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MH 108 11.98% (mh108-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 108 11.98% (mh108-il)
Reynolds number: 50,000
Max Cl/Cd: 25.86 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh108-il-50000-n5.txt
Download as CSV file: xf-mh108-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 108  11.98%                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.6814   0.09435   0.08769  -0.0002   1.0000   0.0475
 -11.000  -0.7045   0.08447   0.07782  -0.0068   1.0000   0.0465
 -10.750  -0.7346   0.07473   0.06800  -0.0141   1.0000   0.0450
 -10.500  -0.7677   0.06680   0.05988  -0.0192   1.0000   0.0434
 -10.250  -0.7920   0.06150   0.05436  -0.0205   1.0000   0.0430
 -10.000  -0.8083   0.05769   0.05034  -0.0195   1.0000   0.0435
  -9.750  -0.8173   0.05419   0.04659  -0.0182   1.0000   0.0447
  -9.500  -0.8222   0.05061   0.04264  -0.0168   1.0000   0.0466
  -9.250  -0.8236   0.04691   0.03840  -0.0151   1.0000   0.0490
  -9.000  -0.8148   0.04428   0.03566  -0.0139   1.0000   0.0517
  -8.750  -0.8037   0.04207   0.03331  -0.0125   1.0000   0.0558
  -8.500  -0.7923   0.03930   0.03003  -0.0110   1.0000   0.0616
  -8.250  -0.7774   0.03757   0.02837  -0.0098   1.0000   0.0677
  -8.000  -0.7618   0.03553   0.02608  -0.0085   1.0000   0.0763
  -7.750  -0.7448   0.03377   0.02403  -0.0072   1.0000   0.0871
  -7.500  -0.7271   0.03230   0.02251  -0.0060   1.0000   0.0986
  -7.250  -0.7087   0.03092   0.02107  -0.0048   1.0000   0.1123
  -7.000  -0.6892   0.02961   0.01965  -0.0037   1.0000   0.1271
  -6.750  -0.6691   0.02843   0.01846  -0.0026   1.0000   0.1429
  -6.500  -0.6489   0.02738   0.01743  -0.0016   1.0000   0.1599
  -6.250  -0.6277   0.02636   0.01636  -0.0005   1.0000   0.1781
  -6.000  -0.6060   0.02542   0.01533   0.0004   1.0000   0.1993
  -5.750  -0.5845   0.02454   0.01455   0.0014   1.0000   0.2197
  -5.500  -0.5624   0.02373   0.01372   0.0024   1.0000   0.2438
  -5.250  -0.5406   0.02297   0.01303   0.0033   1.0000   0.2688
  -5.000  -0.5187   0.02226   0.01237   0.0043   1.0000   0.2957
  -4.750  -0.4970   0.02160   0.01180   0.0053   1.0000   0.3257
  -4.500  -0.4755   0.02099   0.01128   0.0064   1.0000   0.3574
  -4.250  -0.4546   0.02043   0.01084   0.0076   1.0000   0.3914
  -4.000  -0.4346   0.01990   0.01047   0.0090   1.0000   0.4268
  -3.750  -0.4159   0.01944   0.01014   0.0105   1.0000   0.4650
  -3.500  -0.3994   0.01903   0.00994   0.0125   1.0000   0.5031
  -3.250  -0.3701   0.01867   0.00978   0.0119   0.9814   0.5523
  -3.000  -0.3255   0.01836   0.00965   0.0091   0.9437   0.6123
  -2.750  -0.2789   0.01818   0.00957   0.0065   0.9092   0.6726
  -2.500  -0.2333   0.01815   0.00957   0.0046   0.8744   0.7270
  -2.250  -0.1902   0.01826   0.00957   0.0033   0.8399   0.7746
  -2.000  -0.1488   0.01846   0.00959   0.0024   0.8070   0.8143
  -1.750  -0.1105   0.01870   0.00959   0.0018   0.7756   0.8492
  -1.500  -0.0710   0.01895   0.00957   0.0009   0.7463   0.8792
  -1.250  -0.0272   0.01919   0.00954  -0.0012   0.7181   0.9044
  -1.000   0.0161   0.01937   0.00944  -0.0035   0.6913   0.9284
  -0.750   0.0607   0.01948   0.00931  -0.0064   0.6663   0.9507
  -0.500   0.1057   0.01953   0.00909  -0.0097   0.6435   0.9714
  -0.250   0.1532   0.01949   0.00884  -0.0138   0.6206   0.9907
   0.000   0.1873   0.01945   0.00861  -0.0155   0.6017   1.0000
   0.250   0.2074   0.01949   0.00851  -0.0145   0.5860   1.0000
   0.500   0.2280   0.01958   0.00847  -0.0136   0.5713   1.0000
   0.750   0.2489   0.01971   0.00849  -0.0126   0.5571   1.0000
   1.000   0.2702   0.01986   0.00855  -0.0117   0.5436   1.0000
   1.250   0.2919   0.02005   0.00866  -0.0108   0.5311   1.0000
   1.500   0.3137   0.02027   0.00879  -0.0099   0.5195   1.0000
   1.750   0.3354   0.02049   0.00891  -0.0089   0.5089   1.0000
   2.000   0.3574   0.02077   0.00918  -0.0081   0.4975   1.0000
   2.250   0.3802   0.02108   0.00946  -0.0073   0.4871   1.0000
   2.500   0.4028   0.02139   0.00970  -0.0065   0.4778   1.0000
   2.750   0.4253   0.02174   0.01004  -0.0057   0.4679   1.0000
   3.000   0.4480   0.02214   0.01047  -0.0049   0.4587   1.0000
   3.250   0.4706   0.02249   0.01075  -0.0040   0.4508   1.0000
   3.500   0.4930   0.02296   0.01130  -0.0033   0.4411   1.0000
   3.750   0.5156   0.02338   0.01171  -0.0024   0.4334   1.0000
   4.000   0.5380   0.02387   0.01226  -0.0016   0.4246   1.0000
   4.250   0.5604   0.02437   0.01281  -0.0007   0.4164   1.0000
   4.500   0.5828   0.02484   0.01333   0.0002   0.4084   1.0000
   4.750   0.6047   0.02543   0.01402   0.0010   0.3997   1.0000
   5.000   0.6273   0.02588   0.01446   0.0019   0.3924   1.0000
   5.250   0.6485   0.02657   0.01531   0.0027   0.3832   1.0000
   5.500   0.6713   0.02698   0.01572   0.0038   0.3762   1.0000
   5.750   0.6917   0.02775   0.01669   0.0046   0.3667   1.0000
   6.000   0.7133   0.02833   0.01734   0.0056   0.3586   1.0000
   6.250   0.7344   0.02895   0.01806   0.0065   0.3500   1.0000
   6.500   0.7544   0.02971   0.01901   0.0075   0.3409   1.0000
   6.750   0.7771   0.03012   0.01943   0.0086   0.3333   1.0000
   7.000   0.7952   0.03107   0.02062   0.0095   0.3231   1.0000
   7.250   0.8156   0.03173   0.02139   0.0106   0.3144   1.0000
   7.500   0.8360   0.03233   0.02210   0.0117   0.3054   1.0000
   7.750   0.8530   0.03332   0.02334   0.0128   0.2952   1.0000
   8.000   0.8736   0.03389   0.02399   0.0139   0.2866   1.0000
   8.250   0.8916   0.03466   0.02492   0.0150   0.2767   1.0000
   8.500   0.9063   0.03581   0.02630   0.0162   0.2664   1.0000
   8.750   0.9251   0.03644   0.02703   0.0174   0.2573   1.0000
   9.000   0.9419   0.03719   0.02793   0.0187   0.2474   1.0000
   9.250   0.9522   0.03866   0.02970   0.0199   0.2372   1.0000
   9.500   0.9672   0.03951   0.03067   0.0212   0.2278   1.0000
   9.750   0.9836   0.04008   0.03132   0.0226   0.2183   1.0000
  10.000   0.9864   0.04209   0.03360   0.0240   0.2087   1.0000
  10.250   0.9967   0.04316   0.03477   0.0254   0.1998   1.0000
  10.500   1.0073   0.04407   0.03576   0.0268   0.1909   1.0000
  10.750   0.9996   0.04682   0.03872   0.0282   0.1834   1.0000
  11.000   1.0132   0.04719   0.03906   0.0298   0.1749   1.0000
  11.250   0.9850   0.05165   0.04374   0.0305   0.1704   1.0000
  11.500   1.0027   0.05162   0.04367   0.0320   0.1617   1.0000
  11.750   0.9633   0.05885   0.05108   0.0292   0.1589   1.0000
  12.000   0.8897   0.07340   0.06569   0.0207   0.1574   1.0000
  12.250   0.8533   0.08325   0.07551   0.0155   0.1518   1.0000
  12.500   0.8480   0.08766   0.07994   0.0140   0.1463   1.0000
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