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MH 43 8.5% (mh43-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 43 8.5% (mh43-il)
Reynolds number: 100,000
Max Cl/Cd: 50.08 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh43-il-100000.txt
Download as CSV file: xf-mh43-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 43  8.5%                                     
  
 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  -0.5102   0.09706   0.09252  -0.0023   1.0000   0.0900
  -8.250  -0.5150   0.09352   0.08906  -0.0061   1.0000   0.0938
  -8.000  -0.5406   0.08973   0.08540  -0.0170   1.0000   0.0956
  -7.750  -0.5192   0.08521   0.08092  -0.0112   1.0000   0.0984
  -7.500  -0.5121   0.08180   0.07754  -0.0114   1.0000   0.1016
  -7.250  -0.4514   0.06817   0.06428  -0.0164   1.0000   0.1119
  -7.000  -0.5177   0.07190   0.06765  -0.0234   1.0000   0.1109
  -6.750  -0.5044   0.06857   0.06436  -0.0224   1.0000   0.1143
  -6.250  -0.4891   0.05990   0.05558  -0.0277   1.0000   0.1270
  -6.000  -0.4800   0.04422   0.03864  -0.0357   1.0000   0.0584
  -5.750  -0.4602   0.03853   0.03226  -0.0349   1.0000   0.0432
  -5.500  -0.4439   0.03421   0.02767  -0.0345   1.0000   0.0410
  -5.250  -0.4256   0.03060   0.02362  -0.0335   1.0000   0.0391
  -5.000  -0.4064   0.02784   0.02039  -0.0322   1.0000   0.0395
  -4.750  -0.3877   0.02583   0.01794  -0.0305   1.0000   0.0420
  -4.500  -0.3696   0.02437   0.01598  -0.0285   1.0000   0.0438
  -4.250  -0.3528   0.02177   0.01321  -0.0266   1.0000   0.0456
  -4.000  -0.3362   0.02011   0.01151  -0.0247   1.0000   0.0494
  -3.750  -0.3189   0.01875   0.01002  -0.0226   1.0000   0.0579
  -3.500  -0.3026   0.01744   0.00882  -0.0208   1.0000   0.0816
  -3.250  -0.2863   0.01591   0.00776  -0.0192   1.0000   0.1517
  -3.000  -0.2702   0.01451   0.00712  -0.0179   1.0000   0.2863
  -2.750  -0.2545   0.01372   0.00696  -0.0164   1.0000   0.4207
  -2.500  -0.2290   0.01279   0.00707  -0.0157   0.9943   0.6570
  -2.250  -0.1839   0.01244   0.00720  -0.0164   0.9893   0.9102
  -2.000  -0.1006   0.01246   0.00676  -0.0273   0.9884   1.0000
  -1.750  -0.0498   0.01260   0.00656  -0.0327   0.9781   1.0000
  -1.500   0.0027   0.01272   0.00639  -0.0382   0.9688   1.0000
  -1.250   0.0517   0.01279   0.00621  -0.0429   0.9582   1.0000
  -1.000   0.1003   0.01283   0.00608  -0.0474   0.9479   1.0000
  -0.750   0.1464   0.01286   0.00596  -0.0513   0.9372   1.0000
  -0.500   0.1884   0.01289   0.00586  -0.0541   0.9258   1.0000
  -0.250   0.2236   0.01297   0.00584  -0.0556   0.9129   1.0000
   0.000   0.2527   0.01310   0.00589  -0.0557   0.8990   1.0000
   0.250   0.2780   0.01327   0.00599  -0.0551   0.8848   1.0000
   0.500   0.3012   0.01346   0.00612  -0.0539   0.8706   1.0000
   0.750   0.3234   0.01366   0.00626  -0.0525   0.8565   1.0000
   1.000   0.3450   0.01386   0.00642  -0.0509   0.8426   1.0000
   1.250   0.3666   0.01406   0.00658  -0.0493   0.8287   1.0000
   1.500   0.3883   0.01425   0.00676  -0.0477   0.8148   1.0000
   1.750   0.4103   0.01443   0.00691  -0.0462   0.8009   1.0000
   2.000   0.4326   0.01460   0.00707  -0.0446   0.7869   1.0000
   2.250   0.4551   0.01476   0.00722  -0.0431   0.7728   1.0000
   2.500   0.4780   0.01490   0.00736  -0.0417   0.7584   1.0000
   2.750   0.5011   0.01502   0.00754  -0.0402   0.7436   1.0000
   3.000   0.5245   0.01512   0.00765  -0.0387   0.7285   1.0000
   3.250   0.5480   0.01518   0.00774  -0.0372   0.7131   1.0000
   3.500   0.5719   0.01522   0.00778  -0.0357   0.6975   1.0000
   3.750   0.5956   0.01532   0.00799  -0.0345   0.6782   1.0000
   4.000   0.6197   0.01532   0.00802  -0.0330   0.6596   1.0000
   4.250   0.6438   0.01534   0.00809  -0.0316   0.6391   1.0000
   4.500   0.6681   0.01531   0.00808  -0.0302   0.6174   1.0000
   4.750   0.6922   0.01533   0.00815  -0.0288   0.5921   1.0000
   5.000   0.7162   0.01533   0.00819  -0.0274   0.5645   1.0000
   5.250   0.7400   0.01537   0.00833  -0.0260   0.5324   1.0000
   5.500   0.7632   0.01547   0.00843  -0.0246   0.4950   1.0000
   5.750   0.7858   0.01569   0.00865  -0.0233   0.4487   1.0000
   6.000   0.8070   0.01612   0.00895  -0.0219   0.3925   1.0000
   6.250   0.8265   0.01688   0.00946  -0.0205   0.3253   1.0000
   6.500   0.8437   0.01808   0.01028  -0.0192   0.2528   1.0000
   6.750   0.8596   0.01969   0.01146  -0.0178   0.1861   1.0000
   7.000   0.8751   0.02146   0.01289  -0.0164   0.1341   1.0000
   7.250   0.8913   0.02352   0.01472  -0.0148   0.1020   1.0000
   7.500   0.9081   0.02554   0.01651  -0.0136   0.0795   1.0000
   7.750   0.9291   0.02808   0.01913  -0.0123   0.0668   1.0000
   8.000   0.9491   0.03017   0.02134  -0.0112   0.0554   1.0000
   8.250   0.9705   0.03293   0.02449  -0.0098   0.0482   1.0000
   8.500   0.9870   0.03614   0.02784  -0.0088   0.0415   1.0000
   8.750   1.0026   0.03906   0.03130  -0.0072   0.0379   1.0000
   9.000   1.0142   0.04290   0.03564  -0.0055   0.0364   1.0000
   9.250   1.0203   0.04709   0.04034  -0.0037   0.0359   1.0000
   9.500   1.0202   0.05148   0.04522  -0.0020   0.0362   1.0000
   9.750   1.0156   0.05559   0.04972  -0.0004   0.0358   1.0000
  10.000   1.0045   0.05975   0.05423   0.0011   0.0359   1.0000
  10.250   0.9854   0.06377   0.05851   0.0027   0.0366   1.0000
  10.500   0.9636   0.06847   0.06343   0.0027   0.0381   1.0000
  10.750   0.9442   0.07335   0.06846   0.0011   0.0390   1.0000
  11.000   0.9203   0.07914   0.07440  -0.0024   0.0384   1.0000
  11.250   0.9026   0.08567   0.08101  -0.0062   0.0401   1.0000
  11.500   0.8865   0.09259   0.08798  -0.0105   0.0411   1.0000
  11.750   0.8719   0.10008   0.09549  -0.0150   0.0419   1.0000
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