Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

MH 25 9.98% (mh25-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 25 9.98% (mh25-il)
Reynolds number: 50,000
Max Cl/Cd: 32.9 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh25-il-50000-n5.txt
Download as CSV file: xf-mh25-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 25  9.98%                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4768   0.09996   0.09299  -0.0380   1.0000   0.0385
  -9.250  -0.4824   0.09629   0.08939  -0.0386   1.0000   0.0375
  -9.000  -0.4906   0.09237   0.08556  -0.0395   1.0000   0.0367
  -8.750  -0.5014   0.08836   0.08161  -0.0407   1.0000   0.0358
  -8.500  -0.5172   0.08446   0.07778  -0.0410   1.0000   0.0352
  -8.250  -0.5349   0.08144   0.07481  -0.0394   1.0000   0.0345
  -8.000  -0.5534   0.07838   0.07176  -0.0370   1.0000   0.0340
  -7.750  -0.5712   0.07454   0.06787  -0.0349   1.0000   0.0327
  -7.500  -0.5870   0.07067   0.06385  -0.0323   1.0000   0.0318
  -7.000  -0.6012   0.06457   0.05718  -0.0264   1.0000   0.0303
  -6.750  -0.6029   0.06125   0.05374  -0.0237   1.0000   0.0300
  -6.500  -0.6039   0.05790   0.05017  -0.0209   1.0000   0.0298
  -6.250  -0.6023   0.05468   0.04672  -0.0181   1.0000   0.0295
  -6.000  -0.5985   0.05153   0.04328  -0.0154   1.0000   0.0293
  -5.750  -0.5928   0.04832   0.03971  -0.0125   1.0000   0.0292
  -5.500  -0.5842   0.04532   0.03634  -0.0099   1.0000   0.0291
  -5.250  -0.5730   0.04244   0.03302  -0.0073   1.0000   0.0291
  -5.000  -0.5591   0.03980   0.02994  -0.0050   1.0000   0.0292
  -4.750  -0.5424   0.03723   0.02688  -0.0028   1.0000   0.0295
  -4.500  -0.5229   0.03496   0.02412  -0.0008   1.0000   0.0301
  -4.250  -0.5025   0.03255   0.02145   0.0007   1.0000   0.0315
  -4.000  -0.4822   0.03097   0.01971   0.0019   1.0000   0.0354
  -3.750  -0.4587   0.02956   0.01796   0.0033   1.0000   0.0411
  -3.500  -0.4342   0.02797   0.01611   0.0045   1.0000   0.0450
  -3.250  -0.4101   0.02674   0.01469   0.0056   1.0000   0.0563
  -3.000  -0.3870   0.02549   0.01342   0.0066   1.0000   0.0753
  -2.750  -0.3099   0.02122   0.01323   0.0000   1.0000   0.8436
  -2.500  -0.1432   0.02278   0.01322  -0.0249   1.0000   1.0000
  -2.250  -0.1325   0.02264   0.01282  -0.0223   1.0000   1.0000
  -2.000  -0.1216   0.02254   0.01249  -0.0199   1.0000   1.0000
  -1.750  -0.1103   0.02247   0.01221  -0.0174   1.0000   1.0000
  -1.500  -0.0988   0.02244   0.01199  -0.0150   1.0000   1.0000
  -1.250  -0.0871   0.02243   0.01180  -0.0126   1.0000   1.0000
  -1.000  -0.0753   0.02245   0.01166  -0.0102   1.0000   1.0000
  -0.750  -0.0634   0.02250   0.01153  -0.0079   1.0000   1.0000
  -0.500  -0.0515   0.02258   0.01148  -0.0056   1.0000   1.0000
  -0.250  -0.0394   0.02269   0.01147  -0.0033   1.0000   1.0000
   0.000  -0.0274   0.02283   0.01151  -0.0011   1.0000   1.0000
   0.250  -0.0019   0.02311   0.01168  -0.0017   0.9960   1.0000
   0.500   0.0369   0.02353   0.01198  -0.0048   0.9871   1.0000
   0.750   0.0754   0.02397   0.01234  -0.0079   0.9780   1.0000
   1.000   0.1153   0.02443   0.01276  -0.0111   0.9690   1.0000
   1.250   0.1519   0.02477   0.01308  -0.0136   0.9583   1.0000
   1.500   0.1877   0.02507   0.01339  -0.0159   0.9470   1.0000
   1.750   0.2236   0.02533   0.01368  -0.0181   0.9353   1.0000
   2.000   0.2594   0.02554   0.01396  -0.0202   0.9229   1.0000
   2.250   0.2946   0.02570   0.01421  -0.0221   0.9098   1.0000
   2.500   0.3288   0.02577   0.01438  -0.0236   0.8958   1.0000
   2.750   0.3626   0.02577   0.01449  -0.0249   0.8809   1.0000
   3.000   0.3970   0.02569   0.01454  -0.0261   0.8654   1.0000
   3.250   0.4303   0.02551   0.01460  -0.0270   0.8487   1.0000
   3.500   0.4565   0.02531   0.01457  -0.0264   0.8288   1.0000
   3.750   0.4931   0.02491   0.01438  -0.0274   0.8109   1.0000
   4.000   0.5203   0.02455   0.01421  -0.0267   0.7888   1.0000
   4.250   0.5545   0.02397   0.01395  -0.0268   0.7666   1.0000
   4.500   0.5889   0.02342   0.01364  -0.0268   0.7396   1.0000
   4.750   0.6264   0.02286   0.01331  -0.0273   0.7054   1.0000
   5.000   0.6687   0.02226   0.01289  -0.0283   0.6604   1.0000
   5.250   0.7045   0.02203   0.01277  -0.0284   0.6016   1.0000
   5.500   0.7313   0.02223   0.01283  -0.0271   0.5361   1.0000
   5.750   0.7477   0.02276   0.01317  -0.0244   0.4732   1.0000
   6.000   0.7592   0.02348   0.01367  -0.0210   0.4140   1.0000
   6.250   0.7680   0.02431   0.01429  -0.0175   0.3584   1.0000
   6.500   0.7756   0.02525   0.01501  -0.0140   0.3060   1.0000
   6.750   0.7835   0.02626   0.01585  -0.0107   0.2572   1.0000
   7.000   0.7913   0.02740   0.01680  -0.0075   0.2127   1.0000
   7.250   0.7998   0.02865   0.01787  -0.0046   0.1729   1.0000
   7.500   0.8096   0.03001   0.01909  -0.0019   0.1400   1.0000
   7.750   0.8207   0.03148   0.02047   0.0005   0.1140   1.0000
   8.000   0.8346   0.03307   0.02223   0.0026   0.0952   1.0000
   8.250   0.8451   0.03454   0.02369   0.0050   0.0798   1.0000
   8.500   0.8647   0.03651   0.02586   0.0064   0.0693   1.0000
   8.750   0.8856   0.03875   0.02829   0.0075   0.0614   1.0000
   9.000   0.8947   0.04047   0.03003   0.0098   0.0537   1.0000
   9.250   0.9134   0.04315   0.03320   0.0113   0.0485   1.0000
   9.500   0.9270   0.04601   0.03642   0.0132   0.0452   1.0000
   9.750   0.9354   0.04884   0.03949   0.0154   0.0429   1.0000
  10.000   0.9371   0.05194   0.04280   0.0182   0.0406   1.0000
  10.250   0.9275   0.05463   0.04598   0.0226   0.0387   1.0000
  10.500   0.9169   0.05739   0.04908   0.0265   0.0373   1.0000
  10.750   0.9037   0.06030   0.05228   0.0300   0.0360   1.0000
  11.000   0.8893   0.06354   0.05578   0.0327   0.0354   1.0000
  11.250   0.8724   0.06711   0.05957   0.0346   0.0349   1.0000
  11.500   0.8528   0.07129   0.06397   0.0356   0.0351   1.0000
  11.750   0.8314   0.07606   0.06892   0.0352   0.0354   1.0000
  12.000   0.8081   0.08185   0.07486   0.0333   0.0360   1.0000
  12.250   0.7846   0.08880   0.08192   0.0297   0.0371   1.0000
  12.500   0.7664   0.09598   0.08913   0.0257   0.0386   1.0000
<< Back to MH 25 9.98% (mh25-il)

Polar data table (+)

Polar graphs


<< Back to MH 25 9.98% (mh25-il)