Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

MH 42 8.94% (mh42-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: MH 42 8.94% (mh42-il)
Reynolds number: 200,000
Max Cl/Cd: 66.96 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh42-il-200000.txt
Download as CSV file: xf-mh42-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 42  8.94%                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4348   0.11251   0.10930  -0.0051   1.0000   0.0352
 -10.000  -0.4340   0.10810   0.10491  -0.0072   1.0000   0.0353
  -9.000  -0.5104   0.09434   0.09102  -0.0118   1.0000   0.0363
  -8.750  -0.5035   0.09120   0.08789  -0.0113   1.0000   0.0373
  -8.500  -0.4989   0.08792   0.08464  -0.0122   1.0000   0.0381
  -8.250  -0.4963   0.08438   0.08114  -0.0136   1.0000   0.0392
  -8.000  -0.4965   0.08052   0.07732  -0.0158   1.0000   0.0401
  -7.750  -0.5000   0.07641   0.07327  -0.0188   1.0000   0.0409
  -7.500  -0.5034   0.07149   0.06838  -0.0235   1.0000   0.0418
  -7.250  -0.5022   0.06625   0.06311  -0.0282   1.0000   0.0428
  -7.000  -0.4995   0.06049   0.05724  -0.0327   1.0000   0.0448
  -6.750  -0.4969   0.05644   0.05252  -0.0368   1.0000   0.0477
  -6.500  -0.4929   0.04908   0.04530  -0.0376   1.0000   0.0496
  -6.250  -0.4791   0.04618   0.04240  -0.0374   1.0000   0.0513
  -6.000  -0.4659   0.04305   0.03913  -0.0371   1.0000   0.0536
  -5.750  -0.4541   0.03294   0.02784  -0.0342   1.0000   0.0237
  -5.500  -0.4475   0.02846   0.02304  -0.0320   1.0000   0.0215
  -5.250  -0.4386   0.02531   0.01945  -0.0290   1.0000   0.0196
  -5.000  -0.4282   0.02247   0.01607  -0.0258   1.0000   0.0181
  -4.750  -0.4015   0.02012   0.01330  -0.0256   0.9969   0.0175
  -4.500  -0.3619   0.01799   0.01090  -0.0278   0.9905   0.0182
  -4.250  -0.3210   0.01651   0.00927  -0.0303   0.9839   0.0215
  -4.000  -0.2820   0.01503   0.00771  -0.0327   0.9767   0.0276
  -3.750  -0.2414   0.01346   0.00607  -0.0351   0.9701   0.0487
  -3.500  -0.2070   0.01178   0.00505  -0.0369   0.9604   0.1682
  -3.250  -0.1710   0.01108   0.00467  -0.0388   0.9508   0.2619
  -3.000  -0.1386   0.01041   0.00440  -0.0399   0.9403   0.3720
  -2.750  -0.1132   0.00971   0.00426  -0.0394   0.9277   0.5173
  -2.500  -0.0916   0.00920   0.00417  -0.0375   0.9143   0.6453
  -2.250  -0.0708   0.00887   0.00414  -0.0351   0.9010   0.7510
  -2.000  -0.0477   0.00870   0.00412  -0.0329   0.8884   0.8356
  -1.750  -0.0155   0.00866   0.00407  -0.0326   0.8767   0.9008
  -1.500   0.0278   0.00867   0.00396  -0.0350   0.8661   0.9425
  -1.250   0.0760   0.00869   0.00380  -0.0386   0.8557   0.9696
  -1.000   0.1278   0.00866   0.00359  -0.0432   0.8452   0.9892
  -0.750   0.1677   0.00862   0.00340  -0.0458   0.8324   1.0000
  -0.500   0.1881   0.00863   0.00326  -0.0444   0.8186   1.0000
  -0.250   0.2096   0.00866   0.00318  -0.0431   0.8051   1.0000
   0.000   0.2318   0.00871   0.00311  -0.0419   0.7919   1.0000
   0.250   0.2546   0.00877   0.00307  -0.0409   0.7789   1.0000
   0.500   0.2779   0.00884   0.00304  -0.0399   0.7660   1.0000
   0.750   0.3016   0.00891   0.00303  -0.0390   0.7533   1.0000
   1.000   0.3257   0.00900   0.00304  -0.0381   0.7406   1.0000
   1.250   0.3500   0.00909   0.00306  -0.0373   0.7279   1.0000
   1.500   0.3745   0.00918   0.00310  -0.0365   0.7151   1.0000
   1.750   0.3991   0.00928   0.00313  -0.0357   0.7023   1.0000
   2.000   0.4239   0.00938   0.00318  -0.0350   0.6891   1.0000
   2.250   0.4489   0.00949   0.00324  -0.0343   0.6756   1.0000
   2.500   0.4740   0.00960   0.00331  -0.0336   0.6617   1.0000
   2.750   0.4993   0.00970   0.00341  -0.0329   0.6472   1.0000
   3.000   0.5246   0.00982   0.00350  -0.0323   0.6322   1.0000
   3.250   0.5499   0.00993   0.00359  -0.0316   0.6166   1.0000
   3.500   0.5753   0.01005   0.00368  -0.0310   0.6005   1.0000
   3.750   0.6007   0.01018   0.00382  -0.0304   0.5831   1.0000
   4.000   0.6261   0.01031   0.00396  -0.0298   0.5640   1.0000
   4.250   0.6513   0.01046   0.00408  -0.0292   0.5448   1.0000
   4.500   0.6766   0.01062   0.00425  -0.0286   0.5225   1.0000
   4.750   0.7017   0.01081   0.00446  -0.0279   0.4991   1.0000
   5.000   0.7265   0.01103   0.00465  -0.0273   0.4733   1.0000
   5.250   0.7511   0.01128   0.00489  -0.0267   0.4447   1.0000
   5.500   0.7754   0.01158   0.00515  -0.0260   0.4127   1.0000
   5.750   0.7991   0.01196   0.00546  -0.0253   0.3776   1.0000
   6.000   0.8222   0.01242   0.00583  -0.0246   0.3388   1.0000
   6.250   0.8447   0.01298   0.00631  -0.0239   0.2946   1.0000
   6.500   0.8663   0.01366   0.00684  -0.0231   0.2478   1.0000
   6.750   0.8870   0.01448   0.00745  -0.0223   0.1987   1.0000
   7.000   0.9071   0.01540   0.00818  -0.0215   0.1547   1.0000
   7.250   0.9266   0.01643   0.00904  -0.0206   0.1185   1.0000
   7.500   0.9449   0.01760   0.01006  -0.0195   0.0882   1.0000
   7.750   0.9623   0.01886   0.01124  -0.0182   0.0650   1.0000
   8.000   0.9786   0.02027   0.01265  -0.0167   0.0518   1.0000
   8.250   0.9940   0.02181   0.01424  -0.0151   0.0433   1.0000
   8.500   1.0070   0.02373   0.01612  -0.0134   0.0361   1.0000
   8.750   1.0265   0.02451   0.01713  -0.0123   0.0295   1.0000
   9.000   1.0379   0.02711   0.01981  -0.0104   0.0250   1.0000
   9.250   1.0545   0.02786   0.02070  -0.0092   0.0197   1.0000
   9.500   1.0636   0.03125   0.02421  -0.0074   0.0171   1.0000
   9.750   1.0763   0.03398   0.02725  -0.0057   0.0162   1.0000
  10.000   1.0869   0.03653   0.03013  -0.0038   0.0153   1.0000
  10.250   1.0927   0.03956   0.03350  -0.0019   0.0149   1.0000
  10.500   1.0924   0.04271   0.03699   0.0005   0.0148   1.0000
  10.750   1.0851   0.04581   0.04040   0.0033   0.0147   1.0000
  11.000   1.0743   0.04914   0.04400   0.0053   0.0148   1.0000
  11.250   1.0607   0.05284   0.04797   0.0064   0.0148   1.0000
  11.500   1.0461   0.05687   0.05224   0.0065   0.0149   1.0000
  11.750   1.0298   0.06147   0.05706   0.0056   0.0151   1.0000
  12.000   1.0123   0.06663   0.06243   0.0036   0.0152   1.0000
  12.250   0.9939   0.07246   0.06844   0.0007   0.0153   1.0000
  12.500   0.9752   0.07896   0.07511  -0.0032   0.0154   1.0000
  12.750   0.9557   0.08629   0.08258  -0.0080   0.0156   1.0000
  13.000   0.9351   0.09466   0.09109  -0.0138   0.0157   1.0000
  13.250   0.9135   0.10420   0.10075  -0.0202   0.0159   1.0000
  13.500   0.8944   0.11397   0.11058  -0.0264   0.0163   1.0000
  13.750   0.7795   0.11669   0.11360  -0.0240   0.0169   1.0000
<< Back to MH 42 8.94% (mh42-il)

Polar data table (+)

Polar graphs


<< Back to MH 42 8.94% (mh42-il)