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MH 43 8.5% (mh43-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 43 8.5% (mh43-il)
Reynolds number: 100,000
Max Cl/Cd: 49.08 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh43-il-100000-n5.txt
Download as CSV file: xf-mh43-il-100000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5235   0.09100   0.08631  -0.0048   1.0000   0.0159
  -8.500  -0.5245   0.08625   0.08162  -0.0076   1.0000   0.0154
  -8.250  -0.5270   0.08125   0.07670  -0.0108   1.0000   0.0149
  -8.000  -0.5315   0.07599   0.07152  -0.0147   1.0000   0.0146
  -7.750  -0.5372   0.06969   0.06526  -0.0206   1.0000   0.0143
  -7.500  -0.5406   0.06140   0.05689  -0.0269   1.0000   0.0136
  -7.250  -0.5417   0.05361   0.04885  -0.0308   1.0000   0.0130
  -7.000  -0.5367   0.04786   0.04274  -0.0327   1.0000   0.0126
  -6.750  -0.5266   0.04338   0.03786  -0.0335   1.0000   0.0123
  -6.500  -0.5139   0.03932   0.03337  -0.0337   1.0000   0.0122
  -6.250  -0.4985   0.03573   0.02934  -0.0335   1.0000   0.0122
  -6.000  -0.4816   0.03225   0.02537  -0.0331   1.0000   0.0122
  -5.750  -0.4632   0.02906   0.02172  -0.0324   1.0000   0.0124
  -5.500  -0.4432   0.02639   0.01866  -0.0316   1.0000   0.0127
  -5.250  -0.4229   0.02430   0.01630  -0.0307   1.0000   0.0135
  -5.000  -0.4025   0.02300   0.01484  -0.0299   1.0000   0.0155
  -4.750  -0.3829   0.02179   0.01342  -0.0286   1.0000   0.0182
  -4.500  -0.3618   0.02050   0.01192  -0.0274   0.9976   0.0201
  -4.250  -0.3272   0.01858   0.00976  -0.0290   0.9845   0.0232
  -4.000  -0.2921   0.01729   0.00836  -0.0307   0.9719   0.0343
  -3.750  -0.2582   0.01586   0.00707  -0.0321   0.9594   0.0722
  -3.500  -0.2253   0.01478   0.00637  -0.0336   0.9471   0.1555
  -3.250  -0.1932   0.01408   0.00594  -0.0348   0.9347   0.2427
  -3.000  -0.1633   0.01341   0.00561  -0.0355   0.9222   0.3410
  -2.750  -0.1353   0.01283   0.00535  -0.0355   0.9097   0.4468
  -2.500  -0.1089   0.01233   0.00513  -0.0349   0.8976   0.5579
  -2.250  -0.0838   0.01197   0.00503  -0.0336   0.8859   0.6619
  -2.000  -0.0587   0.01174   0.00495  -0.0320   0.8743   0.7531
  -1.750  -0.0300   0.01161   0.00487  -0.0312   0.8630   0.8307
  -1.500   0.0078   0.01154   0.00470  -0.0323   0.8528   0.8944
  -1.250   0.0515   0.01150   0.00449  -0.0349   0.8431   0.9426
  -1.000   0.0983   0.01145   0.00426  -0.0385   0.8334   0.9790
  -0.750   0.1381   0.01142   0.00407  -0.0411   0.8220   1.0000
  -0.500   0.1607   0.01148   0.00397  -0.0401   0.8096   1.0000
  -0.250   0.1837   0.01155   0.00391  -0.0392   0.7976   1.0000
   0.000   0.2073   0.01163   0.00388  -0.0383   0.7860   1.0000
   0.250   0.2309   0.01172   0.00386  -0.0374   0.7746   1.0000
   0.500   0.2547   0.01181   0.00386  -0.0365   0.7634   1.0000
   0.750   0.2787   0.01191   0.00387  -0.0356   0.7520   1.0000
   1.000   0.3031   0.01201   0.00391  -0.0349   0.7399   1.0000
   1.250   0.3277   0.01212   0.00396  -0.0342   0.7278   1.0000
   1.500   0.3525   0.01223   0.00403  -0.0334   0.7154   1.0000
   1.750   0.3774   0.01234   0.00412  -0.0327   0.7028   1.0000
   2.000   0.4024   0.01245   0.00420  -0.0320   0.6899   1.0000
   2.250   0.4276   0.01257   0.00430  -0.0314   0.6767   1.0000
   2.500   0.4529   0.01269   0.00441  -0.0307   0.6630   1.0000
   2.750   0.4782   0.01282   0.00458  -0.0301   0.6487   1.0000
   3.000   0.5036   0.01295   0.00472  -0.0294   0.6337   1.0000
   3.250   0.5290   0.01308   0.00486  -0.0287   0.6178   1.0000
   3.500   0.5544   0.01322   0.00503  -0.0281   0.6004   1.0000
   3.750   0.5798   0.01337   0.00522  -0.0275   0.5810   1.0000
   4.000   0.6050   0.01353   0.00544  -0.0268   0.5607   1.0000
   4.250   0.6301   0.01371   0.00566  -0.0261   0.5374   1.0000
   4.500   0.6551   0.01392   0.00589  -0.0254   0.5114   1.0000
   4.750   0.6797   0.01416   0.00614  -0.0247   0.4824   1.0000
   5.000   0.7041   0.01446   0.00644  -0.0239   0.4487   1.0000
   5.250   0.7279   0.01483   0.00684  -0.0232   0.4098   1.0000
   5.500   0.7510   0.01531   0.00724  -0.0224   0.3657   1.0000
   5.750   0.7734   0.01593   0.00772  -0.0216   0.3178   1.0000
   6.000   0.7950   0.01669   0.00832  -0.0209   0.2668   1.0000
   6.250   0.8162   0.01755   0.00903  -0.0201   0.2166   1.0000
   6.500   0.8366   0.01854   0.00984  -0.0194   0.1695   1.0000
   6.750   0.8566   0.01962   0.01076  -0.0187   0.1281   1.0000
   7.000   0.8758   0.02082   0.01181  -0.0179   0.0936   1.0000
   7.250   0.8947   0.02207   0.01302  -0.0170   0.0703   1.0000
   7.500   0.9124   0.02347   0.01446  -0.0159   0.0530   1.0000
   7.750   0.9290   0.02497   0.01600  -0.0148   0.0419   1.0000
   8.000   0.9456   0.02652   0.01776  -0.0134   0.0352   1.0000
   8.250   0.9607   0.02822   0.01955  -0.0121   0.0287   1.0000
   8.500   0.9762   0.02992   0.02143  -0.0107   0.0241   1.0000
   8.750   0.9872   0.03241   0.02397  -0.0092   0.0208   1.0000
   9.000   1.0037   0.03401   0.02590  -0.0080   0.0171   1.0000
   9.250   1.0164   0.03635   0.02848  -0.0066   0.0152   1.0000
   9.500   1.0269   0.03882   0.03118  -0.0052   0.0142   1.0000
   9.750   1.0327   0.04173   0.03430  -0.0038   0.0131   1.0000
  10.000   1.0315   0.04568   0.03855  -0.0021   0.0123   1.0000
  10.250   1.0306   0.04811   0.04133  -0.0002   0.0118   1.0000
  10.500   1.0246   0.05119   0.04473   0.0013   0.0115   1.0000
  10.750   1.0164   0.05452   0.04833   0.0020   0.0112   1.0000
  11.000   1.0058   0.05815   0.05225   0.0017   0.0102   1.0000
  11.250   0.9921   0.06279   0.05714   0.0005   0.0105   1.0000
  11.500   0.9765   0.06808   0.06264  -0.0017   0.0108   1.0000
  11.750   0.9601   0.07399   0.06875  -0.0049   0.0108   1.0000
  12.000   0.9428   0.08070   0.07562  -0.0091   0.0111   1.0000
  12.250   0.9240   0.08848   0.08356  -0.0143   0.0113   1.0000
  12.500   0.9061   0.09686   0.09203  -0.0198   0.0117   1.0000
  12.750   0.8886   0.10589   0.10112  -0.0255   0.0121   1.0000
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