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MH 24 9.01% (mh24-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MH 24 9.01% (mh24-il)
Reynolds number: 50,000
Max Cl/Cd: 34.16 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh24-il-50000.txt
Download as CSV file: xf-mh24-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 24  9.01%                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4881   0.12894   0.12183  -0.0195   1.0000   0.1816
 -10.500  -0.4755   0.12438   0.11728  -0.0186   1.0000   0.1909
 -10.250  -0.4949   0.12354   0.11657  -0.0210   1.0000   0.1960
 -10.000  -0.4761   0.11851   0.11153  -0.0193   1.0000   0.2072
  -9.750  -0.4704   0.11485   0.10791  -0.0188   1.0000   0.2174
  -9.500  -0.4796   0.11236   0.10554  -0.0196   1.0000   0.2252
  -9.250  -0.4853   0.11013   0.10339  -0.0195   1.0000   0.2363
  -9.000  -0.4790   0.10650   0.09980  -0.0184   1.0000   0.2491
  -8.750  -0.4738   0.10297   0.09622  -0.0173   1.0000   0.2615
  -8.500  -0.4717   0.09980   0.09313  -0.0162   1.0000   0.2742
  -8.250  -0.4754   0.09700   0.09042  -0.0150   1.0000   0.2886
  -8.000  -0.4795   0.09444   0.08795  -0.0136   1.0000   0.3029
  -7.750  -0.4925   0.09237   0.08599  -0.0118   1.0000   0.3178
  -7.500  -0.4760   0.08819   0.08184  -0.0095   1.0000   0.3362
  -7.250  -0.4787   0.08578   0.07951  -0.0070   1.0000   0.3559
  -5.250  -0.5609   0.05078   0.04321  -0.0145   1.0000   0.1259
  -5.000  -0.5474   0.04637   0.03820  -0.0125   1.0000   0.1086
  -4.750  -0.5321   0.04276   0.03399  -0.0102   1.0000   0.0976
  -4.500  -0.5150   0.03986   0.03006  -0.0073   1.0000   0.0883
  -4.250  -0.4954   0.03652   0.02651  -0.0057   1.0000   0.0862
  -4.000  -0.4740   0.03381   0.02342  -0.0039   1.0000   0.0845
  -3.750  -0.4502   0.03134   0.02049  -0.0023   1.0000   0.0844
  -3.500  -0.1702   0.02135   0.01332  -0.0360   1.0000   1.0000
  -3.250  -0.1631   0.02100   0.01259  -0.0333   1.0000   1.0000
  -3.000  -0.1547   0.02072   0.01188  -0.0306   1.0000   1.0000
  -2.750  -0.1453   0.02050   0.01135  -0.0279   1.0000   1.0000
  -2.500  -0.1351   0.02033   0.01089  -0.0253   1.0000   1.0000
  -2.250  -0.1244   0.02020   0.01049  -0.0227   1.0000   1.0000
  -2.000  -0.1133   0.02010   0.01016  -0.0201   1.0000   1.0000
  -1.750  -0.1019   0.02003   0.00987  -0.0176   1.0000   1.0000
  -1.500  -0.0901   0.01999   0.00963  -0.0152   1.0000   1.0000
  -1.250  -0.0782   0.01998   0.00944  -0.0127   1.0000   1.0000
  -1.000  -0.0660   0.01999   0.00924  -0.0103   1.0000   1.0000
  -0.750  -0.0537   0.02003   0.00913  -0.0080   1.0000   1.0000
  -0.500  -0.0412   0.02009   0.00907  -0.0057   1.0000   1.0000
  -0.250  -0.0286   0.02018   0.00904  -0.0035   1.0000   1.0000
   0.000  -0.0158   0.02030   0.00905  -0.0013   1.0000   1.0000
   0.250  -0.0030   0.02045   0.00911   0.0008   1.0000   1.0000
   0.500   0.0099   0.02063   0.00918   0.0029   1.0000   1.0000
   0.750   0.0229   0.02085   0.00933   0.0048   1.0000   1.0000
   1.000   0.0358   0.02110   0.00954   0.0067   1.0000   1.0000
   1.250   0.0488   0.02139   0.00979   0.0086   1.0000   1.0000
   1.500   0.0617   0.02173   0.01011   0.0103   1.0000   1.0000
   1.750   0.0746   0.02211   0.01049   0.0119   1.0000   1.0000
   2.000   0.0875   0.02255   0.01093   0.0134   1.0000   1.0000
   2.250   0.1003   0.02305   0.01144   0.0148   1.0000   1.0000
   2.500   0.1130   0.02361   0.01202   0.0160   1.0000   1.0000
   2.750   0.1254   0.02424   0.01269   0.0172   1.0000   1.0000
   3.000   0.1375   0.02496   0.01345   0.0181   1.0000   1.0000
   3.250   0.1515   0.02579   0.01435   0.0185   0.9991   1.0000
   3.500   0.2313   0.02798   0.01683   0.0062   0.9697   1.0000
   3.750   0.2976   0.02934   0.01847  -0.0026   0.9380   1.0000
   4.000   0.3647   0.03021   0.01968  -0.0106   0.9052   1.0000
   4.250   0.4276   0.03042   0.02036  -0.0169   0.8705   1.0000
   4.500   0.5004   0.02978   0.02023  -0.0234   0.8333   1.0000
   4.750   0.5842   0.02778   0.01899  -0.0297   0.7901   1.0000
   5.000   0.6828   0.02382   0.01582  -0.0349   0.7310   1.0000
   5.250   0.7386   0.02184   0.01391  -0.0338   0.6342   1.0000
   5.500   0.7588   0.02221   0.01382  -0.0295   0.5296   1.0000
   5.750   0.7697   0.02338   0.01452  -0.0249   0.4327   1.0000
   6.000   0.7787   0.02494   0.01550  -0.0207   0.3458   1.0000
   6.250   0.7907   0.02682   0.01687  -0.0173   0.2713   1.0000
   6.500   0.8051   0.02884   0.01847  -0.0146   0.2138   1.0000
   6.750   0.8246   0.03119   0.02065  -0.0126   0.1726   1.0000
   7.000   0.8443   0.03362   0.02309  -0.0107   0.1453   1.0000
   7.250   0.8664   0.03666   0.02643  -0.0090   0.1301   1.0000
   7.500   0.8802   0.03904   0.02904  -0.0065   0.1156   1.0000
   7.750   0.8958   0.04220   0.03241  -0.0044   0.1068   1.0000
   8.000   0.9039   0.04575   0.03659  -0.0009   0.1039   1.0000
   8.250   0.9084   0.04955   0.04092   0.0026   0.1024   1.0000
   8.500   0.9085   0.05351   0.04534   0.0061   0.1023   1.0000
   8.750   0.9034   0.05766   0.04993   0.0097   0.1031   1.0000
   9.000   0.8951   0.06174   0.05436   0.0130   0.1040   1.0000
   9.250   0.8828   0.06580   0.05871   0.0162   0.1043   1.0000
   9.500   0.8684   0.06991   0.06302   0.0188   0.1052   1.0000
   9.750   0.8528   0.07408   0.06733   0.0211   0.1063   1.0000
  10.000   0.8409   0.07825   0.07156   0.0229   0.1076   1.0000
  10.250   0.8267   0.08269   0.07604   0.0241   0.1082   1.0000
  10.500   0.8126   0.08745   0.08083   0.0244   0.1086   1.0000
  10.750   0.7346   0.09977   0.09311   0.0119   0.1317   1.0000
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