -4.250  -0.3835   0.02466   0.01505  -0.0181   1.0000   0.1515
  -4.000  -0.3680   0.02292   0.01364  -0.0158   1.0000   0.2028
  -3.750  -0.3587   0.02102   0.01258  -0.0124   1.0000   0.3431
  -3.500  -0.3520   0.02044   0.01245  -0.0085   1.0000   0.4441
  -3.250  -0.3428   0.02003   0.01239  -0.0047   1.0000   0.5226
  -3.000  -0.3304   0.01949   0.01210  -0.0012   1.0000   0.5958
  -2.750  -0.3168   0.01888   0.01174   0.0023   1.0000   0.6724
  -2.500  -0.3026   0.01828   0.01149   0.0065   1.0000   0.7684
  -2.250  -0.1053   0.01807   0.01053  -0.0212   1.0000   1.0000
  -2.000  -0.1320   0.01778   0.01006  -0.0160   1.0000   1.0000
  -1.750  -0.1320   0.01785   0.00983  -0.0134   1.0000   1.0000
  -1.500  -0.1247   0.01804   0.00971  -0.0116   1.0000   1.0000
  -1.250  -0.1141   0.01830   0.00972  -0.0102   1.0000   1.0000
  -1.000  -0.1017   0.01863   0.00981  -0.0091   1.0000   1.0000
  -0.750  -0.0847   0.01904   0.01000  -0.0088   0.9987   1.0000
  -0.500  -0.0251   0.01996   0.01063  -0.0164   0.9826   1.0000
  -0.250   0.0290   0.02077   0.01123  -0.0227   0.9654   1.0000
   0.000   0.0834   0.02156   0.01184  -0.0288   0.9479   1.0000
   0.250   0.1411   0.02231   0.01248  -0.0352   0.9305   1.0000
   0.500   0.1933   0.02297   0.01307  -0.0404   0.9125   1.0000
   0.750   0.2407   0.02358   0.01363  -0.0445   0.8936   1.0000
   1.000   0.2877   0.02414   0.01417  -0.0481   0.8752   1.0000
   1.250   0.3294   0.02469   0.01471  -0.0504   0.8569   1.0000
   1.500   0.3558   0.02534   0.01535  -0.0502   0.8367   1.0000
   1.750   0.3879   0.02587   0.01588  -0.0504   0.8180   1.0000
   2.000   0.4166   0.02639   0.01641  -0.0499   0.7997   1.0000
   2.250   0.4367   0.02707   0.01712  -0.0484   0.7794   1.0000
   2.500   0.4621   0.02753   0.01759  -0.0470   0.7608   1.0000
   2.750   0.4879   0.02786   0.01794  -0.0454   0.7434   1.0000
   3.000   0.5058   0.02857   0.01868  -0.0436   0.7224   1.0000
   3.250   0.5289   0.02892   0.01910  -0.0417   0.7038   1.0000
   3.500   0.5530   0.02908   0.01929  -0.0395   0.6863   1.0000
   3.750   0.5729   0.02962   0.01989  -0.0376   0.6657   1.0000
   4.000   0.5954   0.02982   0.02014  -0.0354   0.6465   1.0000
   4.250   0.6199   0.02968   0.02007  -0.0328   0.6288   1.0000
   4.500   0.6404   0.03011   0.02058  -0.0309   0.6071   1.0000
   4.750   0.6644   0.02995   0.02046  -0.0283   0.5877   1.0000
   5.000   0.6874   0.02993   0.02053  -0.0259   0.5670   1.0000
   5.250   0.7108   0.02986   0.02051  -0.0234   0.5452   1.0000
   5.500   0.7340   0.02986   0.02056  -0.0211   0.5228   1.0000
   5.750   0.7587   0.02958   0.02027  -0.0185   0.5003   1.0000
   6.000   0.7811   0.02987   0.02066  -0.0165   0.4748   1.0000
   6.250   0.8043   0.03009   0.02088  -0.0145   0.4495   1.0000
   6.500   0.8281   0.03028   0.02103  -0.0124   0.4239   1.0000
   6.750   0.8522   0.03055   0.02120  -0.0104   0.3984   1.0000
   7.000   0.8737   0.03136   0.02206  -0.0089   0.3713   1.0000
   7.250   0.8946   0.03242   0.02323  -0.0076   0.3454   1.0000
   7.500   0.9157   0.03352   0.02435  -0.0062   0.3211   1.0000
   7.750   0.9390   0.03443   0.02515  -0.0048   0.2988   1.0000
   8.000   0.9564   0.03621   0.02715  -0.0037   0.2770   1.0000
   8.250   0.9776   0.03769   0.02866  -0.0026   0.2581   1.0000
   8.500   0.9964   0.03939   0.03047  -0.0015   0.2397   1.0000
   8.750   1.0122   0.04182   0.03313  -0.0005   0.2248   1.0000
   9.000   1.0265   0.04421   0.03573   0.0006   0.2100   1.0000
   9.250   1.0404   0.04669   0.03839   0.0016   0.1967   1.0000
   9.500   1.0572   0.04925   0.04101   0.0026   0.1850   1.0000
   9.750   1.0473   0.05399   0.04638   0.0034   0.1786   1.0000
  10.000   1.0555   0.05694   0.04945   0.0044   0.1688   1.0000
  10.250   1.0348   0.06263   0.05552   0.0045   0.1674   1.0000
  10.500   1.0046   0.06891   0.06202   0.0038   0.1681   1.0000
  10.750   0.9696   0.07561   0.06876   0.0021   0.1700   1.0000
  11.000   0.9401   0.08356   0.07669  -0.0015   0.1716   1.0000
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