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MH 42 8.94% (mh42-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MH 42 8.94% (mh42-il)
Reynolds number: 50,000
Max Cl/Cd: 32.75 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh42-il-50000.txt
Download as CSV file: xf-mh42-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 42  8.94%                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4812   0.10736   0.10086   0.0036   1.0000   0.2274
  -8.500  -0.4926   0.10570   0.09931   0.0013   1.0000   0.2355
  -8.250  -0.4882   0.10217   0.09585   0.0012   1.0000   0.2492
  -8.000  -0.4802   0.09839   0.09212   0.0015   1.0000   0.2625
  -7.750  -0.4689   0.09430   0.08807   0.0019   1.0000   0.2745
  -7.500  -0.4622   0.09053   0.08436   0.0020   1.0000   0.2856
  -7.250  -0.4592   0.08722   0.08114   0.0018   1.0000   0.2971
  -7.000  -0.4579   0.08397   0.07798   0.0019   1.0000   0.3099
  -6.750  -0.4571   0.08078   0.07488   0.0021   1.0000   0.3233
  -6.500  -0.4560   0.07756   0.07176   0.0024   1.0000   0.3370
  -6.250  -0.4525   0.07412   0.06840   0.0025   1.0000   0.3515
  -6.000  -0.4772   0.05285   0.04574  -0.0359   1.0000   0.1129
  -5.750  -0.4614   0.04855   0.04145  -0.0353   1.0000   0.1095
  -5.500  -0.4492   0.04331   0.03519  -0.0355   1.0000   0.0997
  -5.250  -0.4323   0.03944   0.03112  -0.0346   1.0000   0.0982
  -5.000  -0.4150   0.03589   0.02713  -0.0332   1.0000   0.0975
  -4.750  -0.3964   0.03290   0.02352  -0.0316   1.0000   0.0993
  -4.500  -0.3786   0.03064   0.02120  -0.0302   1.0000   0.1103
  -4.250  -0.3586   0.02814   0.01847  -0.0285   1.0000   0.1197
  -4.000  -0.3387   0.02619   0.01630  -0.0268   1.0000   0.1372
  -3.750  -0.3184   0.02426   0.01424  -0.0250   1.0000   0.1653
  -3.500  -0.2989   0.02237   0.01260  -0.0231   1.0000   0.2205
  -3.250  -0.2813   0.02034   0.01126  -0.0211   1.0000   0.3340
  -3.000  -0.2692   0.01872   0.01058  -0.0178   1.0000   0.4848
  -2.750  -0.0932   0.01702   0.00942  -0.0341   1.0000   1.0000
  -2.500  -0.1144   0.01672   0.00907  -0.0288   1.0000   1.0000
  -2.250  -0.1237   0.01668   0.00880  -0.0245   1.0000   1.0000
  -2.000  -0.1229   0.01676   0.00860  -0.0214   1.0000   1.0000
  -1.750  -0.1160   0.01691   0.00846  -0.0191   1.0000   1.0000
  -1.500  -0.1055   0.01712   0.00839  -0.0174   1.0000   1.0000
  -1.250  -0.0929   0.01738   0.00839  -0.0160   1.0000   1.0000
  -1.000  -0.0789   0.01768   0.00845  -0.0149   1.0000   1.0000
  -0.750  -0.0640   0.01802   0.00857  -0.0139   1.0000   1.0000
  -0.500  -0.0485   0.01841   0.00873  -0.0131   1.0000   1.0000
  -0.250  -0.0327   0.01884   0.00898  -0.0125   1.0000   1.0000
   0.000  -0.0165   0.01931   0.00929  -0.0120   1.0000   1.0000
   0.250   0.0006   0.01984   0.00966  -0.0117   0.9997   1.0000
   0.500   0.0535   0.02088   0.01055  -0.0181   0.9843   1.0000
   0.750   0.1058   0.02190   0.01142  -0.0242   0.9691   1.0000
   1.000   0.1532   0.02278   0.01222  -0.0292   0.9531   1.0000
   1.250   0.1973   0.02359   0.01299  -0.0333   0.9363   1.0000
   1.500   0.2419   0.02438   0.01376  -0.0374   0.9195   1.0000
   1.750   0.2887   0.02512   0.01452  -0.0417   0.9028   1.0000
   2.000   0.3363   0.02579   0.01526  -0.0458   0.8861   1.0000
   2.250   0.3709   0.02644   0.01596  -0.0476   0.8677   1.0000
   2.500   0.4149   0.02698   0.01660  -0.0506   0.8498   1.0000
   2.750   0.4614   0.02738   0.01711  -0.0535   0.8326   1.0000
   3.000   0.4891   0.02799   0.01787  -0.0535   0.8130   1.0000
   3.250   0.5250   0.02835   0.01836  -0.0541   0.7942   1.0000
   3.500   0.5601   0.02860   0.01875  -0.0543   0.7755   1.0000
   3.750   0.5858   0.02905   0.01934  -0.0532   0.7545   1.0000
   4.000   0.6217   0.02894   0.01944  -0.0525   0.7358   1.0000
   4.250   0.6428   0.02942   0.02005  -0.0506   0.7129   1.0000
   4.500   0.6705   0.02942   0.02021  -0.0487   0.6914   1.0000
   4.750   0.6982   0.02925   0.02019  -0.0464   0.6689   1.0000
   5.000   0.7218   0.02927   0.02044  -0.0439   0.6439   1.0000
   5.250   0.7466   0.02906   0.02037  -0.0412   0.6179   1.0000
   5.500   0.7718   0.02868   0.02013  -0.0382   0.5903   1.0000
   5.750   0.7975   0.02812   0.01966  -0.0351   0.5603   1.0000
   6.000   0.8211   0.02773   0.01935  -0.0320   0.5260   1.0000
   6.250   0.8455   0.02718   0.01877  -0.0288   0.4880   1.0000
   6.500   0.8665   0.02708   0.01874  -0.0258   0.4435   1.0000
   6.750   0.8874   0.02710   0.01855  -0.0227   0.3945   1.0000
   7.000   0.9049   0.02779   0.01902  -0.0200   0.3413   1.0000
   7.250   0.9212   0.02902   0.02002  -0.0176   0.2895   1.0000
   7.500   0.9373   0.03059   0.02124  -0.0154   0.2426   1.0000
   7.750   0.9549   0.03270   0.02307  -0.0136   0.2033   1.0000
   8.000   0.9703   0.03503   0.02549  -0.0118   0.1714   1.0000
   8.250   0.9893   0.03781   0.02820  -0.0104   0.1479   1.0000
   8.500   1.0046   0.04058   0.03123  -0.0088   0.1294   1.0000
   8.750   1.0214   0.04445   0.03541  -0.0074   0.1197   1.0000
   9.000   1.0365   0.04792   0.03900  -0.0062   0.1093   1.0000
   9.250   1.0403   0.05140   0.04306  -0.0043   0.1018   1.0000
   9.500   1.0529   0.05596   0.04781  -0.0034   0.0970   1.0000
   9.750   1.0487   0.06066   0.05307  -0.0017   0.0963   1.0000
  10.000   1.0403   0.06553   0.05836  -0.0004   0.0962   1.0000
  10.250   1.0282   0.07040   0.06354   0.0006   0.0963   1.0000
  10.500   1.0135   0.07525   0.06860   0.0012   0.0967   1.0000
  10.750   0.9975   0.08000   0.07348   0.0017   0.0972   1.0000
  11.250   0.8484   0.10814   0.10162  -0.0221   0.1330   1.0000
  11.500   0.8443   0.11509   0.10853  -0.0247   0.1355   1.0000
  11.750   0.8450   0.12143   0.11487  -0.0263   0.1366   1.0000
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