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MH 122 9.32% (mh122-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 122 9.32% (mh122-il)
Reynolds number: 100,000
Max Cl/Cd: 58.66 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh122-il-100000-n5.txt
Download as CSV file: xf-mh122-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4215   0.10172   0.09706  -0.0348   1.0000   0.0211
  -8.250  -0.4278   0.09935   0.09474  -0.0332   1.0000   0.0202
  -8.000  -0.4337   0.09673   0.09219  -0.0325   0.9996   0.0195
  -7.750  -0.4260   0.09241   0.08781  -0.0362   0.9959   0.0184
  -7.500  -0.4213   0.08782   0.08325  -0.0402   0.9914   0.0174
  -7.250  -0.4184   0.08336   0.07882  -0.0443   0.9858   0.0166
  -7.000  -0.4120   0.07773   0.07322  -0.0507   0.9803   0.0157
  -6.750  -0.4012   0.06933   0.06486  -0.0619   0.9730   0.0146
  -6.500  -0.3862   0.06026   0.05550  -0.0720   0.9669   0.0132
  -6.000  -0.3487   0.05125   0.04585  -0.0802   0.9586   0.0124
  -5.750  -0.3328   0.04652   0.04080  -0.0831   0.9540   0.0121
  -5.500  -0.3122   0.04217   0.03603  -0.0857   0.9502   0.0119
  -5.250  -0.2850   0.03806   0.03143  -0.0885   0.9475   0.0117
  -5.000  -0.2541   0.03442   0.02723  -0.0911   0.9457   0.0116
  -4.750  -0.2257   0.03142   0.02370  -0.0924   0.9432   0.0117
  -4.500  -0.2001   0.02908   0.02088  -0.0925   0.9402   0.0118
  -4.250  -0.1713   0.02749   0.01889  -0.0929   0.9377   0.0126
  -4.000  -0.1419   0.02532   0.01650  -0.0941   0.9359   0.0155
  -3.750  -0.1108   0.02414   0.01511  -0.0949   0.9341   0.0186
  -3.500  -0.0790   0.02283   0.01363  -0.0956   0.9326   0.0205
  -3.250  -0.0494   0.02174   0.01229  -0.0961   0.9306   0.0237
  -3.000  -0.0243   0.02098   0.01147  -0.0961   0.9271   0.0368
  -2.750   0.0075   0.01934   0.01044  -0.0979   0.9251   0.1567
  -2.500   0.0359   0.01824   0.01050  -0.0989   0.9232   0.4801
  -2.250   0.0649   0.01825   0.01056  -0.0990   0.9208   0.5554
  -2.000   0.0944   0.01831   0.01065  -0.0991   0.9188   0.6168
  -1.750   0.1133   0.01843   0.01076  -0.0972   0.9142   0.6496
  -1.500   0.1397   0.01848   0.01066  -0.0970   0.9108   0.6684
  -1.250   0.1698   0.01850   0.01057  -0.0976   0.9082   0.6849
  -1.000   0.2015   0.01852   0.01051  -0.0985   0.9061   0.7012
  -0.750   0.2240   0.01862   0.01057  -0.0976   0.9016   0.7178
  -0.500   0.2495   0.01870   0.01059  -0.0973   0.8976   0.7364
  -0.250   0.2791   0.01872   0.01060  -0.0977   0.8948   0.7570
   0.000   0.3106   0.01870   0.01059  -0.0984   0.8925   0.7807
   0.250   0.3282   0.01882   0.01077  -0.0965   0.8866   0.8081
   0.500   0.3535   0.01878   0.01081  -0.0959   0.8826   0.8451
   0.750   0.3854   0.01863   0.01076  -0.0966   0.8800   0.9114
   1.000   0.4128   0.01876   0.01086  -0.0970   0.8743   1.0000
   1.250   0.4436   0.01892   0.01097  -0.0980   0.8698   1.0000
   1.500   0.4793   0.01899   0.01102  -0.0998   0.8668   1.0000
   1.750   0.5044   0.01923   0.01127  -0.0996   0.8606   1.0000
   2.000   0.5359   0.01932   0.01136  -0.1005   0.8557   1.0000
   2.250   0.5740   0.01925   0.01133  -0.1025   0.8527   1.0000
   2.500   0.5958   0.01949   0.01161  -0.1016   0.8442   1.0000
   2.750   0.6342   0.01930   0.01149  -0.1034   0.8402   1.0000
   3.000   0.6592   0.01939   0.01173  -0.1028   0.8312   1.0000
   3.250   0.7019   0.01893   0.01139  -0.1051   0.8262   1.0000
   3.500   0.7300   0.01873   0.01132  -0.1047   0.8151   1.0000
   3.750   0.7643   0.01819   0.01097  -0.1050   0.8023   1.0000
   4.000   0.8033   0.01736   0.01029  -0.1058   0.7862   1.0000
   4.250   0.8235   0.01710   0.01016  -0.1036   0.7649   1.0000
   4.500   0.8474   0.01679   0.00998  -0.1021   0.7411   1.0000
   4.750   0.8687   0.01659   0.00992  -0.1001   0.7104   1.0000
   5.000   0.9023   0.01606   0.00943  -0.0999   0.6534   1.0000
   5.250   0.9473   0.01615   0.00869  -0.1014   0.4745   1.0000
   5.500   0.9544   0.01758   0.00937  -0.0976   0.3457   1.0000
   5.750   0.9629   0.01905   0.01023  -0.0946   0.2411   1.0000
   6.000   0.9753   0.02040   0.01115  -0.0923   0.1675   1.0000
   6.250   0.9899   0.02159   0.01210  -0.0904   0.1253   1.0000
   6.500   1.0052   0.02271   0.01309  -0.0885   0.0955   1.0000
   6.750   1.0205   0.02384   0.01422  -0.0865   0.0776   1.0000
   7.000   1.0353   0.02504   0.01541  -0.0846   0.0629   1.0000
   7.250   1.0506   0.02624   0.01665  -0.0827   0.0506   1.0000
   7.500   1.0649   0.02773   0.01827  -0.0805   0.0430   1.0000
   7.750   1.0803   0.02915   0.01986  -0.0788   0.0343   1.0000
   8.000   1.0966   0.03080   0.02164  -0.0771   0.0281   1.0000
   8.250   1.1144   0.03268   0.02371  -0.0757   0.0218   1.0000
   8.500   1.1320   0.03470   0.02588  -0.0743   0.0179   1.0000
   8.750   1.1529   0.03791   0.02935  -0.0736   0.0152   1.0000
   9.000   1.1713   0.04008   0.03192  -0.0722   0.0126   1.0000
   9.250   1.1853   0.04275   0.03495  -0.0704   0.0112   1.0000
   9.500   1.1945   0.04582   0.03840  -0.0681   0.0105   1.0000
   9.750   1.1980   0.04891   0.04186  -0.0653   0.0101   1.0000
  10.000   1.1964   0.05209   0.04539  -0.0621   0.0098   1.0000
  10.250   1.1904   0.05544   0.04909  -0.0587   0.0096   1.0000
  10.500   1.1808   0.05901   0.05298  -0.0556   0.0095   1.0000
  10.750   1.1680   0.06283   0.05712  -0.0527   0.0094   1.0000
  11.000   1.1527   0.06695   0.06154  -0.0504   0.0094   1.0000
  11.250   1.1356   0.07147   0.06635  -0.0489   0.0094   1.0000
  11.500   1.1168   0.07646   0.07161  -0.0483   0.0094   1.0000
  11.750   1.0965   0.08213   0.07753  -0.0488   0.0095   1.0000
  12.000   1.0742   0.08879   0.08443  -0.0508   0.0096   1.0000
  12.250   1.0494   0.09701   0.09287  -0.0547   0.0099   1.0000
  12.500   1.0224   0.10777   0.10382  -0.0616   0.0103   1.0000
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