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MH 62 9.3% (mh62-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 62 9.3% (mh62-il)
Reynolds number: 100,000
Max Cl/Cd: 45.99 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh62-il-100000-n5.txt
Download as CSV file: xf-mh62-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 62  9.3%                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5629   0.08877   0.08427   0.0012   1.0000   0.0178
  -8.750  -0.5652   0.08333   0.07889  -0.0023   1.0000   0.0177
  -8.500  -0.5690   0.07754   0.07316  -0.0064   1.0000   0.0175
  -8.250  -0.5734   0.07178   0.06745  -0.0112   1.0000   0.0170
  -8.000  -0.5818   0.06454   0.06017  -0.0177   1.0000   0.0166
  -7.750  -0.5864   0.05868   0.05417  -0.0215   1.0000   0.0162
  -7.500  -0.5885   0.05278   0.04800  -0.0244   1.0000   0.0163
  -7.250  -0.5845   0.04774   0.04263  -0.0259   1.0000   0.0162
  -7.000  -0.5763   0.04295   0.03740  -0.0267   1.0000   0.0162
  -6.750  -0.5639   0.03869   0.03267  -0.0269   1.0000   0.0162
  -6.500  -0.5479   0.03491   0.02838  -0.0267   1.0000   0.0162
  -6.250  -0.5291   0.03161   0.02458  -0.0262   1.0000   0.0164
  -6.000  -0.5080   0.02884   0.02135  -0.0257   1.0000   0.0167
  -5.750  -0.4857   0.02648   0.01860  -0.0250   1.0000   0.0172
  -5.500  -0.4634   0.02454   0.01635  -0.0242   1.0000   0.0178
  -5.250  -0.4426   0.02299   0.01459  -0.0231   1.0000   0.0184
  -5.000  -0.4147   0.02103   0.01249  -0.0237   0.9847   0.0202
  -4.750  -0.3805   0.01990   0.01124  -0.0254   0.9706   0.0251
  -4.500  -0.3482   0.01849   0.00966  -0.0264   0.9575   0.0298
  -4.250  -0.3173   0.01734   0.00844  -0.0271   0.9449   0.0432
  -4.000  -0.2896   0.01597   0.00735  -0.0274   0.9325   0.0937
  -3.750  -0.2636   0.01498   0.00683  -0.0274   0.9203   0.2001
  -3.500  -0.2382   0.01443   0.00652  -0.0271   0.9085   0.2861
  -3.250  -0.2136   0.01402   0.00630  -0.0264   0.8970   0.3581
  -3.000  -0.1892   0.01371   0.00609  -0.0254   0.8861   0.4174
  -2.750  -0.1652   0.01342   0.00589  -0.0243   0.8749   0.4727
  -2.500  -0.1410   0.01315   0.00572  -0.0233   0.8639   0.5280
  -2.250  -0.1167   0.01289   0.00553  -0.0221   0.8533   0.5866
  -2.000  -0.0924   0.01263   0.00540  -0.0208   0.8433   0.6501
  -1.750  -0.0680   0.01238   0.00530  -0.0193   0.8332   0.7200
  -1.500  -0.0395   0.01217   0.00522  -0.0185   0.8227   0.7978
  -1.250   0.0007   0.01203   0.00508  -0.0200   0.8130   0.8757
  -1.000   0.0471   0.01196   0.00489  -0.0230   0.8034   0.9349
  -0.750   0.0923   0.01192   0.00470  -0.0263   0.7922   0.9760
  -0.500   0.1303   0.01191   0.00452  -0.0284   0.7805   1.0000
  -0.250   0.1532   0.01195   0.00443  -0.0274   0.7685   1.0000
   0.000   0.1766   0.01199   0.00435  -0.0264   0.7564   1.0000
   0.250   0.2002   0.01204   0.00429  -0.0255   0.7443   1.0000
   0.500   0.2240   0.01210   0.00423  -0.0245   0.7320   1.0000
   0.750   0.2481   0.01216   0.00419  -0.0236   0.7193   1.0000
   1.000   0.2724   0.01222   0.00417  -0.0227   0.7060   1.0000
   1.250   0.2970   0.01229   0.00416  -0.0219   0.6921   1.0000
   1.500   0.3219   0.01237   0.00419  -0.0212   0.6775   1.0000
   1.750   0.3469   0.01245   0.00421  -0.0205   0.6621   1.0000
   2.000   0.3720   0.01254   0.00425  -0.0198   0.6460   1.0000
   2.250   0.3972   0.01263   0.00429  -0.0190   0.6292   1.0000
   2.500   0.4224   0.01273   0.00434  -0.0183   0.6120   1.0000
   2.750   0.4477   0.01285   0.00444  -0.0176   0.5933   1.0000
   3.000   0.4731   0.01299   0.00454  -0.0170   0.5735   1.0000
   3.250   0.4984   0.01315   0.00464  -0.0163   0.5533   1.0000
   3.500   0.5238   0.01333   0.00481  -0.0158   0.5315   1.0000
   3.750   0.5491   0.01353   0.00497  -0.0152   0.5093   1.0000
   4.000   0.5744   0.01378   0.00516  -0.0146   0.4865   1.0000
   4.250   0.5996   0.01404   0.00539  -0.0140   0.4626   1.0000
   4.500   0.6248   0.01434   0.00569  -0.0135   0.4389   1.0000
   4.750   0.6497   0.01468   0.00598  -0.0130   0.4154   1.0000
   5.000   0.6747   0.01504   0.00632  -0.0125   0.3912   1.0000
   5.250   0.6995   0.01543   0.00669  -0.0121   0.3673   1.0000
   5.500   0.7240   0.01586   0.00710  -0.0116   0.3438   1.0000
   5.750   0.7483   0.01632   0.00759  -0.0111   0.3201   1.0000
   6.000   0.7726   0.01680   0.00809  -0.0107   0.2964   1.0000
   6.250   0.7964   0.01733   0.00862  -0.0102   0.2729   1.0000
   6.500   0.8198   0.01791   0.00918  -0.0097   0.2504   1.0000
   6.750   0.8431   0.01851   0.00982  -0.0092   0.2273   1.0000
   7.000   0.8658   0.01917   0.01050  -0.0087   0.2059   1.0000
   7.250   0.8880   0.01989   0.01129  -0.0081   0.1847   1.0000
   7.500   0.9098   0.02066   0.01209  -0.0076   0.1646   1.0000
   7.750   0.9309   0.02148   0.01294  -0.0070   0.1452   1.0000
   8.000   0.9512   0.02239   0.01386  -0.0063   0.1268   1.0000
   8.250   0.9711   0.02333   0.01488  -0.0056   0.1083   1.0000
   8.500   0.9894   0.02442   0.01598  -0.0049   0.0909   1.0000
   8.750   1.0066   0.02562   0.01720  -0.0040   0.0753   1.0000
   9.000   1.0226   0.02693   0.01857  -0.0030   0.0614   1.0000
   9.250   1.0357   0.02850   0.02017  -0.0019   0.0514   1.0000
   9.500   1.0483   0.03003   0.02186  -0.0007   0.0424   1.0000
   9.750   1.0582   0.03181   0.02380   0.0008   0.0368   1.0000
  10.000   1.0657   0.03363   0.02574   0.0023   0.0323   1.0000
  10.250   1.0695   0.03568   0.02792   0.0040   0.0285   1.0000
  10.500   1.0725   0.03759   0.03002   0.0057   0.0254   1.0000
  10.750   1.0726   0.03979   0.03234   0.0071   0.0234   1.0000
  11.000   1.0695   0.04245   0.03508   0.0080   0.0217   1.0000
  11.250   1.0680   0.04530   0.03814   0.0086   0.0199   1.0000
  11.500   1.0669   0.04819   0.04127   0.0088   0.0183   1.0000
  11.750   1.0635   0.05147   0.04477   0.0086   0.0173   1.0000
  12.000   1.0580   0.05523   0.04872   0.0080   0.0165   1.0000
  12.250   1.0514   0.05924   0.05291   0.0068   0.0160   1.0000
  12.500   1.0438   0.06361   0.05745   0.0052   0.0156   1.0000
  12.750   1.0335   0.06858   0.06257   0.0028   0.0151   1.0000
  13.000   1.0221   0.07400   0.06814   0.0000   0.0147   1.0000
  13.250   1.0107   0.07992   0.07428  -0.0030   0.0150   1.0000
  13.500   0.9958   0.08661   0.08112  -0.0069   0.0146   1.0000
  13.750   0.9795   0.09422   0.08893  -0.0114   0.0149   1.0000
  14.000   0.9587   0.10343   0.09836  -0.0170   0.0152   1.0000
  14.250   0.9307   0.11528   0.11042  -0.0241   0.0160   1.0000
  14.500   0.9004   0.12881   0.12409  -0.0318   0.0173   1.0000
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