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MH 82 13.31% (mh82-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: MH 82 13.31% (mh82-il)
Reynolds number: 1,000,000
Max Cl/Cd: 115.34 at α=10°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh82-il-1000000.txt
Download as CSV file: xf-mh82-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 82  13.31%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3306   0.08662   0.08410   0.0083   0.5940   0.0126
  -8.750  -0.3273   0.08282   0.08029   0.0068   0.5862   0.0127
  -8.500  -0.3275   0.07818   0.07563   0.0048   0.5793   0.0128
  -8.250  -0.3273   0.07400   0.07143   0.0031   0.5722   0.0129
  -8.000  -0.3283   0.06953   0.06696   0.0010   0.5655   0.0131
  -7.750  -0.3342   0.06434   0.06177  -0.0015   0.5601   0.0133
  -7.500  -0.3435   0.05898   0.05641  -0.0045   0.5554   0.0134
  -7.250  -0.3686   0.05269   0.05015  -0.0095   0.5532   0.0132
  -7.000  -0.3830   0.04450   0.04188  -0.0160   0.5503   0.0133
  -6.750  -0.3885   0.03649   0.03371  -0.0200   0.5467   0.0135
  -6.500  -0.4095   0.02138   0.01762  -0.0226   0.5492   0.0150
  -6.250  -0.4019   0.01588   0.01186  -0.0227   0.5418   0.0154
  -6.000  -0.3808   0.01425   0.01012  -0.0225   0.5324   0.0156
  -5.750  -0.3591   0.01273   0.00844  -0.0223   0.5230   0.0158
  -5.500  -0.3367   0.01133   0.00688  -0.0220   0.5144   0.0162
  -5.250  -0.3255   0.01592   0.00979  -0.0206   0.5165   0.0098
  -5.000  -0.2979   0.01544   0.00917  -0.0202   0.5063   0.0097
  -4.750  -0.2701   0.01494   0.00858  -0.0199   0.4968   0.0096
  -4.500  -0.2437   0.01384   0.00736  -0.0195   0.4874   0.0095
  -4.250  -0.2165   0.01305   0.00647  -0.0191   0.4787   0.0095
  -4.000  -0.1892   0.01244   0.00576  -0.0188   0.4700   0.0095
  -3.750  -0.1615   0.01192   0.00517  -0.0184   0.4617   0.0095
  -3.500  -0.1337   0.01151   0.00468  -0.0182   0.4531   0.0095
  -3.250  -0.1056   0.01115   0.00426  -0.0179   0.4446   0.0096
  -3.000  -0.0782   0.01060   0.00363  -0.0176   0.4362   0.0099
  -2.750  -0.0500   0.01027   0.00325  -0.0174   0.4283   0.0103
  -2.500  -0.0215   0.01008   0.00300  -0.0172   0.4203   0.0110
  -2.250   0.0072   0.00989   0.00277  -0.0171   0.4132   0.0119
  -2.000   0.0357   0.00969   0.00251  -0.0169   0.4052   0.0136
  -1.750   0.0644   0.00950   0.00231  -0.0168   0.3984   0.0171
  -1.500   0.0928   0.00925   0.00210  -0.0167   0.3906   0.0358
  -1.250   0.1208   0.00895   0.00198  -0.0166   0.3839   0.0844
  -1.000   0.1492   0.00877   0.00191  -0.0165   0.3770   0.1238
  -0.750   0.1775   0.00861   0.00187  -0.0165   0.3705   0.1701
  -0.500   0.2054   0.00832   0.00182  -0.0165   0.3645   0.2508
  -0.250   0.2327   0.00797   0.00179  -0.0164   0.3578   0.3666
   0.000   0.2585   0.00736   0.00178  -0.0162   0.3523   0.5618
   0.500   0.3056   0.00657   0.00190  -0.0138   0.3403   0.8706
   0.750   0.3309   0.00655   0.00195  -0.0128   0.3360   0.9157
   1.000   0.3572   0.00659   0.00199  -0.0120   0.3309   0.9428
   1.250   0.3861   0.00669   0.00203  -0.0118   0.3251   0.9615
   1.500   0.4186   0.00676   0.00206  -0.0125   0.3205   0.9743
   1.750   0.4535   0.00685   0.00209  -0.0137   0.3153   0.9832
   2.000   0.4917   0.00698   0.00214  -0.0157   0.3095   0.9881
   2.250   0.5303   0.00706   0.00218  -0.0178   0.3056   0.9927
   2.500   0.5742   0.00715   0.00221  -0.0210   0.3009   0.9977
   2.750   0.6103   0.00727   0.00226  -0.0226   0.2960   1.0000
   3.000   0.6354   0.00739   0.00234  -0.0220   0.2919   1.0000
   3.250   0.6610   0.00747   0.00240  -0.0215   0.2892   1.0000
   3.500   0.6866   0.00757   0.00248  -0.0209   0.2859   1.0000
   3.750   0.7124   0.00770   0.00257  -0.0205   0.2825   1.0000
   4.000   0.7381   0.00788   0.00269  -0.0200   0.2782   1.0000
   4.250   0.7645   0.00798   0.00278  -0.0196   0.2757   1.0000
   4.500   0.7911   0.00808   0.00288  -0.0193   0.2731   1.0000
   4.750   0.8178   0.00821   0.00298  -0.0190   0.2702   1.0000
   5.000   0.8445   0.00836   0.00310  -0.0188   0.2671   1.0000
   5.250   0.8712   0.00857   0.00328  -0.0186   0.2631   1.0000
   5.500   0.8986   0.00868   0.00339  -0.0185   0.2610   1.0000
   5.750   0.9261   0.00879   0.00351  -0.0184   0.2588   1.0000
   6.000   0.9536   0.00893   0.00364  -0.0183   0.2563   1.0000
   6.250   0.9809   0.00909   0.00379  -0.0182   0.2535   1.0000
   6.500   1.0080   0.00930   0.00397  -0.0182   0.2501   1.0000
   6.750   1.0352   0.00950   0.00416  -0.0181   0.2472   1.0000
   7.000   1.0629   0.00962   0.00431  -0.0181   0.2454   1.0000
   7.250   1.0904   0.00976   0.00447  -0.0181   0.2433   1.0000
   7.500   1.1178   0.00993   0.00464  -0.0182   0.2407   1.0000
   7.750   1.1449   0.01013   0.00483  -0.0182   0.2379   1.0000
   8.000   1.1714   0.01040   0.00508  -0.0181   0.2344   1.0000
   8.250   1.1985   0.01059   0.00529  -0.0181   0.2324   1.0000
   8.500   1.2259   0.01073   0.00547  -0.0181   0.2305   1.0000
   8.750   1.2530   0.01090   0.00566  -0.0182   0.2281   1.0000
   9.000   1.2798   0.01110   0.00587  -0.0182   0.2254   1.0000
   9.250   1.3060   0.01136   0.00613  -0.0182   0.2225   1.0000
   9.500   1.3316   0.01169   0.00645  -0.0181   0.2192   1.0000
   9.750   1.3586   0.01183   0.00665  -0.0181   0.2174   1.0000
  10.000   1.3852   0.01201   0.00687  -0.0181   0.2150   1.0000
  10.250   1.4113   0.01224   0.00712  -0.0181   0.2122   1.0000
  10.500   1.4367   0.01253   0.00741  -0.0180   0.2091   1.0000
  10.750   1.4610   0.01290   0.00778  -0.0178   0.2055   1.0000
  11.000   1.4873   0.01307   0.00802  -0.0178   0.2034   1.0000
  11.250   1.5129   0.01330   0.00829  -0.0178   0.2007   1.0000
  11.500   1.5375   0.01360   0.00861  -0.0176   0.1974   1.0000
  11.750   1.5606   0.01401   0.00902  -0.0174   0.1937   1.0000
  12.000   1.5848   0.01431   0.00937  -0.0172   0.1912   1.0000
  12.250   1.6092   0.01457   0.00969  -0.0170   0.1883   1.0000
  12.500   1.6321   0.01493   0.01007  -0.0167   0.1848   1.0000
  12.750   1.6528   0.01542   0.01057  -0.0162   0.1809   1.0000
  13.000   1.6750   0.01579   0.01099  -0.0159   0.1781   1.0000
  13.250   1.6967   0.01615   0.01140  -0.0155   0.1749   1.0000
  13.500   1.7158   0.01665   0.01193  -0.0148   0.1710   1.0000
  13.750   1.7317   0.01730   0.01259  -0.0138   0.1668   1.0000
  14.000   1.7502   0.01772   0.01308  -0.0131   0.1633   1.0000
  14.250   1.7591   0.01841   0.01380  -0.0111   0.1592   1.0000
  14.500   1.7617   0.01951   0.01491  -0.0090   0.1546   1.0000
  14.750   1.7717   0.02041   0.01588  -0.0080   0.1504   1.0000
  15.000   1.7727   0.02207   0.01755  -0.0068   0.1445   1.0000
  15.250   1.7788   0.02355   0.01908  -0.0062   0.1405   1.0000
  15.500   1.7807   0.02550   0.02107  -0.0058   0.1354   1.0000
  15.750   1.7784   0.02797   0.02358  -0.0056   0.1311   1.0000
  16.000   1.7810   0.03009   0.02577  -0.0056   0.1275   1.0000
  16.250   1.7759   0.03305   0.02878  -0.0058   0.1234   1.0000
  16.500   1.7623   0.03698   0.03274  -0.0063   0.1162   1.0000
  16.750   1.7608   0.03976   0.03563  -0.0067   0.1159   1.0000
  17.000   1.7324   0.04554   0.04141  -0.0079   0.1077   1.0000
  17.250   1.7226   0.04939   0.04536  -0.0088   0.1058   1.0000
  17.500   1.6961   0.05536   0.05138  -0.0105   0.1008   1.0000
  17.750   1.6737   0.06116   0.05726  -0.0124   0.0967   1.0000
  18.000   1.6593   0.06610   0.06228  -0.0140   0.0947   1.0000
  18.250   1.6322   0.07290   0.06915  -0.0166   0.0908   1.0000
  18.500   1.6232   0.07736   0.07372  -0.0183   0.0908   1.0000
  18.750   1.5975   0.08432   0.08075  -0.0211   0.0868   1.0000
  19.000   1.5815   0.09003   0.08654  -0.0235   0.0845   1.0000
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