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MH 108 11.98% (mh108-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 108 11.98% (mh108-il)
Reynolds number: 100,000
Max Cl/Cd: 36.13 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh108-il-100000.txt
Download as CSV file: xf-mh108-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.7171   0.08168   0.07697  -0.0114   1.0000   0.0491
 -10.750  -0.7357   0.07455   0.06982  -0.0161   1.0000   0.0484
 -10.500  -0.7583   0.06831   0.06349  -0.0201   1.0000   0.0476
 -10.250  -0.7806   0.06323   0.05829  -0.0216   1.0000   0.0465
 -10.000  -0.8054   0.05886   0.05373  -0.0208   1.0000   0.0459
  -9.750  -0.8248   0.05469   0.04931  -0.0189   1.0000   0.0454
  -9.500  -0.8367   0.05065   0.04491  -0.0170   1.0000   0.0459
  -9.250  -0.8423   0.04668   0.04052  -0.0149   1.0000   0.0465
  -9.000  -0.8420   0.04291   0.03627  -0.0127   1.0000   0.0472
  -8.750  -0.8368   0.03935   0.03217  -0.0105   1.0000   0.0482
  -8.500  -0.8265   0.03640   0.02863  -0.0082   1.0000   0.0495
  -8.250  -0.8107   0.03306   0.02526  -0.0072   1.0000   0.0529
  -8.000  -0.7932   0.03148   0.02344  -0.0057   1.0000   0.0591
  -7.750  -0.7744   0.02899   0.02083  -0.0043   1.0000   0.0654
  -7.500  -0.7553   0.02723   0.01881  -0.0029   1.0000   0.0755
  -7.250  -0.7358   0.02572   0.01727  -0.0015   1.0000   0.0889
  -7.000  -0.7161   0.02448   0.01609  -0.0003   1.0000   0.1047
  -6.750  -0.6960   0.02346   0.01507   0.0010   1.0000   0.1224
  -6.500  -0.6753   0.02250   0.01398   0.0023   1.0000   0.1411
  -6.250  -0.6538   0.02144   0.01305   0.0034   1.0000   0.1596
  -6.000  -0.6322   0.02058   0.01223   0.0045   1.0000   0.1794
  -5.750  -0.6104   0.01973   0.01137   0.0057   1.0000   0.2008
  -5.500  -0.5888   0.01895   0.01072   0.0068   1.0000   0.2235
  -5.250  -0.5674   0.01818   0.01006   0.0080   1.0000   0.2479
  -5.000  -0.5464   0.01749   0.00948   0.0093   1.0000   0.2751
  -4.750  -0.5260   0.01685   0.00896   0.0107   1.0000   0.3043
  -4.500  -0.5065   0.01625   0.00854   0.0122   1.0000   0.3353
  -4.250  -0.4883   0.01570   0.00819   0.0139   1.0000   0.3685
  -4.000  -0.4721   0.01524   0.00791   0.0158   1.0000   0.4045
  -3.750  -0.4603   0.01485   0.00776   0.0183   1.0000   0.4390
  -3.500  -0.4393   0.01456   0.00769   0.0186   0.9935   0.4835
  -3.250  -0.3830   0.01406   0.00752   0.0130   0.9692   0.5560
  -3.000  -0.3317   0.01363   0.00738   0.0091   0.9428   0.6283
  -2.750  -0.2855   0.01334   0.00731   0.0068   0.9137   0.6946
  -2.500  -0.2466   0.01328   0.00734   0.0064   0.8820   0.7530
  -2.250  -0.2134   0.01342   0.00745   0.0074   0.8494   0.8021
  -2.000  -0.1787   0.01373   0.00763   0.0080   0.8174   0.8425
  -1.750  -0.1395   0.01415   0.00787   0.0077   0.7866   0.8753
  -1.500  -0.0943   0.01463   0.00809   0.0061   0.7568   0.9011
  -1.250  -0.0440   0.01508   0.00827   0.0030   0.7275   0.9231
  -1.000   0.0100   0.01544   0.00835  -0.0011   0.6991   0.9425
  -0.750   0.0653   0.01568   0.00830  -0.0059   0.6724   0.9615
  -0.500   0.1199   0.01575   0.00814  -0.0111   0.6462   0.9810
  -0.250   0.1795   0.01554   0.00770  -0.0176   0.6211   0.9977
   0.000   0.2032   0.01546   0.00747  -0.0176   0.6037   1.0000
   0.250   0.2221   0.01547   0.00733  -0.0166   0.5884   1.0000
   0.500   0.2418   0.01552   0.00726  -0.0156   0.5739   1.0000
   0.750   0.2623   0.01559   0.00723  -0.0146   0.5601   1.0000
   1.000   0.2833   0.01571   0.00724  -0.0137   0.5473   1.0000
   1.250   0.3048   0.01585   0.00728  -0.0127   0.5359   1.0000
   1.500   0.3266   0.01602   0.00734  -0.0118   0.5251   1.0000
   1.750   0.3487   0.01622   0.00751  -0.0110   0.5135   1.0000
   2.000   0.3709   0.01646   0.00773  -0.0101   0.5033   1.0000
   2.250   0.3933   0.01671   0.00785  -0.0092   0.4948   1.0000
   2.500   0.4160   0.01699   0.00817  -0.0084   0.4843   1.0000
   2.750   0.4387   0.01731   0.00847  -0.0076   0.4756   1.0000
   3.000   0.4615   0.01761   0.00872  -0.0067   0.4671   1.0000
   3.250   0.4843   0.01799   0.00914  -0.0060   0.4581   1.0000
   3.500   0.5074   0.01830   0.00937  -0.0050   0.4508   1.0000
   3.750   0.5301   0.01873   0.00990  -0.0043   0.4415   1.0000
   4.000   0.5534   0.01909   0.01019  -0.0034   0.4344   1.0000
   4.250   0.5761   0.01953   0.01073  -0.0026   0.4254   1.0000
   4.500   0.5991   0.01995   0.01117  -0.0017   0.4177   1.0000
   4.750   0.6220   0.02036   0.01162  -0.0009   0.4093   1.0000
   5.000   0.6446   0.02086   0.01219   0.0000   0.4011   1.0000
   5.250   0.6680   0.02122   0.01252   0.0009   0.3931   1.0000
   5.500   0.6899   0.02179   0.01325   0.0017   0.3842   1.0000
   5.750   0.7141   0.02210   0.01346   0.0027   0.3769   1.0000
   6.000   0.7353   0.02270   0.01426   0.0036   0.3669   1.0000
   6.250   0.7580   0.02316   0.01476   0.0045   0.3584   1.0000
   6.500   0.7811   0.02353   0.01517   0.0055   0.3494   1.0000
   6.750   0.8021   0.02414   0.01594   0.0065   0.3394   1.0000
   7.000   0.8256   0.02449   0.01625   0.0074   0.3307   1.0000
   7.250   0.8477   0.02490   0.01676   0.0084   0.3205   1.0000
   7.500   0.8682   0.02550   0.01753   0.0095   0.3098   1.0000
   7.750   0.8907   0.02590   0.01794   0.0105   0.3001   1.0000
   8.000   0.9142   0.02613   0.01815   0.0115   0.2900   1.0000
   8.250   0.9335   0.02670   0.01891   0.0128   0.2783   1.0000
   8.500   0.9536   0.02725   0.01958   0.0139   0.2672   1.0000
   8.750   0.9755   0.02757   0.01991   0.0150   0.2564   1.0000
   9.000   0.9996   0.02767   0.01993   0.0160   0.2458   1.0000
   9.250   1.0172   0.02819   0.02065   0.0174   0.2335   1.0000
   9.500   1.0351   0.02870   0.02131   0.0187   0.2213   1.0000
   9.750   1.0531   0.02922   0.02192   0.0201   0.2093   1.0000
  10.000   1.0709   0.02968   0.02244   0.0215   0.1973   1.0000
  10.250   1.0882   0.03019   0.02298   0.0228   0.1854   1.0000
  10.500   1.1043   0.03077   0.02357   0.0243   0.1732   1.0000
  10.750   1.1192   0.03151   0.02427   0.0257   0.1611   1.0000
  11.000   1.1313   0.03243   0.02519   0.0273   0.1488   1.0000
  11.250   1.1376   0.03373   0.02668   0.0293   0.1377   1.0000
  11.500   1.1418   0.03523   0.02831   0.0314   0.1271   1.0000
  11.750   1.1457   0.03680   0.02991   0.0333   0.1174   1.0000
  12.000   1.1507   0.03824   0.03120   0.0351   0.1076   1.0000
  12.250   1.1381   0.04023   0.03349   0.0381   0.1018   1.0000
  12.500   1.1387   0.04208   0.03521   0.0396   0.0941   1.0000
  12.750   1.1249   0.04488   0.03829   0.0405   0.0896   1.0000
  13.000   1.1276   0.04697   0.04017   0.0410   0.0822   1.0000
  13.250   1.1115   0.05081   0.04438   0.0403   0.0792   1.0000
  13.500   1.1010   0.05445   0.04818   0.0392   0.0753   1.0000
  13.750   1.1022   0.05715   0.05073   0.0392   0.0696   1.0000
  14.000   1.0844   0.06217   0.05603   0.0369   0.0677   1.0000
  14.250   1.0668   0.06755   0.06164   0.0343   0.0659   1.0000
  14.500   1.0508   0.07294   0.06721   0.0315   0.0641   1.0000
  14.750   1.0597   0.07482   0.06885   0.0322   0.0585   1.0000
  15.000   1.0374   0.08142   0.07569   0.0284   0.0580   1.0000
  15.250   1.0146   0.08859   0.08306   0.0243   0.0580   1.0000
  15.500   0.9879   0.09685   0.09150   0.0194   0.0583   1.0000
  15.750   0.9606   0.10593   0.10076   0.0143   0.0589   1.0000
  16.000   0.7551   0.17172   0.16635  -0.0207   0.0951   1.0000
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