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MH 70 11.08% (mh70-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 70 11.08% (mh70-il)
Reynolds number: 100,000
Max Cl/Cd: 50.65 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh70-il-100000.txt
Download as CSV file: xf-mh70-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 70  11.08%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3556   0.09508   0.09051  -0.0257   1.0000   0.1069
  -8.250  -0.3825   0.09280   0.08841  -0.0331   1.0000   0.1105
  -8.000  -0.3726   0.08818   0.08384  -0.0323   1.0000   0.1126
  -7.750  -0.3525   0.08516   0.08083  -0.0296   1.0000   0.1169
  -7.500  -0.3568   0.08237   0.07815  -0.0310   1.0000   0.1216
  -7.250  -0.3968   0.08006   0.07603  -0.0380   1.0000   0.1250
  -7.000  -0.4379   0.07938   0.07535  -0.0374   1.0000   0.1255
  -6.750  -0.4209   0.07578   0.07195  -0.0310   1.0000   0.1276
  -6.500  -0.4266   0.07445   0.07070  -0.0266   1.0000   0.1293
  -6.250  -0.4363   0.07295   0.06925  -0.0236   1.0000   0.1320
  -6.000  -0.4488   0.07090   0.06721  -0.0231   1.0000   0.1362
  -5.750  -0.4255   0.06559   0.06182  -0.0299   0.9928   0.1456
  -5.500  -0.3966   0.06046   0.05653  -0.0375   0.9845   0.1594
  -5.250  -0.3655   0.04156   0.03594  -0.0515   0.9746   0.0730
  -5.000  -0.3310   0.03522   0.02865  -0.0537   0.9682   0.0570
  -4.750  -0.2970   0.03146   0.02432  -0.0556   0.9610   0.0538
  -4.500  -0.2582   0.02855   0.02080  -0.0577   0.9550   0.0534
  -4.250  -0.2226   0.02679   0.01863  -0.0590   0.9470   0.0570
  -4.000  -0.1760   0.02485   0.01623  -0.0618   0.9423   0.0595
  -3.750  -0.1461   0.02310   0.01454  -0.0622   0.9334   0.0654
  -3.500  -0.1009   0.02157   0.01303  -0.0652   0.9284   0.0792
  -3.250  -0.0708   0.02034   0.01195  -0.0655   0.9194   0.1066
  -3.000  -0.0360   0.01810   0.01086  -0.0670   0.9132   0.2948
  -2.750  -0.0118   0.01750   0.01081  -0.0663   0.9031   0.4413
  -2.500   0.0223   0.01684   0.01071  -0.0666   0.8967   0.5871
  -2.250   0.0419   0.01652   0.01085  -0.0638   0.8861   0.7143
  -2.000   0.0819   0.01623   0.01081  -0.0633   0.8809   0.8617
  -1.750   0.1598   0.01613   0.01048  -0.0711   0.8752   0.9591
  -1.500   0.2580   0.01562   0.00957  -0.0841   0.8709   1.0000
  -1.250   0.2741   0.01570   0.00947  -0.0824   0.8582   1.0000
  -1.000   0.2940   0.01575   0.00933  -0.0808   0.8471   1.0000
  -0.750   0.3128   0.01585   0.00928  -0.0791   0.8352   1.0000
  -0.500   0.3308   0.01603   0.00932  -0.0772   0.8224   1.0000
  -0.250   0.3507   0.01618   0.00933  -0.0755   0.8107   1.0000
   0.000   0.3740   0.01619   0.00917  -0.0740   0.8012   1.0000
   0.250   0.3939   0.01635   0.00924  -0.0723   0.7884   1.0000
   0.500   0.4147   0.01652   0.00930  -0.0707   0.7761   1.0000
   0.750   0.4372   0.01660   0.00927  -0.0692   0.7649   1.0000
   1.000   0.4613   0.01658   0.00912  -0.0677   0.7546   1.0000
   1.250   0.4833   0.01672   0.00920  -0.0664   0.7414   1.0000
   1.500   0.5062   0.01683   0.00923  -0.0650   0.7289   1.0000
   1.750   0.5304   0.01686   0.00917  -0.0638   0.7172   1.0000
   2.000   0.5561   0.01678   0.00899  -0.0625   0.7066   1.0000
   2.250   0.5796   0.01687   0.00903  -0.0613   0.6927   1.0000
   2.500   0.6037   0.01694   0.00905  -0.0602   0.6791   1.0000
   2.750   0.6283   0.01698   0.00904  -0.0591   0.6655   1.0000
   3.000   0.6534   0.01701   0.00902  -0.0581   0.6518   1.0000
   3.250   0.6787   0.01702   0.00897  -0.0571   0.6380   1.0000
   3.500   0.7041   0.01704   0.00893  -0.0561   0.6238   1.0000
   3.750   0.7295   0.01708   0.00890  -0.0551   0.6088   1.0000
   4.000   0.7546   0.01714   0.00893  -0.0542   0.5931   1.0000
   4.250   0.7797   0.01723   0.00898  -0.0533   0.5767   1.0000
   4.500   0.8045   0.01734   0.00905  -0.0524   0.5596   1.0000
   4.750   0.8294   0.01748   0.00916  -0.0515   0.5422   1.0000
   5.000   0.8542   0.01765   0.00926  -0.0506   0.5244   1.0000
   5.250   0.8791   0.01786   0.00938  -0.0497   0.5066   1.0000
   5.500   0.9039   0.01811   0.00953  -0.0489   0.4886   1.0000
   5.750   0.9270   0.01847   0.00992  -0.0480   0.4688   1.0000
   6.000   0.9505   0.01884   0.01025  -0.0471   0.4495   1.0000
   6.250   0.9742   0.01925   0.01059  -0.0463   0.4309   1.0000
   6.500   0.9978   0.01970   0.01096  -0.0455   0.4129   1.0000
   6.750   1.0205   0.02021   0.01144  -0.0446   0.3946   1.0000
   7.000   1.0427   0.02078   0.01201  -0.0437   0.3764   1.0000
   7.250   1.0648   0.02136   0.01260  -0.0428   0.3591   1.0000
   7.500   1.0869   0.02200   0.01321  -0.0420   0.3426   1.0000
   7.750   1.1087   0.02266   0.01386  -0.0411   0.3267   1.0000
   8.000   1.1302   0.02338   0.01458  -0.0402   0.3115   1.0000
   8.250   1.1515   0.02414   0.01535  -0.0394   0.2970   1.0000
   8.500   1.1724   0.02493   0.01615  -0.0385   0.2830   1.0000
   8.750   1.1932   0.02577   0.01700  -0.0376   0.2699   1.0000
   9.000   1.2142   0.02663   0.01785  -0.0368   0.2573   1.0000
   9.250   1.2357   0.02752   0.01868  -0.0360   0.2452   1.0000
   9.500   1.2530   0.02842   0.01975  -0.0348   0.2331   1.0000
   9.750   1.2706   0.02946   0.02092  -0.0336   0.2217   1.0000
  10.000   1.2893   0.03052   0.02202  -0.0326   0.2111   1.0000
  10.250   1.3106   0.03155   0.02293  -0.0320   0.2006   1.0000
  10.500   1.3230   0.03264   0.02429  -0.0302   0.1906   1.0000
  10.750   1.3380   0.03390   0.02566  -0.0289   0.1811   1.0000
  11.000   1.3585   0.03505   0.02670  -0.0283   0.1717   1.0000
  11.250   1.3655   0.03632   0.02829  -0.0260   0.1631   1.0000
  11.500   1.3795   0.03775   0.02977  -0.0247   0.1549   1.0000
  11.750   1.3914   0.03894   0.03101  -0.0232   0.1469   1.0000
  12.000   1.3972   0.04067   0.03297  -0.0212   0.1399   1.0000
  12.250   1.4125   0.04190   0.03413  -0.0201   0.1323   1.0000
  12.500   1.4084   0.04382   0.03635  -0.0171   0.1270   1.0000
  12.750   1.4110   0.04530   0.03793  -0.0149   0.1213   1.0000
  13.000   1.4168   0.04734   0.04005  -0.0133   0.1157   1.0000
  13.250   1.4066   0.04962   0.04262  -0.0108   0.1118   1.0000
  13.500   1.4271   0.05117   0.04397  -0.0105   0.1050   1.0000
  13.750   1.4081   0.05417   0.04736  -0.0083   0.1028   1.0000
  14.000   1.3935   0.05739   0.05088  -0.0069   0.1000   1.0000
  14.250   1.3899   0.05994   0.05354  -0.0062   0.0963   1.0000
  14.500   1.3961   0.06260   0.05622  -0.0058   0.0921   1.0000
  14.750   1.3718   0.06729   0.06125  -0.0058   0.0910   1.0000
  15.000   1.3459   0.07274   0.06699  -0.0067   0.0900   1.0000
  15.250   1.3164   0.07918   0.07371  -0.0086   0.0895   1.0000
  15.500   1.2803   0.08721   0.08201  -0.0120   0.0898   1.0000
  15.750   1.2367   0.09737   0.09240  -0.0173   0.0910   1.0000
  16.000   1.1892   0.10974   0.10494  -0.0243   0.0924   1.0000
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