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

MH 108 11.98% (mh108-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: MH 108 11.98% (mh108-il)
Reynolds number: 200,000
Max Cl/Cd: 56.28 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh108-il-200000.txt
Download as CSV file: xf-mh108-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.7425   0.09011   0.08662   0.0004   1.0000   0.0224
 -12.000  -0.7748   0.07842   0.07486  -0.0079   1.0000   0.0214
 -11.750  -0.8075   0.06793   0.06419  -0.0165   1.0000   0.0209
 -11.500  -0.8936   0.05312   0.04858  -0.0260   1.0000   0.0180
 -11.250  -0.9071   0.04974   0.04505  -0.0256   1.0000   0.0183
 -11.000  -0.9152   0.04727   0.04247  -0.0241   1.0000   0.0186
 -10.750  -0.9346   0.04378   0.03858  -0.0206   1.0000   0.0182
 -10.500  -0.9313   0.04209   0.03684  -0.0188   1.0000   0.0189
 -10.250  -0.9282   0.03991   0.03447  -0.0169   1.0000   0.0193
 -10.000  -0.9189   0.03840   0.03285  -0.0153   1.0000   0.0204
  -9.750  -0.9132   0.03579   0.02992  -0.0132   1.0000   0.0207
  -9.500  -0.9035   0.03343   0.02724  -0.0112   1.0000   0.0214
  -9.250  -0.8909   0.03105   0.02453  -0.0094   1.0000   0.0218
  -9.000  -0.8753   0.02901   0.02221  -0.0078   1.0000   0.0224
  -8.750  -0.8572   0.02735   0.02030  -0.0063   1.0000   0.0231
  -8.500  -0.8420   0.02467   0.01752  -0.0048   1.0000   0.0244
  -8.250  -0.8235   0.02333   0.01616  -0.0034   1.0000   0.0263
  -8.000  -0.8035   0.02221   0.01493  -0.0021   1.0000   0.0293
  -7.750  -0.7859   0.02080   0.01351  -0.0006   1.0000   0.0338
  -7.500  -0.7660   0.01970   0.01232   0.0008   1.0000   0.0401
  -7.250  -0.7470   0.01855   0.01117   0.0023   1.0000   0.0508
  -7.000  -0.7274   0.01755   0.01025   0.0036   1.0000   0.0654
  -6.750  -0.7058   0.01685   0.00959   0.0046   1.0000   0.0808
  -6.500  -0.6833   0.01628   0.00903   0.0056   1.0000   0.0967
  -6.250  -0.6605   0.01578   0.00851   0.0065   1.0000   0.1132
  -6.000  -0.6386   0.01518   0.00797   0.0075   1.0000   0.1299
  -5.750  -0.6167   0.01463   0.00751   0.0086   1.0000   0.1473
  -5.500  -0.5945   0.01414   0.00707   0.0096   1.0000   0.1661
  -5.250  -0.5726   0.01367   0.00666   0.0107   1.0000   0.1866
  -5.000  -0.5515   0.01321   0.00632   0.0119   1.0000   0.2085
  -4.750  -0.5310   0.01279   0.00599   0.0132   1.0000   0.2322
  -4.500  -0.5114   0.01242   0.00573   0.0147   1.0000   0.2575
  -4.250  -0.4775   0.01198   0.00546   0.0130   0.9879   0.2911
  -4.000  -0.4318   0.01152   0.00517   0.0092   0.9587   0.3350
  -3.750  -0.3881   0.01110   0.00488   0.0061   0.9224   0.3813
  -3.500  -0.3545   0.01080   0.00465   0.0053   0.8810   0.4252
  -3.250  -0.3306   0.01061   0.00447   0.0067   0.8414   0.4663
  -3.000  -0.3090   0.01043   0.00432   0.0084   0.8076   0.5086
  -2.750  -0.2874   0.01026   0.00418   0.0102   0.7775   0.5523
  -2.500  -0.2654   0.01009   0.00407   0.0118   0.7498   0.5994
  -2.250  -0.2430   0.00992   0.00399   0.0135   0.7243   0.6489
  -2.000  -0.2201   0.00980   0.00392   0.0151   0.7013   0.6995
  -1.750  -0.1959   0.00971   0.00390   0.0165   0.6783   0.7494
  -1.500  -0.1698   0.00970   0.00391   0.0176   0.6573   0.7961
  -1.250  -0.1406   0.00976   0.00396   0.0181   0.6357   0.8380
  -1.000  -0.1067   0.00993   0.00405   0.0177   0.6157   0.8714
  -0.750  -0.0702   0.01016   0.00416   0.0167   0.5954   0.8981
  -0.500  -0.0298   0.01043   0.00429   0.0148   0.5749   0.9173
  -0.250   0.0117   0.01073   0.00442   0.0126   0.5563   0.9325
   0.000   0.0559   0.01104   0.00454   0.0098   0.5385   0.9446
   0.250   0.0993   0.01128   0.00465   0.0070   0.5205   0.9565
   0.500   0.1433   0.01151   0.00474   0.0039   0.5037   0.9677
   0.750   0.1917   0.01168   0.00477  -0.0002   0.4881   0.9764
   1.000   0.2377   0.01180   0.00476  -0.0039   0.4736   0.9857
   1.250   0.2846   0.01186   0.00471  -0.0079   0.4600   0.9945
   1.500   0.3249   0.01186   0.00459  -0.0107   0.4488   1.0000
   1.750   0.3467   0.01189   0.00458  -0.0098   0.4391   1.0000
   2.000   0.3689   0.01197   0.00461  -0.0089   0.4305   1.0000
   2.250   0.3914   0.01206   0.00462  -0.0081   0.4224   1.0000
   2.500   0.4143   0.01216   0.00471  -0.0073   0.4141   1.0000
   2.750   0.4372   0.01230   0.00476  -0.0065   0.4069   1.0000
   3.000   0.4605   0.01241   0.00490  -0.0057   0.3990   1.0000
   3.250   0.4837   0.01259   0.00499  -0.0049   0.3922   1.0000
   3.500   0.5071   0.01273   0.00519  -0.0041   0.3847   1.0000
   3.750   0.5305   0.01292   0.00531  -0.0033   0.3781   1.0000
   4.000   0.5540   0.01310   0.00553  -0.0025   0.3709   1.0000
   4.250   0.5776   0.01329   0.00568  -0.0017   0.3643   1.0000
   4.500   0.6012   0.01351   0.00595  -0.0009   0.3575   1.0000
   4.750   0.6249   0.01370   0.00614  -0.0001   0.3506   1.0000
   5.000   0.6485   0.01395   0.00639   0.0007   0.3441   1.0000
   5.250   0.6721   0.01415   0.00664   0.0015   0.3369   1.0000
   5.500   0.6958   0.01442   0.00690   0.0022   0.3305   1.0000
   5.750   0.7194   0.01462   0.00716   0.0031   0.3229   1.0000
   6.000   0.7430   0.01490   0.00743   0.0038   0.3163   1.0000
   6.250   0.7665   0.01510   0.00773   0.0047   0.3084   1.0000
   6.500   0.7899   0.01538   0.00801   0.0055   0.3011   1.0000
   6.750   0.8132   0.01558   0.00828   0.0063   0.2928   1.0000
   7.000   0.8363   0.01585   0.00861   0.0072   0.2848   1.0000
   7.250   0.8595   0.01606   0.00883   0.0080   0.2763   1.0000
   7.500   0.8822   0.01632   0.00922   0.0089   0.2671   1.0000
   7.750   0.9049   0.01659   0.00948   0.0098   0.2582   1.0000
   8.000   0.9273   0.01679   0.00977   0.0108   0.2480   1.0000
   8.250   0.9493   0.01706   0.01014   0.0117   0.2372   1.0000
   8.500   0.9711   0.01734   0.01047   0.0127   0.2262   1.0000
   8.750   0.9924   0.01765   0.01083   0.0137   0.2150   1.0000
   9.000   1.0131   0.01800   0.01119   0.0148   0.2031   1.0000
   9.250   1.0333   0.01839   0.01165   0.0159   0.1904   1.0000
   9.500   1.0528   0.01887   0.01218   0.0170   0.1774   1.0000
   9.750   1.0714   0.01944   0.01280   0.0182   0.1646   1.0000
  10.000   1.0891   0.02009   0.01350   0.0195   0.1523   1.0000
  10.250   1.1058   0.02083   0.01431   0.0208   0.1406   1.0000
  10.500   1.1211   0.02166   0.01517   0.0222   0.1294   1.0000
  10.750   1.1346   0.02257   0.01610   0.0238   0.1184   1.0000
  11.000   1.1458   0.02360   0.01711   0.0255   0.1077   1.0000
  11.250   1.1569   0.02457   0.01817   0.0271   0.0970   1.0000
  11.500   1.1653   0.02568   0.01937   0.0290   0.0870   1.0000
  11.750   1.1676   0.02701   0.02074   0.0314   0.0784   1.0000
  12.000   1.1633   0.02856   0.02230   0.0341   0.0720   1.0000
  12.250   1.1608   0.03040   0.02425   0.0357   0.0654   1.0000
  12.500   1.1533   0.03306   0.02694   0.0362   0.0602   1.0000
  12.750   1.1490   0.03591   0.02992   0.0359   0.0551   1.0000
  13.000   1.1424   0.03931   0.03338   0.0349   0.0508   1.0000
  13.250   1.1303   0.04342   0.03749   0.0337   0.0475   1.0000
  13.500   1.1256   0.04702   0.04126   0.0323   0.0440   1.0000
  13.750   1.1168   0.05114   0.04546   0.0306   0.0411   1.0000
  14.000   1.1035   0.05568   0.04998   0.0290   0.0387   1.0000
  14.250   1.0950   0.05994   0.05436   0.0274   0.0361   1.0000
  14.500   1.0869   0.06416   0.05870   0.0257   0.0341   1.0000
  14.750   1.0782   0.06853   0.06313   0.0239   0.0324   1.0000
  15.000   1.0681   0.07301   0.06762   0.0221   0.0306   1.0000
  15.250   1.0608   0.07720   0.07185   0.0208   0.0288   1.0000
  15.500   1.0528   0.08204   0.07684   0.0185   0.0273   1.0000
  15.750   1.0469   0.08652   0.08143   0.0166   0.0261   1.0000
<< Back to MH 108 11.98% (mh108-il)

Polar data table (+)

Polar graphs


<< Back to MH 108 11.98% (mh108-il)