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

MH 70 11.08% (mh70-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: MH 70 11.08% (mh70-il)
Reynolds number: 200,000
Max Cl/Cd: 67.9 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh70-il-200000-n5.txt
Download as CSV file: xf-mh70-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 70  11.08%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3982   0.09563   0.09208  -0.0238   1.0000   0.0117
  -9.500  -0.3994   0.09087   0.08737  -0.0261   1.0000   0.0117
  -9.250  -0.3956   0.08774   0.08427  -0.0275   1.0000   0.0114
  -9.000  -0.3977   0.08307   0.07966  -0.0299   1.0000   0.0114
  -8.750  -0.3990   0.07884   0.07548  -0.0322   1.0000   0.0111
  -8.500  -0.4044   0.07381   0.07052  -0.0353   1.0000   0.0111
  -8.250  -0.4128   0.06858   0.06538  -0.0388   1.0000   0.0108
  -8.000  -0.4277   0.06214   0.05902  -0.0445   1.0000   0.0106
  -7.750  -0.4342   0.04435   0.04067  -0.0621   0.9470   0.0100
  -7.500  -0.4296   0.03671   0.03237  -0.0658   0.9249   0.0099
  -7.250  -0.4192   0.03197   0.02703  -0.0662   0.9083   0.0100
  -7.000  -0.4024   0.02916   0.02376  -0.0659   0.8953   0.0104
  -6.750  -0.3844   0.02670   0.02080  -0.0651   0.8833   0.0110
  -6.500  -0.3647   0.02434   0.01782  -0.0641   0.8725   0.0117
  -6.250  -0.3432   0.02283   0.01608  -0.0634   0.8633   0.0122
  -6.000  -0.3203   0.02152   0.01453  -0.0626   0.8535   0.0125
  -5.750  -0.2967   0.02024   0.01301  -0.0619   0.8449   0.0128
  -5.500  -0.2727   0.01911   0.01167  -0.0611   0.8363   0.0132
  -5.250  -0.2481   0.01809   0.01049  -0.0604   0.8279   0.0136
  -5.000  -0.2235   0.01717   0.00941  -0.0596   0.8199   0.0143
  -4.750  -0.1985   0.01637   0.00847  -0.0590   0.8118   0.0150
  -4.500  -0.1736   0.01568   0.00772  -0.0584   0.8040   0.0159
  -4.250  -0.1480   0.01510   0.00704  -0.0579   0.7960   0.0175
  -4.000  -0.1221   0.01462   0.00648  -0.0574   0.7884   0.0203
  -3.750  -0.0960   0.01413   0.00592  -0.0570   0.7806   0.0248
  -3.500  -0.0698   0.01364   0.00536  -0.0565   0.7729   0.0317
  -3.250  -0.0437   0.01313   0.00489  -0.0561   0.7653   0.0483
  -3.000  -0.0180   0.01255   0.00449  -0.0557   0.7575   0.0925
  -2.750   0.0076   0.01202   0.00423  -0.0555   0.7500   0.1662
  -2.500   0.0337   0.01163   0.00404  -0.0552   0.7419   0.2325
  -2.250   0.0597   0.01129   0.00387  -0.0548   0.7343   0.2986
  -2.000   0.0855   0.01094   0.00375  -0.0544   0.7259   0.3733
  -1.750   0.1113   0.01065   0.00364  -0.0540   0.7180   0.4427
  -1.500   0.1368   0.01038   0.00353  -0.0534   0.7095   0.5092
  -1.250   0.1620   0.01011   0.00346  -0.0526   0.7009   0.5796
  -1.000   0.1864   0.00985   0.00341  -0.0516   0.6923   0.6568
  -0.750   0.2103   0.00962   0.00339  -0.0502   0.6832   0.7370
  -0.250   0.2646   0.00939   0.00335  -0.0485   0.6644   0.8808
   0.000   0.3021   0.00937   0.00328  -0.0500   0.6543   0.9299
   0.250   0.3423   0.00938   0.00317  -0.0523   0.6436   0.9631
   0.500   0.3830   0.00939   0.00309  -0.0549   0.6313   0.9867
   0.750   0.4197   0.00943   0.00302  -0.0567   0.6192   1.0000
   1.000   0.4442   0.00951   0.00299  -0.0560   0.6074   1.0000
   1.250   0.4688   0.00960   0.00298  -0.0553   0.5952   1.0000
   1.500   0.4936   0.00970   0.00298  -0.0546   0.5823   1.0000
   1.750   0.5186   0.00981   0.00301  -0.0540   0.5686   1.0000
   2.000   0.5438   0.00994   0.00305  -0.0534   0.5545   1.0000
   2.250   0.5690   0.01007   0.00310  -0.0528   0.5402   1.0000
   2.500   0.5943   0.01022   0.00316  -0.0523   0.5254   1.0000
   2.750   0.6196   0.01038   0.00324  -0.0517   0.5104   1.0000
   3.000   0.6449   0.01056   0.00334  -0.0512   0.4947   1.0000
   3.250   0.6702   0.01075   0.00346  -0.0507   0.4789   1.0000
   3.500   0.6954   0.01096   0.00358  -0.0502   0.4628   1.0000
   3.750   0.7205   0.01119   0.00373  -0.0497   0.4467   1.0000
   4.000   0.7456   0.01143   0.00391  -0.0492   0.4303   1.0000
   4.250   0.7705   0.01168   0.00410  -0.0487   0.4140   1.0000
   4.500   0.7953   0.01195   0.00430  -0.0482   0.3975   1.0000
   4.750   0.8200   0.01224   0.00453  -0.0477   0.3811   1.0000
   5.000   0.8446   0.01253   0.00477  -0.0472   0.3648   1.0000
   5.250   0.8690   0.01284   0.00503  -0.0467   0.3488   1.0000
   5.500   0.8933   0.01317   0.00531  -0.0462   0.3330   1.0000
   5.750   0.9173   0.01351   0.00563  -0.0456   0.3175   1.0000
   6.000   0.9411   0.01388   0.00595  -0.0451   0.3026   1.0000
   6.250   0.9647   0.01426   0.00629  -0.0445   0.2884   1.0000
   6.500   0.9880   0.01466   0.00667  -0.0439   0.2746   1.0000
   6.750   1.0112   0.01505   0.00705  -0.0433   0.2613   1.0000
   7.000   1.0342   0.01547   0.00746  -0.0427   0.2483   1.0000
   7.250   1.0569   0.01589   0.00789  -0.0421   0.2363   1.0000
   7.500   1.0791   0.01635   0.00834  -0.0414   0.2249   1.0000
   7.750   1.1007   0.01684   0.00882  -0.0406   0.2141   1.0000
   8.000   1.1223   0.01732   0.00932  -0.0398   0.2032   1.0000
   8.250   1.1436   0.01781   0.00984  -0.0390   0.1930   1.0000
   8.500   1.1639   0.01835   0.01039  -0.0381   0.1837   1.0000
   8.750   1.1837   0.01891   0.01097  -0.0372   0.1742   1.0000
   9.000   1.2036   0.01945   0.01156  -0.0363   0.1654   1.0000
   9.250   1.2215   0.02008   0.01220  -0.0351   0.1572   1.0000
   9.500   1.2399   0.02067   0.01284  -0.0340   0.1489   1.0000
   9.750   1.2566   0.02133   0.01355  -0.0327   0.1415   1.0000
  10.000   1.2722   0.02201   0.01427  -0.0313   0.1338   1.0000
  10.250   1.2857   0.02270   0.01502  -0.0296   0.1273   1.0000
  10.500   1.2975   0.02348   0.01583  -0.0277   0.1205   1.0000
  10.750   1.3091   0.02430   0.01672  -0.0259   0.1146   1.0000
  11.000   1.3199   0.02521   0.01770  -0.0243   0.1084   1.0000
  11.250   1.3297   0.02623   0.01877  -0.0227   0.1029   1.0000
  11.500   1.3397   0.02729   0.01991  -0.0213   0.0971   1.0000
  11.750   1.3471   0.02857   0.02123  -0.0198   0.0921   1.0000
  12.000   1.3568   0.02977   0.02254  -0.0186   0.0866   1.0000
  12.250   1.3619   0.03133   0.02414  -0.0174   0.0820   1.0000
  12.500   1.3704   0.03274   0.02567  -0.0165   0.0774   1.0000
  12.750   1.3756   0.03445   0.02745  -0.0155   0.0729   1.0000
  13.000   1.3792   0.03637   0.02944  -0.0148   0.0693   1.0000
  13.250   1.3848   0.03820   0.03140  -0.0141   0.0653   1.0000
  13.500   1.3862   0.04048   0.03374  -0.0136   0.0618   1.0000
  13.750   1.3877   0.04283   0.03620  -0.0133   0.0588   1.0000
  14.000   1.3901   0.04520   0.03869  -0.0131   0.0556   1.0000
  14.250   1.3887   0.04805   0.04163  -0.0132   0.0528   1.0000
  14.500   1.3856   0.05120   0.04487  -0.0134   0.0505   1.0000
  14.750   1.3855   0.05410   0.04793  -0.0137   0.0479   1.0000
  15.000   1.3820   0.05753   0.05147  -0.0144   0.0455   1.0000
  15.250   1.3757   0.06149   0.05552  -0.0154   0.0438   1.0000
  15.500   1.3697   0.06556   0.05971  -0.0166   0.0421   1.0000
  15.750   1.3656   0.06954   0.06384  -0.0178   0.0403   1.0000
  16.000   1.3593   0.07399   0.06843  -0.0195   0.0386   1.0000
  16.250   1.3508   0.07890   0.07346  -0.0214   0.0372   1.0000
  16.500   1.3398   0.08436   0.07901  -0.0238   0.0361   1.0000
  16.750   1.3304   0.08969   0.08446  -0.0261   0.0351   1.0000
  17.000   1.3224   0.09497   0.08990  -0.0284   0.0338   1.0000
  17.250   1.3130   0.10056   0.09564  -0.0311   0.0327   1.0000
  17.500   1.3025   0.10649   0.10170  -0.0340   0.0317   1.0000
  17.750   1.2914   0.11265   0.10797  -0.0371   0.0308   1.0000
  18.000   1.2796   0.11904   0.11445  -0.0405   0.0300   1.0000
<< Back to MH 70 11.08% (mh70-il)

Polar data table (+)

Polar graphs


<< Back to MH 70 11.08% (mh70-il)