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MH 83 13.29% (mh83-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 83 13.29% (mh83-il)
Reynolds number: 50,000
Max Cl/Cd: 26.68 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh83-il-50000-n5.txt
Download as CSV file: xf-mh83-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2398   0.11669   0.11103  -0.0138   1.0000   0.1086
  -9.000  -0.2420   0.11486   0.10934  -0.0179   1.0000   0.1097
  -8.750  -0.2402   0.11242   0.10704  -0.0217   1.0000   0.1101
  -8.500  -0.2233   0.10794   0.10264  -0.0246   0.9475   0.1108
  -8.250  -0.1898   0.10260   0.09720  -0.0255   0.9087   0.1139
  -7.750  -0.1806   0.09288   0.08728  -0.0342   0.8545   0.0722
  -7.250  -0.1753   0.08571   0.08000  -0.0375   0.8142   0.0628
  -7.000  -0.1690   0.08302   0.07728  -0.0376   0.7966   0.0616
  -6.750  -0.1638   0.07999   0.07422  -0.0390   0.7806   0.0600
  -6.250  -0.1565   0.06978   0.06384  -0.0503   0.7558   0.0547
  -6.000  -0.1451   0.06623   0.06022  -0.0528   0.7418   0.0540
  -5.750  -0.1329   0.06204   0.05593  -0.0563   0.7292   0.0532
  -5.500  -0.1196   0.05733   0.05100  -0.0603   0.7185   0.0524
  -5.250  -0.1034   0.05250   0.04590  -0.0644   0.7068   0.0517
  -5.000  -0.0843   0.04778   0.04078  -0.0681   0.6957   0.0512
  -4.750  -0.0629   0.04366   0.03614  -0.0706   0.6856   0.0513
  -4.500  -0.0385   0.04025   0.03220  -0.0725   0.6734   0.0527
  -4.250  -0.0127   0.03711   0.02834  -0.0737   0.6628   0.0546
  -4.000   0.0126   0.03520   0.02611  -0.0738   0.6514   0.0566
  -3.750   0.0389   0.03353   0.02413  -0.0739   0.6396   0.0585
  -3.500   0.0657   0.03181   0.02197  -0.0736   0.6297   0.0606
  -3.250   0.0934   0.03032   0.02005  -0.0733   0.6181   0.0638
  -3.000   0.1197   0.02944   0.01908  -0.0729   0.6073   0.0689
  -2.750   0.1464   0.02842   0.01780  -0.0722   0.5975   0.0752
  -2.500   0.1737   0.02762   0.01682  -0.0718   0.5864   0.0844
  -2.250   0.2002   0.02684   0.01592  -0.0711   0.5779   0.0988
  -2.000   0.2280   0.02620   0.01528  -0.0711   0.5668   0.1261
  -1.750   0.2555   0.02553   0.01473  -0.0710   0.5579   0.1755
  -1.500   0.2828   0.02509   0.01446  -0.0709   0.5479   0.2438
  -1.250   0.3096   0.02469   0.01424  -0.0706   0.5392   0.3172
  -1.000   0.3355   0.02434   0.01411  -0.0701   0.5302   0.3962
  -0.750   0.3601   0.02400   0.01402  -0.0691   0.5222   0.4904
  -0.500   0.3816   0.02363   0.01404  -0.0673   0.5137   0.6120
  -0.250   0.4016   0.02297   0.01380  -0.0640   0.5073   0.8139
   0.000   0.4383   0.02315   0.01374  -0.0657   0.4975   1.0000
   0.500   0.4939   0.02395   0.01387  -0.0658   0.4823   1.0000
   0.750   0.5217   0.02425   0.01382  -0.0655   0.4761   1.0000
   1.000   0.5485   0.02482   0.01419  -0.0656   0.4686   1.0000
   1.250   0.5755   0.02527   0.01441  -0.0655   0.4618   1.0000
   1.500   0.6030   0.02559   0.01443  -0.0652   0.4567   1.0000
   1.750   0.6284   0.02636   0.01514  -0.0654   0.4488   1.0000
   2.000   0.6553   0.02679   0.01536  -0.0651   0.4433   1.0000
   2.250   0.6817   0.02734   0.01573  -0.0650   0.4381   1.0000
   2.500   0.7063   0.02817   0.01652  -0.0650   0.4313   1.0000
   2.750   0.7329   0.02863   0.01681  -0.0648   0.4263   1.0000
   3.000   0.7587   0.02922   0.01726  -0.0646   0.4215   1.0000
   3.250   0.7816   0.03028   0.01834  -0.0647   0.4151   1.0000
   3.500   0.8070   0.03089   0.01886  -0.0644   0.4105   1.0000
   3.750   0.8343   0.03127   0.01905  -0.0640   0.4071   1.0000
   4.000   0.8536   0.03275   0.02065  -0.0642   0.4005   1.0000
   4.250   0.8767   0.03365   0.02153  -0.0640   0.3956   1.0000
   4.500   0.9027   0.03415   0.02191  -0.0636   0.3920   1.0000
   4.750   0.9245   0.03525   0.02301  -0.0635   0.3878   1.0000
   5.000   0.9399   0.03709   0.02499  -0.0635   0.3820   1.0000
   5.250   0.9621   0.03802   0.02591  -0.0632   0.3779   1.0000
   5.500   0.9884   0.03847   0.02625  -0.0628   0.3748   1.0000
   5.750   0.9994   0.04069   0.02862  -0.0627   0.3696   1.0000
   6.000   1.0076   0.04312   0.03119  -0.0626   0.3642   1.0000
   6.250   1.0274   0.04426   0.03235  -0.0622   0.3607   1.0000
   6.500   1.0539   0.04466   0.03267  -0.0617   0.3582   1.0000
   6.750   1.0204   0.05127   0.03963  -0.0620   0.3498   1.0000
   7.000   1.0235   0.05398   0.04238  -0.0618   0.3452   1.0000
   7.250   1.0455   0.05473   0.04312  -0.0612   0.3427   1.0000
   7.500   1.0692   0.05539   0.04376  -0.0606   0.3405   1.0000
   8.000   0.9059   0.08309   0.07182  -0.0703   0.3163   1.0000
   8.250   0.9145   0.08567   0.07441  -0.0705   0.3127   1.0000
   8.500   0.9336   0.08681   0.07555  -0.0700   0.3103   1.0000
   9.500   0.9375   0.10188   0.09077  -0.0735   0.2939   1.0000
   9.750   0.9094   0.10973   0.09867  -0.0768   0.2869   1.0000
  10.000   0.9125   0.11329   0.10230  -0.0777   0.2830   1.0000
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