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MH 44 9.66% (mh44-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 44 9.66% (mh44-il)
Reynolds number: 100,000
Max Cl/Cd: 45.63 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh44-il-100000-n5.txt
Download as CSV file: xf-mh44-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 44  9.66%                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5490   0.09026   0.08551  -0.0085   1.0000   0.0185
  -9.250  -0.5521   0.08502   0.08033  -0.0114   1.0000   0.0183
  -9.000  -0.5577   0.07901   0.07438  -0.0153   1.0000   0.0180
  -8.750  -0.5650   0.07209   0.06751  -0.0207   1.0000   0.0176
  -8.500  -0.5801   0.06457   0.05995  -0.0272   1.0000   0.0173
  -8.250  -0.5931   0.05939   0.05464  -0.0294   1.0000   0.0170
  -8.000  -0.6016   0.05425   0.04929  -0.0306   1.0000   0.0168
  -7.750  -0.6047   0.04953   0.04426  -0.0310   1.0000   0.0165
  -7.500  -0.6031   0.04511   0.03947  -0.0306   1.0000   0.0163
  -7.250  -0.5970   0.04117   0.03511  -0.0297   1.0000   0.0161
  -7.000  -0.5875   0.03755   0.03104  -0.0285   1.0000   0.0160
  -6.750  -0.5749   0.03441   0.02745  -0.0270   1.0000   0.0160
  -6.500  -0.5600   0.03172   0.02434  -0.0255   1.0000   0.0160
  -6.250  -0.5437   0.02941   0.02167  -0.0239   1.0000   0.0162
  -6.000  -0.5272   0.02742   0.01937  -0.0221   1.0000   0.0166
  -5.750  -0.5110   0.02567   0.01738  -0.0200   1.0000   0.0170
  -5.500  -0.4954   0.02426   0.01573  -0.0179   1.0000   0.0177
  -5.250  -0.4798   0.02319   0.01445  -0.0157   1.0000   0.0192
  -5.000  -0.4665   0.02191   0.01311  -0.0134   1.0000   0.0212
  -4.750  -0.4356   0.02067   0.01178  -0.0144   0.9921   0.0238
  -4.500  -0.4017   0.01943   0.01035  -0.0157   0.9839   0.0269
  -4.250  -0.3688   0.01826   0.00907  -0.0170   0.9752   0.0351
  -4.000  -0.3349   0.01691   0.00774  -0.0184   0.9676   0.0614
  -3.750  -0.3057   0.01537   0.00704  -0.0195   0.9585   0.2003
  -3.500  -0.2746   0.01473   0.00673  -0.0205   0.9491   0.2947
  -3.250  -0.2431   0.01419   0.00650  -0.0213   0.9404   0.3839
  -3.000  -0.2132   0.01379   0.00622  -0.0216   0.9304   0.4462
  -2.750  -0.1843   0.01346   0.00600  -0.0216   0.9200   0.5037
  -2.500  -0.1551   0.01314   0.00580  -0.0215   0.9100   0.5650
  -2.250  -0.1253   0.01282   0.00563  -0.0213   0.9005   0.6323
  -2.000  -0.0965   0.01253   0.00549  -0.0208   0.8894   0.7051
  -1.750  -0.0610   0.01229   0.00541  -0.0214   0.8796   0.7868
  -1.500  -0.0095   0.01216   0.00530  -0.0252   0.8720   0.8627
  -1.250   0.0399   0.01213   0.00517  -0.0289   0.8612   0.9139
  -1.000   0.0858   0.01213   0.00504  -0.0321   0.8496   0.9474
  -0.750   0.1268   0.01215   0.00492  -0.0345   0.8368   0.9752
  -0.500   0.1708   0.01211   0.00474  -0.0377   0.8236   0.9982
  -0.250   0.1947   0.01210   0.00461  -0.0369   0.8083   1.0000
   0.000   0.2167   0.01211   0.00452  -0.0356   0.7925   1.0000
   0.250   0.2389   0.01212   0.00442  -0.0344   0.7765   1.0000
   0.500   0.2613   0.01214   0.00434  -0.0331   0.7602   1.0000
   0.750   0.2839   0.01216   0.00428  -0.0319   0.7433   1.0000
   1.000   0.3070   0.01220   0.00425  -0.0307   0.7252   1.0000
   1.250   0.3301   0.01225   0.00422  -0.0296   0.7071   1.0000
   1.500   0.3533   0.01231   0.00418  -0.0284   0.6892   1.0000
   1.750   0.3769   0.01240   0.00419  -0.0273   0.6698   1.0000
   2.000   0.4005   0.01251   0.00421  -0.0263   0.6502   1.0000
   2.250   0.4243   0.01263   0.00427  -0.0252   0.6306   1.0000
   2.500   0.4482   0.01278   0.00435  -0.0243   0.6096   1.0000
   2.750   0.4721   0.01294   0.00443  -0.0233   0.5894   1.0000
   3.000   0.4962   0.01312   0.00456  -0.0225   0.5677   1.0000
   3.250   0.5202   0.01333   0.00472  -0.0216   0.5469   1.0000
   3.500   0.5443   0.01355   0.00490  -0.0207   0.5249   1.0000
   3.750   0.5682   0.01380   0.00508  -0.0199   0.5038   1.0000
   4.000   0.5922   0.01405   0.00531  -0.0191   0.4814   1.0000
   4.250   0.6159   0.01434   0.00558  -0.0183   0.4593   1.0000
   4.500   0.6396   0.01464   0.00585  -0.0175   0.4364   1.0000
   4.750   0.6632   0.01497   0.00616  -0.0167   0.4132   1.0000
   5.000   0.6865   0.01532   0.00647  -0.0158   0.3899   1.0000
   5.250   0.7097   0.01570   0.00686  -0.0150   0.3655   1.0000
   5.500   0.7327   0.01610   0.00726  -0.0142   0.3412   1.0000
   5.750   0.7552   0.01655   0.00768  -0.0134   0.3164   1.0000
   6.000   0.7774   0.01704   0.00813  -0.0125   0.2920   1.0000
   6.250   0.7995   0.01756   0.00864  -0.0117   0.2670   1.0000
   6.500   0.8212   0.01812   0.00923  -0.0108   0.2431   1.0000
   6.750   0.8423   0.01874   0.00983  -0.0099   0.2206   1.0000
   7.000   0.8632   0.01940   0.01049  -0.0090   0.1983   1.0000
   7.250   0.8836   0.02011   0.01119  -0.0080   0.1777   1.0000
   7.500   0.9035   0.02086   0.01196  -0.0070   0.1578   1.0000
   7.750   0.9224   0.02171   0.01279  -0.0060   0.1403   1.0000
   8.000   0.9414   0.02255   0.01372  -0.0049   0.1232   1.0000
   8.250   0.9595   0.02347   0.01469  -0.0038   0.1076   1.0000
   8.500   0.9766   0.02447   0.01573  -0.0026   0.0939   1.0000
   8.750   0.9927   0.02555   0.01686  -0.0012   0.0821   1.0000
   9.000   1.0071   0.02676   0.01810   0.0002   0.0725   1.0000
   9.250   1.0207   0.02798   0.01937   0.0016   0.0634   1.0000
   9.500   1.0340   0.02927   0.02082   0.0033   0.0560   1.0000
   9.750   1.0432   0.03078   0.02232   0.0050   0.0505   1.0000
  10.000   1.0549   0.03214   0.02395   0.0067   0.0449   1.0000
  10.250   1.0621   0.03370   0.02559   0.0086   0.0413   1.0000
  10.500   1.0657   0.03555   0.02752   0.0109   0.0389   1.0000
  10.750   1.0711   0.03730   0.02951   0.0130   0.0360   1.0000
  11.000   1.0744   0.03907   0.03143   0.0147   0.0334   1.0000
  11.250   1.0750   0.04102   0.03347   0.0161   0.0313   1.0000
  11.500   1.0742   0.04361   0.03609   0.0174   0.0297   1.0000
  11.750   1.0754   0.04622   0.03901   0.0184   0.0285   1.0000
  12.000   1.0739   0.04918   0.04224   0.0191   0.0274   1.0000
  12.250   1.0697   0.05238   0.04568   0.0192   0.0261   1.0000
  12.500   1.0642   0.05578   0.04928   0.0188   0.0251   1.0000
  12.750   1.0570   0.05950   0.05316   0.0179   0.0240   1.0000
  13.000   1.0493   0.06358   0.05741   0.0165   0.0234   1.0000
  13.250   1.0408   0.06782   0.06174   0.0146   0.0225   1.0000
  13.500   1.0298   0.07286   0.06692   0.0123   0.0221   1.0000
  13.750   1.0163   0.07862   0.07285   0.0094   0.0218   1.0000
  14.000   1.0014   0.08495   0.07935   0.0060   0.0217   1.0000
  14.250   0.9838   0.09215   0.08673   0.0018   0.0217   1.0000
  14.500   0.9621   0.10093   0.09572  -0.0036   0.0220   1.0000
  14.750   0.8710   0.12984   0.12499  -0.0207   0.0273   1.0000
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