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MH 24 9.01% (mh24-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 24 9.01% (mh24-il)
Reynolds number: 100,000
Max Cl/Cd: 47.03 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh24-il-100000-n5.txt
Download as CSV file: xf-mh24-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 24  9.01%                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4728   0.10346   0.09835  -0.0321   1.0000   0.0239
  -9.750  -0.4724   0.09993   0.09485  -0.0321   1.0000   0.0224
  -9.500  -0.4744   0.09613   0.09111  -0.0329   1.0000   0.0214
  -9.250  -0.4779   0.09228   0.08732  -0.0340   1.0000   0.0206
  -9.000  -0.4836   0.08824   0.08335  -0.0352   1.0000   0.0199
  -8.750  -0.4921   0.08406   0.07924  -0.0367   1.0000   0.0192
  -8.500  -0.5042   0.07988   0.07515  -0.0385   1.0000   0.0188
  -8.250  -0.5219   0.07622   0.07153  -0.0385   1.0000   0.0185
  -8.000  -0.5407   0.07348   0.06881  -0.0362   1.0000   0.0183
  -7.750  -0.5572   0.06970   0.06500  -0.0343   1.0000   0.0177
  -7.500  -0.5721   0.06536   0.06056  -0.0321   1.0000   0.0168
  -7.250  -0.5791   0.06099   0.05596  -0.0296   1.0000   0.0157
  -6.750  -0.5813   0.05548   0.05013  -0.0241   1.0000   0.0149
  -6.500  -0.5844   0.05204   0.04651  -0.0212   1.0000   0.0147
  -6.250  -0.5841   0.04882   0.04308  -0.0184   1.0000   0.0144
  -6.000  -0.5813   0.04559   0.03959  -0.0156   1.0000   0.0142
  -5.750  -0.5762   0.04238   0.03606  -0.0128   1.0000   0.0140
  -5.500  -0.5684   0.03932   0.03266  -0.0101   1.0000   0.0138
  -5.250  -0.5579   0.03651   0.02947  -0.0075   1.0000   0.0136
  -5.000  -0.5451   0.03371   0.02625  -0.0050   1.0000   0.0135
  -4.750  -0.5297   0.03127   0.02339  -0.0028   1.0000   0.0134
  -4.500  -0.5120   0.02899   0.02069  -0.0007   1.0000   0.0132
  -4.250  -0.4922   0.02693   0.01813   0.0011   1.0000   0.0133
  -4.000  -0.4712   0.02521   0.01608   0.0027   1.0000   0.0134
  -3.750  -0.4460   0.02358   0.01417   0.0035   0.9990   0.0136
  -3.500  -0.4160   0.02214   0.01250   0.0032   0.9963   0.0142
  -3.250  -0.3857   0.02117   0.01137   0.0027   0.9933   0.0152
  -3.000  -0.3586   0.02002   0.01015   0.0025   0.9898   0.0207
  -2.750  -0.3285   0.01932   0.00923   0.0021   0.9859   0.0245
  -2.500  -0.2990   0.01806   0.00815   0.0018   0.9826   0.0623
  -2.250  -0.2833   0.01531   0.00787   0.0031   0.9796   0.5279
  -2.000  -0.2157   0.01553   0.00902  -0.0012   0.9855   0.9369
  -1.750  -0.1428   0.01602   0.00909  -0.0099   0.9893   0.9747
  -1.500  -0.0663   0.01621   0.00892  -0.0200   0.9943   1.0000
  -1.250  -0.0313   0.01621   0.00871  -0.0221   0.9886   1.0000
  -1.000   0.0059   0.01629   0.00863  -0.0247   0.9832   1.0000
  -0.750   0.0408   0.01632   0.00853  -0.0267   0.9770   1.0000
  -0.500   0.0785   0.01637   0.00848  -0.0292   0.9710   1.0000
  -0.250   0.1132   0.01639   0.00839  -0.0311   0.9639   1.0000
   0.000   0.1523   0.01641   0.00835  -0.0338   0.9575   1.0000
   0.250   0.1860   0.01640   0.00830  -0.0354   0.9493   1.0000
   0.500   0.2282   0.01637   0.00827  -0.0386   0.9431   1.0000
   0.750   0.2608   0.01630   0.00820  -0.0398   0.9332   1.0000
   1.000   0.2977   0.01620   0.00812  -0.0418   0.9245   1.0000
   1.250   0.3408   0.01603   0.00800  -0.0449   0.9167   1.0000
   1.500   0.3725   0.01586   0.00791  -0.0456   0.9050   1.0000
   1.750   0.4030   0.01566   0.00777  -0.0460   0.8924   1.0000
   2.000   0.4321   0.01542   0.00760  -0.0460   0.8783   1.0000
   2.250   0.4600   0.01515   0.00742  -0.0457   0.8627   1.0000
   2.500   0.4780   0.01498   0.00733  -0.0435   0.8410   1.0000
   2.750   0.5028   0.01473   0.00723  -0.0424   0.8183   1.0000
   3.000   0.5328   0.01441   0.00700  -0.0423   0.7916   1.0000
   3.250   0.5696   0.01403   0.00667  -0.0432   0.7571   1.0000
   3.500   0.6064   0.01374   0.00634  -0.0441   0.7062   1.0000
   3.750   0.6371   0.01375   0.00624  -0.0440   0.6428   1.0000
   4.000   0.6599   0.01403   0.00630  -0.0425   0.5760   1.0000
   4.250   0.6783   0.01448   0.00650  -0.0404   0.5107   1.0000
   4.500   0.6945   0.01501   0.00680  -0.0381   0.4475   1.0000
   4.750   0.7096   0.01560   0.00717  -0.0357   0.3874   1.0000
   5.000   0.7241   0.01623   0.00759  -0.0333   0.3303   1.0000
   5.250   0.7383   0.01691   0.00807  -0.0309   0.2756   1.0000
   5.500   0.7523   0.01762   0.00859  -0.0285   0.2260   1.0000
   5.750   0.7663   0.01838   0.00927  -0.0262   0.1792   1.0000
   6.000   0.7801   0.01919   0.00993  -0.0239   0.1392   1.0000
   6.250   0.7933   0.02008   0.01067  -0.0215   0.1044   1.0000
   6.500   0.8062   0.02102   0.01151  -0.0190   0.0794   1.0000
   6.750   0.8185   0.02202   0.01252  -0.0163   0.0625   1.0000
   7.000   0.8310   0.02300   0.01350  -0.0137   0.0491   1.0000
   7.250   0.8420   0.02415   0.01472  -0.0108   0.0421   1.0000
   7.500   0.8535   0.02532   0.01602  -0.0080   0.0372   1.0000
   7.750   0.8622   0.02700   0.01773  -0.0049   0.0336   1.0000
   8.000   0.8773   0.02827   0.01927  -0.0026   0.0292   1.0000
   8.250   0.8893   0.02954   0.02065  -0.0002   0.0248   1.0000
   8.500   0.9016   0.03215   0.02342   0.0021   0.0224   1.0000
   8.750   0.9149   0.03373   0.02538   0.0044   0.0186   1.0000
   9.000   0.9245   0.03531   0.02730   0.0069   0.0161   1.0000
   9.250   0.9304   0.03772   0.02992   0.0097   0.0147   1.0000
   9.750   0.9295   0.04407   0.03701   0.0164   0.0131   1.0000
  10.000   0.9245   0.04665   0.03993   0.0202   0.0128   1.0000
  10.250   0.9148   0.04939   0.04299   0.0241   0.0125   1.0000
  10.500   0.9030   0.05210   0.04604   0.0274   0.0114   1.0000
  10.750   0.8889   0.05540   0.04959   0.0299   0.0118   1.0000
  11.000   0.8729   0.05886   0.05330   0.0315   0.0109   1.0000
  11.250   0.8538   0.06332   0.05796   0.0318   0.0119   1.0000
  11.500   0.8346   0.06818   0.06303   0.0304   0.0113   1.0000
  11.750   0.8160   0.07393   0.06890   0.0277   0.0123   1.0000
  12.000   0.7960   0.08107   0.07615   0.0231   0.0127   1.0000
  12.250   0.7775   0.08918   0.08433   0.0176   0.0130   1.0000
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