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MH 122 9.32% (mh122-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 122 9.32% (mh122-il)
Reynolds number: 50,000
Max Cl/Cd: 37.95 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh122-il-50000-n5.txt
Download as CSV file: xf-mh122-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 122  9.32%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.4398   0.09734   0.09089  -0.0358   1.0000   0.0440
  -7.500  -0.4492   0.09480   0.08845  -0.0341   1.0000   0.0426
  -7.250  -0.4608   0.09245   0.08620  -0.0326   1.0000   0.0415
  -7.000  -0.4704   0.08953   0.08337  -0.0323   1.0000   0.0403
  -6.750  -0.4778   0.08590   0.07980  -0.0333   1.0000   0.0390
  -6.500  -0.4836   0.08089   0.07494  -0.0367   1.0000   0.0374
  -6.250  -0.4844   0.07395   0.06766  -0.0454   1.0000   0.0338
  -6.000  -0.4814   0.06994   0.06365  -0.0455   1.0000   0.0331
  -5.750  -0.4756   0.06578   0.05940  -0.0467   1.0000   0.0326
  -5.500  -0.4664   0.06148   0.05483  -0.0485   1.0000   0.0319
  -5.250  -0.4527   0.05705   0.05015  -0.0508   1.0000   0.0313
  -5.000  -0.4345   0.05262   0.04536  -0.0534   1.0000   0.0306
  -4.750  -0.4117   0.04820   0.04048  -0.0560   1.0000   0.0301
  -4.500  -0.3855   0.04418   0.03593  -0.0583   1.0000   0.0298
  -4.250  -0.3575   0.04065   0.03184  -0.0600   1.0000   0.0298
  -4.000  -0.3287   0.03758   0.02819  -0.0612   1.0000   0.0301
  -3.750  -0.3000   0.03498   0.02504  -0.0617   1.0000   0.0309
  -3.500  -0.2691   0.03298   0.02249  -0.0623   0.9988   0.0329
  -3.250  -0.2386   0.03116   0.02048  -0.0633   0.9967   0.0389
  -3.000  -0.2080   0.02982   0.01883  -0.0635   0.9947   0.0443
  -2.750  -0.1788   0.02846   0.01728  -0.0636   0.9926   0.0495
  -2.500  -0.1470   0.02731   0.01586  -0.0648   0.9902   0.0726
  -2.250  -0.1072   0.02501   0.01417  -0.0684   0.9893   0.1747
  -2.000  -0.0823   0.02394   0.01477  -0.0677   0.9872   0.5844
  -1.750  -0.0666   0.02419   0.01528  -0.0638   0.9836   0.6991
  -1.500  -0.0512   0.02422   0.01530  -0.0602   0.9795   0.7608
  -1.250  -0.0270   0.02420   0.01507  -0.0596   0.9755   0.7925
  -1.000  -0.0005   0.02422   0.01491  -0.0594   0.9717   0.8241
  -0.750   0.0250   0.02416   0.01466  -0.0592   0.9676   0.8658
  -0.500   0.0577   0.02386   0.01425  -0.0609   0.9615   0.9871
  -0.250   0.0972   0.02431   0.01433  -0.0646   0.9582   1.0000
   0.000   0.1294   0.02465   0.01438  -0.0666   0.9534   1.0000
   0.250   0.1629   0.02507   0.01450  -0.0687   0.9488   1.0000
   0.500   0.1995   0.02559   0.01480  -0.0713   0.9449   1.0000
   0.750   0.2271   0.02594   0.01500  -0.0722   0.9389   1.0000
   1.000   0.2607   0.02643   0.01535  -0.0741   0.9340   1.0000
   1.250   0.2913   0.02689   0.01569  -0.0754   0.9284   1.0000
   1.500   0.3218   0.02734   0.01606  -0.0767   0.9223   1.0000
   1.750   0.3553   0.02785   0.01651  -0.0784   0.9169   1.0000
   2.000   0.3831   0.02828   0.01692  -0.0791   0.9096   1.0000
   2.250   0.4169   0.02877   0.01741  -0.0809   0.9037   1.0000
   2.500   0.4449   0.02920   0.01789  -0.0815   0.8956   1.0000
   2.750   0.4754   0.02964   0.01838  -0.0826   0.8879   1.0000
   3.000   0.5088   0.03006   0.01888  -0.0841   0.8803   1.0000
   3.250   0.5361   0.03047   0.01937  -0.0845   0.8707   1.0000
   3.500   0.5685   0.03083   0.01986  -0.0856   0.8618   1.0000
   3.750   0.6041   0.03111   0.02040  -0.0872   0.8528   1.0000
   4.000   0.6331   0.03138   0.02084  -0.0875   0.8410   1.0000
   4.250   0.6640   0.03154   0.02120  -0.0881   0.8286   1.0000
   4.500   0.6972   0.03153   0.02152  -0.0887   0.8151   1.0000
   4.750   0.7339   0.03121   0.02149  -0.0894   0.8001   1.0000
   5.000   0.7638   0.03078   0.02135  -0.0888   0.7799   1.0000
   5.250   0.8020   0.02962   0.02054  -0.0885   0.7565   1.0000
   5.500   0.8280   0.02866   0.01989  -0.0862   0.7260   1.0000
   5.750   0.8526   0.02765   0.01931  -0.0836   0.6898   1.0000
   6.000   0.8743   0.02689   0.01884  -0.0807   0.6387   1.0000
   6.250   0.9340   0.02461   0.01598  -0.0802   0.4540   1.0000
   6.500   0.9396   0.02644   0.01679  -0.0762   0.3094   1.0000
   6.750   0.9428   0.02856   0.01826  -0.0730   0.2217   1.0000
   7.000   0.9515   0.03058   0.01986  -0.0707   0.1668   1.0000
   7.250   0.9657   0.03247   0.02157  -0.0689   0.1323   1.0000
   7.500   0.9834   0.03428   0.02331  -0.0677   0.1058   1.0000
   7.750   1.0068   0.03624   0.02523  -0.0671   0.0864   1.0000
   8.000   1.0398   0.03830   0.02753  -0.0674   0.0684   1.0000
   8.250   1.0797   0.04117   0.03080  -0.0688   0.0549   1.0000
   8.500   1.1108   0.04435   0.03424  -0.0692   0.0454   1.0000
   8.750   1.1294   0.04700   0.03717  -0.0682   0.0385   1.0000
   9.000   1.1527   0.05166   0.04229  -0.0675   0.0355   1.0000
   9.250   1.1617   0.05567   0.04698  -0.0649   0.0328   1.0000
   9.500   1.1637   0.05884   0.05057  -0.0621   0.0299   1.0000
   9.750   1.1623   0.06137   0.05331  -0.0593   0.0276   1.0000
  10.000   1.1576   0.06464   0.05675  -0.0566   0.0262   1.0000
  10.250   1.1480   0.06879   0.06112  -0.0536   0.0258   1.0000
  10.500   1.1349   0.07262   0.06532  -0.0506   0.0256   1.0000
  10.750   1.1195   0.07668   0.06968  -0.0483   0.0256   1.0000
  11.000   1.1024   0.08102   0.07430  -0.0467   0.0256   1.0000
  11.250   1.0843   0.08571   0.07923  -0.0460   0.0256   1.0000
  11.500   1.0660   0.09079   0.08451  -0.0463   0.0257   1.0000
  11.750   1.0478   0.09631   0.09021  -0.0476   0.0258   1.0000
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