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MH 91 14.98% (mh91-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 91 14.98% (mh91-il)
Reynolds number: 100,000
Max Cl/Cd: 34.26 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh91-il-100000.txt
Download as CSV file: xf-mh91-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 91  14.98%                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5303   0.07808   0.07385  -0.0184   1.0000   0.0780
 -10.250  -0.5912   0.06672   0.06232  -0.0254   1.0000   0.0759
 -10.000  -0.6452   0.05971   0.05507  -0.0274   1.0000   0.0747
  -9.750  -0.6782   0.05423   0.04932  -0.0261   1.0000   0.0693
  -9.500  -0.7578   0.05935   0.05389  -0.0198   1.0000   0.0691
  -9.250  -0.7844   0.05350   0.04732  -0.0161   1.0000   0.0612
  -9.000  -0.7790   0.04947   0.04307  -0.0146   1.0000   0.0589
  -8.750  -0.7929   0.04559   0.03808  -0.0097   1.0000   0.0542
  -8.500  -0.7751   0.04208   0.03445  -0.0089   1.0000   0.0535
  -8.250  -0.7584   0.03918   0.03131  -0.0078   1.0000   0.0530
  -8.000  -0.7409   0.03653   0.02836  -0.0065   1.0000   0.0528
  -7.750  -0.7210   0.03422   0.02579  -0.0054   1.0000   0.0528
  -7.500  -0.7003   0.03218   0.02350  -0.0043   1.0000   0.0533
  -7.250  -0.6823   0.03064   0.02173  -0.0027   1.0000   0.0541
  -7.000  -0.6679   0.02902   0.02022  -0.0010   1.0000   0.0563
  -6.750  -0.6629   0.02822   0.01946   0.0022   1.0000   0.0581
  -6.500  -0.6597   0.02757   0.01875   0.0056   1.0000   0.0604
  -6.250  -0.6226   0.02586   0.01705   0.0035   0.9937   0.0643
  -6.000  -0.5718   0.02407   0.01534  -0.0010   0.9832   0.0730
  -5.750  -0.5263   0.02222   0.01375  -0.0050   0.9715   0.0893
  -5.500  -0.4900   0.01993   0.01195  -0.0075   0.9580   0.1402
  -5.250  -0.4817   0.01723   0.01098  -0.0055   0.9388   0.3943
  -5.000  -0.4572   0.01679   0.01094  -0.0045   0.9215   0.4973
  -4.750  -0.4329   0.01670   0.01103  -0.0028   0.9046   0.5631
  -4.500  -0.4100   0.01680   0.01124  -0.0006   0.8879   0.6146
  -4.250  -0.3872   0.01708   0.01158   0.0020   0.8719   0.6576
  -4.000  -0.3645   0.01750   0.01201   0.0049   0.8562   0.6944
  -3.750  -0.3389   0.01806   0.01252   0.0076   0.8413   0.7234
  -3.500  -0.3155   0.01850   0.01284   0.0104   0.8270   0.7483
  -3.250  -0.2902   0.01892   0.01315   0.0126   0.8115   0.7688
  -3.000  -0.2620   0.01938   0.01349   0.0143   0.7960   0.7865
  -2.750  -0.2337   0.01981   0.01378   0.0159   0.7808   0.8035
  -2.500  -0.1949   0.02036   0.01418   0.0159   0.7658   0.8152
  -2.250  -0.1600   0.02072   0.01437   0.0163   0.7513   0.8282
  -2.000  -0.1284   0.02092   0.01438   0.0169   0.7375   0.8422
  -1.750  -0.0984   0.02108   0.01439   0.0175   0.7223   0.8570
  -1.500  -0.0465   0.02133   0.01445   0.0143   0.7055   0.8644
  -1.250  -0.0115   0.02137   0.01435   0.0136   0.6899   0.8774
  -1.000   0.0280   0.02142   0.01425   0.0120   0.6740   0.8891
  -0.750   0.0723   0.02141   0.01406   0.0096   0.6579   0.8989
  -0.500   0.1063   0.02136   0.01386   0.0087   0.6433   0.9117
  -0.250   0.1474   0.02129   0.01361   0.0066   0.6282   0.9228
   0.000   0.1896   0.02116   0.01331   0.0041   0.6127   0.9333
   0.250   0.2274   0.02103   0.01308   0.0021   0.5967   0.9451
   0.500   0.2653   0.02093   0.01288   0.0000   0.5811   0.9571
   0.750   0.3114   0.02065   0.01248  -0.0037   0.5650   0.9665
   1.000   0.3538   0.02039   0.01210  -0.0068   0.5498   0.9764
   1.250   0.3958   0.02012   0.01171  -0.0099   0.5353   0.9860
   1.500   0.4385   0.01981   0.01125  -0.0132   0.5216   0.9949
   1.750   0.4732   0.01959   0.01095  -0.0152   0.5081   1.0000
   2.000   0.4936   0.01967   0.01102  -0.0145   0.4961   1.0000
   2.250   0.5137   0.01973   0.01095  -0.0136   0.4866   1.0000
   2.500   0.5344   0.01983   0.01104  -0.0130   0.4753   1.0000
   2.750   0.5551   0.01999   0.01116  -0.0122   0.4653   1.0000
   3.000   0.5759   0.02010   0.01118  -0.0113   0.4559   1.0000
   3.250   0.5967   0.02033   0.01145  -0.0107   0.4456   1.0000
   3.500   0.6178   0.02047   0.01146  -0.0097   0.4375   1.0000
   3.750   0.6385   0.02078   0.01185  -0.0091   0.4273   1.0000
   4.000   0.6598   0.02094   0.01187  -0.0081   0.4198   1.0000
   4.250   0.6801   0.02132   0.01238  -0.0074   0.4100   1.0000
   4.500   0.7015   0.02154   0.01246  -0.0065   0.4031   1.0000
   4.750   0.7211   0.02200   0.01306  -0.0056   0.3940   1.0000
   5.000   0.7420   0.02226   0.01324  -0.0046   0.3869   1.0000
   5.250   0.7610   0.02279   0.01387  -0.0036   0.3788   1.0000
   5.500   0.7810   0.02314   0.01421  -0.0026   0.3716   1.0000
   5.750   0.8005   0.02366   0.01474  -0.0015   0.3649   1.0000
   6.000   0.8186   0.02418   0.01535  -0.0003   0.3571   1.0000
   6.250   0.8400   0.02452   0.01554   0.0008   0.3515   1.0000
   6.500   0.8547   0.02534   0.01661   0.0022   0.3439   1.0000
   6.750   0.8738   0.02576   0.01701   0.0035   0.3377   1.0000
   7.000   0.8914   0.02642   0.01769   0.0049   0.3317   1.0000
   7.250   0.9057   0.02717   0.01861   0.0065   0.3248   1.0000
   7.500   0.9262   0.02754   0.01889   0.0078   0.3194   1.0000
   7.750   0.9382   0.02853   0.02006   0.0096   0.3132   1.0000
   8.000   0.9528   0.02921   0.02082   0.0114   0.3069   1.0000
   8.250   0.9758   0.02953   0.02100   0.0124   0.3018   1.0000
   8.500   0.9810   0.03081   0.02258   0.0149   0.2955   1.0000
   8.750   0.9968   0.03139   0.02320   0.0166   0.2895   1.0000
   9.000   1.0208   0.03180   0.02346   0.0174   0.2845   1.0000
   9.250   1.0212   0.03328   0.02529   0.0203   0.2782   1.0000
   9.500   1.0402   0.03371   0.02571   0.0216   0.2724   1.0000
   9.750   1.0591   0.03446   0.02643   0.0227   0.2672   1.0000
  10.000   1.0596   0.03604   0.02831   0.0253   0.2611   1.0000
  10.250   1.0839   0.03626   0.02846   0.0260   0.2555   1.0000
  10.500   1.0944   0.03757   0.02988   0.0275   0.2503   1.0000
  10.750   1.0943   0.03926   0.03181   0.0298   0.2445   1.0000
  11.000   1.1268   0.03906   0.03148   0.0298   0.2388   1.0000
  11.250   1.1215   0.04124   0.03390   0.0322   0.2339   1.0000
  11.500   1.1125   0.04344   0.03633   0.0347   0.2289   1.0000
  11.750   1.1647   0.04223   0.03486   0.0335   0.2226   1.0000
  12.000   1.1342   0.04562   0.03860   0.0372   0.2190   1.0000
  12.250   1.0620   0.05173   0.04499   0.0410   0.2174   1.0000
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