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MH 83 13.29% (mh83-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: MH 83 13.29% (mh83-il)
Reynolds number: 500,000
Max Cl/Cd: 97.59 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh83-il-500000-n5.txt
Download as CSV file: xf-mh83-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 83  13.29%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2589   0.09066   0.08706  -0.0114   0.5755   0.0120
  -8.250  -0.2578   0.08631   0.08270  -0.0136   0.5686   0.0115
  -7.750  -0.4079   0.02978   0.02527  -0.0605   0.5938   0.0104
  -7.500  -0.3874   0.02648   0.02149  -0.0624   0.5839   0.0105
  -7.250  -0.3650   0.02375   0.01837  -0.0635   0.5744   0.0106
  -7.000  -0.3399   0.02202   0.01636  -0.0641   0.5638   0.0107
  -6.750  -0.3137   0.02076   0.01488  -0.0644   0.5539   0.0109
  -6.250  -0.2594   0.01897   0.01273  -0.0648   0.5334   0.0113
  -6.000  -0.2317   0.01821   0.01179  -0.0649   0.5239   0.0115
  -5.750  -0.2038   0.01746   0.01086  -0.0649   0.5138   0.0118
  -5.500  -0.1758   0.01673   0.00994  -0.0649   0.5044   0.0121
  -5.250  -0.1476   0.01601   0.00904  -0.0649   0.4951   0.0123
  -5.000  -0.1192   0.01534   0.00822  -0.0649   0.4869   0.0125
  -4.750  -0.0907   0.01477   0.00750  -0.0649   0.4778   0.0127
  -4.500  -0.0621   0.01427   0.00687  -0.0648   0.4691   0.0130
  -4.250  -0.0334   0.01386   0.00634  -0.0648   0.4598   0.0132
  -4.000  -0.0048   0.01333   0.00573  -0.0648   0.4520   0.0135
  -3.750   0.0239   0.01295   0.00529  -0.0648   0.4440   0.0139
  -3.500   0.0528   0.01265   0.00492  -0.0648   0.4369   0.0143
  -3.250   0.0818   0.01238   0.00458  -0.0647   0.4289   0.0148
  -3.000   0.1108   0.01215   0.00428  -0.0647   0.4212   0.0153
  -2.750   0.1399   0.01194   0.00399  -0.0647   0.4133   0.0158
  -2.500   0.1689   0.01175   0.00373  -0.0647   0.4060   0.0166
  -2.250   0.1981   0.01157   0.00352  -0.0647   0.3995   0.0178
  -2.000   0.2272   0.01145   0.00333  -0.0647   0.3927   0.0190
  -1.750   0.2564   0.01131   0.00314  -0.0646   0.3869   0.0204
  -1.500   0.2855   0.01120   0.00298  -0.0646   0.3804   0.0227
  -1.000   0.3437   0.01090   0.00273  -0.0647   0.3678   0.0516
  -0.750   0.3726   0.01075   0.00267  -0.0648   0.3616   0.0862
  -0.500   0.4016   0.01067   0.00263  -0.0648   0.3564   0.1143
  -0.250   0.4306   0.01054   0.00262  -0.0649   0.3515   0.1549
   0.000   0.4594   0.01040   0.00263  -0.0650   0.3463   0.2142
   0.250   0.4881   0.01032   0.00266  -0.0651   0.3413   0.2707
   0.500   0.5170   0.01024   0.00269  -0.0652   0.3367   0.3189
   0.750   0.5459   0.01019   0.00273  -0.0652   0.3316   0.3636
   1.000   0.5745   0.01017   0.00279  -0.0653   0.3268   0.4147
   1.250   0.6031   0.01011   0.00286  -0.0653   0.3231   0.4775
   1.500   0.6315   0.01000   0.00294  -0.0653   0.3193   0.5535
   1.750   0.6593   0.00989   0.00304  -0.0652   0.3154   0.6428
   2.000   0.6848   0.00966   0.00316  -0.0645   0.3116   0.7727
   2.500   0.7419   0.00949   0.00327  -0.0640   0.3044   1.0000
   2.750   0.7706   0.00963   0.00335  -0.0641   0.3008   1.0000
   3.000   0.7992   0.00980   0.00345  -0.0641   0.2975   1.0000
   3.250   0.8275   0.00998   0.00357  -0.0641   0.2943   1.0000
   3.500   0.8560   0.01014   0.00369  -0.0641   0.2917   1.0000
   3.750   0.8845   0.01028   0.00381  -0.0641   0.2888   1.0000
   4.000   0.9128   0.01044   0.00394  -0.0641   0.2856   1.0000
   4.250   0.9410   0.01062   0.00408  -0.0641   0.2825   1.0000
   4.500   0.9690   0.01082   0.00423  -0.0641   0.2797   1.0000
   4.750   0.9968   0.01103   0.00441  -0.0641   0.2772   1.0000
   5.000   1.0250   0.01119   0.00457  -0.0641   0.2750   1.0000
   5.250   1.0530   0.01136   0.00473  -0.0641   0.2724   1.0000
   5.500   1.0807   0.01155   0.00491  -0.0641   0.2696   1.0000
   5.750   1.1083   0.01176   0.00510  -0.0641   0.2669   1.0000
   6.000   1.1356   0.01200   0.00531  -0.0641   0.2645   1.0000
   6.250   1.1627   0.01225   0.00555  -0.0640   0.2622   1.0000
   6.500   1.1903   0.01243   0.00575  -0.0640   0.2601   1.0000
   6.750   1.2177   0.01263   0.00597  -0.0640   0.2577   1.0000
   7.000   1.2448   0.01285   0.00620  -0.0640   0.2552   1.0000
   7.250   1.2716   0.01309   0.00645  -0.0639   0.2530   1.0000
   7.500   1.2981   0.01335   0.00671  -0.0638   0.2507   1.0000
   7.750   1.3242   0.01365   0.00700  -0.0637   0.2482   1.0000
   8.000   1.3507   0.01389   0.00727  -0.0636   0.2462   1.0000
   8.250   1.3772   0.01412   0.00754  -0.0635   0.2440   1.0000
   8.500   1.4034   0.01438   0.00784  -0.0634   0.2419   1.0000
   8.750   1.4292   0.01465   0.00814  -0.0633   0.2397   1.0000
   9.000   1.4546   0.01495   0.00845  -0.0632   0.2372   1.0000
   9.250   1.4794   0.01530   0.00881  -0.0630   0.2347   1.0000
   9.500   1.5040   0.01565   0.00918  -0.0627   0.2325   1.0000
   9.750   1.5293   0.01592   0.00952  -0.0625   0.2307   1.0000
  10.000   1.5540   0.01622   0.00988  -0.0623   0.2283   1.0000
  10.250   1.5781   0.01655   0.01025  -0.0620   0.2257   1.0000
  10.500   1.6015   0.01691   0.01065  -0.0617   0.2232   1.0000
  10.750   1.6239   0.01733   0.01109  -0.0613   0.2207   1.0000
  11.000   1.6458   0.01777   0.01156  -0.0608   0.2183   1.0000
  11.250   1.6685   0.01812   0.01199  -0.0604   0.2159   1.0000
  11.500   1.6902   0.01852   0.01247  -0.0599   0.2133   1.0000
  11.750   1.7105   0.01898   0.01297  -0.0592   0.2104   1.0000
  12.000   1.7288   0.01952   0.01354  -0.0584   0.2076   1.0000
  12.250   1.7449   0.02013   0.01420  -0.0573   0.2048   1.0000
  12.500   1.7610   0.02063   0.01479  -0.0561   0.2024   1.0000
  12.750   1.7728   0.02126   0.01550  -0.0545   0.1996   1.0000
  13.000   1.7823   0.02209   0.01638  -0.0530   0.1966   1.0000
  13.250   1.7901   0.02315   0.01749  -0.0516   0.1937   1.0000
  13.500   1.7980   0.02431   0.01871  -0.0505   0.1905   1.0000
  13.750   1.8081   0.02544   0.01992  -0.0497   0.1867   1.0000
  14.000   1.8153   0.02687   0.02142  -0.0490   0.1833   1.0000
  14.250   1.8175   0.02879   0.02337  -0.0483   0.1795   1.0000
  14.500   1.8239   0.03047   0.02515  -0.0479   0.1758   1.0000
  14.750   1.8275   0.03249   0.02724  -0.0476   0.1715   1.0000
  15.000   1.8256   0.03510   0.02990  -0.0474   0.1675   1.0000
  15.250   1.8252   0.03767   0.03254  -0.0474   0.1640   1.0000
  15.500   1.8236   0.04045   0.03541  -0.0475   0.1593   1.0000
  15.750   1.8149   0.04412   0.03913  -0.0479   0.1551   1.0000
  16.000   1.8078   0.04768   0.04277  -0.0484   0.1513   1.0000
  16.250   1.7977   0.05171   0.04688  -0.0492   0.1461   1.0000
  16.500   1.7816   0.05666   0.05190  -0.0503   0.1422   1.0000
  16.750   1.7703   0.06118   0.05650  -0.0515   0.1378   1.0000
  17.000   1.7547   0.06644   0.06184  -0.0531   0.1332   1.0000
  17.250   1.7337   0.07264   0.06811  -0.0551   0.1292   1.0000
  17.500   1.7206   0.07788   0.07344  -0.0569   0.1248   1.0000
  17.750   1.7012   0.08414   0.07977  -0.0592   0.1204   1.0000
  18.000   1.6833   0.09036   0.08607  -0.0615   0.1172   1.0000
  18.250   1.6683   0.09623   0.09203  -0.0639   0.1129   1.0000
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