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

MH 201 13.08% (mh201-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 201 13.08% (mh201-il)
Reynolds number: 100,000
Max Cl/Cd: 52.6 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh201-il-100000-n5.txt
Download as CSV file: xf-mh201-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 201  13.08%                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4133   0.09434   0.08930  -0.0507   1.0000   0.0199
 -10.000  -0.4236   0.08919   0.08423  -0.0521   1.0000   0.0197
  -9.750  -0.4370   0.08345   0.07858  -0.0539   1.0000   0.0191
  -9.500  -0.4624   0.07471   0.06989  -0.0581   1.0000   0.0185
  -9.250  -0.4983   0.06829   0.06346  -0.0601   1.0000   0.0180
  -9.000  -0.5360   0.06466   0.05980  -0.0583   1.0000   0.0178
  -8.500  -0.5833   0.05388   0.04828  -0.0615   0.9873   0.0170
  -8.250  -0.5755   0.04933   0.04332  -0.0640   0.9798   0.0169
  -8.000  -0.5620   0.04538   0.03894  -0.0659   0.9733   0.0169
  -7.750  -0.5477   0.04194   0.03507  -0.0667   0.9664   0.0169
  -7.500  -0.5277   0.03844   0.03101  -0.0678   0.9611   0.0170
  -7.250  -0.5067   0.03580   0.02803  -0.0683   0.9559   0.0172
  -7.000  -0.4839   0.03364   0.02557  -0.0687   0.9506   0.0175
  -6.750  -0.4554   0.03187   0.02361  -0.0700   0.9470   0.0185
  -6.500  -0.4309   0.03031   0.02180  -0.0701   0.9420   0.0193
  -6.250  -0.4049   0.02882   0.01995  -0.0702   0.9370   0.0214
  -6.000  -0.3755   0.02739   0.01847  -0.0712   0.9336   0.0226
  -5.750  -0.3443   0.02607   0.01702  -0.0722   0.9308   0.0240
  -5.500  -0.3239   0.02502   0.01584  -0.0711   0.9240   0.0256
  -5.250  -0.2951   0.02388   0.01464  -0.0719   0.9201   0.0277
  -5.000  -0.2624   0.02291   0.01358  -0.0733   0.9173   0.0333
  -4.750  -0.2398   0.02211   0.01272  -0.0728   0.9110   0.0394
  -4.500  -0.2113   0.02114   0.01181  -0.0735   0.9064   0.0534
  -4.250  -0.1796   0.01982   0.01091  -0.0750   0.9034   0.1145
  -4.000  -0.1486   0.01856   0.01033  -0.0768   0.9005   0.2506
  -3.750  -0.1286   0.01767   0.01010  -0.0763   0.8935   0.3878
  -3.500  -0.1024   0.01708   0.01024  -0.0757   0.8896   0.5417
  -3.250  -0.0725   0.01718   0.01050  -0.0750   0.8868   0.6226
  -3.000  -0.0524   0.01744   0.01070  -0.0730   0.8795   0.6620
  -2.750  -0.0227   0.01762   0.01074  -0.0728   0.8750   0.6929
  -2.500   0.0113   0.01774   0.01071  -0.0734   0.8720   0.7168
  -2.250   0.0340   0.01793   0.01078  -0.0722   0.8653   0.7348
  -2.000   0.0613   0.01806   0.01080  -0.0716   0.8601   0.7500
  -1.750   0.0931   0.01810   0.01073  -0.0717   0.8566   0.7632
  -1.500   0.1142   0.01824   0.01079  -0.0700   0.8497   0.7750
  -1.250   0.1412   0.01828   0.01075  -0.0694   0.8442   0.7872
  -1.000   0.1744   0.01823   0.01059  -0.0700   0.8407   0.7996
  -0.750   0.1922   0.01833   0.01066  -0.0677   0.8325   0.8090
  -0.500   0.2223   0.01825   0.01050  -0.0678   0.8274   0.8177
  -0.250   0.2555   0.01811   0.01029  -0.0685   0.8232   0.8253
   0.000   0.2754   0.01814   0.01029  -0.0670   0.8142   0.8328
   0.250   0.3094   0.01797   0.01005  -0.0678   0.8097   0.8392
   0.500   0.3310   0.01798   0.01004  -0.0666   0.8008   0.8465
   0.750   0.3623   0.01781   0.00983  -0.0669   0.7951   0.8523
   1.000   0.3873   0.01779   0.00978  -0.0665   0.7864   0.8596
   1.250   0.4171   0.01760   0.00958  -0.0664   0.7796   0.8646
   1.500   0.4405   0.01756   0.00954  -0.0655   0.7704   0.8708
   1.750   0.4740   0.01737   0.00932  -0.0664   0.7632   0.8759
   2.000   0.4954   0.01732   0.00930  -0.0650   0.7526   0.8813
   2.250   0.5270   0.01716   0.00912  -0.0656   0.7442   0.8862
   2.500   0.5530   0.01707   0.00904  -0.0651   0.7333   0.8914
   2.750   0.5763   0.01699   0.00900  -0.0641   0.7216   0.8966
   3.000   0.6038   0.01689   0.00891  -0.0640   0.7102   0.9019
   3.250   0.6322   0.01676   0.00879  -0.0639   0.6983   0.9066
   3.500   0.6574   0.01666   0.00872  -0.0632   0.6848   0.9120
   3.750   0.6820   0.01660   0.00869  -0.0626   0.6698   0.9179
   4.000   0.7070   0.01652   0.00865  -0.0619   0.6538   0.9233
   4.250   0.7303   0.01649   0.00865  -0.0610   0.6357   0.9299
   4.500   0.7547   0.01647   0.00865  -0.0603   0.6164   0.9364
   4.750   0.7811   0.01645   0.00863  -0.0599   0.5957   0.9432
   5.000   0.8076   0.01648   0.00865  -0.0597   0.5726   0.9503
   5.250   0.8350   0.01658   0.00870  -0.0596   0.5477   0.9586
   5.500   0.8632   0.01678   0.00887  -0.0599   0.5202   0.9684
   6.000   0.9148   0.01739   0.00933  -0.0599   0.4625   1.0000
   6.250   0.9368   0.01785   0.00970  -0.0593   0.4343   1.0000
   6.500   0.9581   0.01837   0.01011  -0.0587   0.4067   1.0000
   6.750   0.9788   0.01893   0.01059  -0.0580   0.3793   1.0000
   7.000   0.9988   0.01952   0.01111  -0.0572   0.3536   1.0000
   7.250   1.0172   0.02017   0.01168  -0.0562   0.3293   1.0000
   7.500   1.0357   0.02082   0.01229  -0.0552   0.3061   1.0000
   7.750   1.0529   0.02156   0.01295  -0.0541   0.2847   1.0000
   8.000   1.0705   0.02230   0.01366  -0.0530   0.2643   1.0000
   8.250   1.0872   0.02309   0.01444  -0.0519   0.2453   1.0000
   8.500   1.1032   0.02392   0.01524  -0.0506   0.2279   1.0000
   8.750   1.1186   0.02479   0.01610  -0.0494   0.2118   1.0000
   9.000   1.1335   0.02571   0.01701  -0.0481   0.1970   1.0000
   9.250   1.1479   0.02666   0.01799  -0.0468   0.1832   1.0000
   9.500   1.1620   0.02765   0.01901  -0.0455   0.1708   1.0000
   9.750   1.1752   0.02870   0.02009  -0.0442   0.1594   1.0000
  10.000   1.1868   0.02986   0.02124  -0.0427   0.1493   1.0000
  10.250   1.1993   0.03100   0.02245  -0.0414   0.1394   1.0000
  10.500   1.2113   0.03220   0.02375  -0.0402   0.1305   1.0000
  10.750   1.2201   0.03360   0.02514  -0.0387   0.1229   1.0000
  11.000   1.2324   0.03487   0.02655  -0.0376   0.1150   1.0000
  11.250   1.2401   0.03642   0.02809  -0.0363   0.1088   1.0000
  11.500   1.2509   0.03784   0.02969  -0.0352   0.1017   1.0000
  11.750   1.2568   0.03959   0.03144  -0.0339   0.0965   1.0000
  12.000   1.2665   0.04119   0.03324  -0.0329   0.0905   1.0000
  12.250   1.2722   0.04304   0.03517  -0.0319   0.0856   1.0000
  12.500   1.2785   0.04499   0.03722  -0.0309   0.0812   1.0000
  12.750   1.2843   0.04698   0.03938  -0.0301   0.0764   1.0000
  13.000   1.2871   0.04924   0.04168  -0.0294   0.0729   1.0000
  13.250   1.2917   0.05153   0.04415  -0.0287   0.0691   1.0000
  13.500   1.2947   0.05397   0.04676  -0.0282   0.0653   1.0000
  13.750   1.2951   0.05664   0.04952  -0.0279   0.0623   1.0000
  14.000   1.2957   0.05949   0.05250  -0.0276   0.0596   1.0000
  14.250   1.2961   0.06250   0.05575  -0.0275   0.0566   1.0000
  14.500   1.2945   0.06573   0.05913  -0.0278   0.0540   1.0000
  14.750   1.2915   0.06918   0.06267  -0.0283   0.0518   1.0000
  15.000   1.2886   0.07288   0.06650  -0.0289   0.0499   1.0000
  15.250   1.2840   0.07702   0.07091  -0.0298   0.0478   1.0000
  15.500   1.2783   0.08139   0.07548  -0.0311   0.0458   1.0000
  15.750   1.2722   0.08590   0.08013  -0.0327   0.0442   1.0000
  16.000   1.2663   0.09048   0.08481  -0.0345   0.0428   1.0000
  16.250   1.2599   0.09532   0.08975  -0.0364   0.0415   1.0000
  16.500   1.2477   0.10153   0.09626  -0.0393   0.0404   1.0000
  16.750   1.2345   0.10815   0.10313  -0.0427   0.0393   1.0000
  17.000   1.2202   0.11522   0.11042  -0.0466   0.0384   1.0000
  17.250   1.2045   0.12280   0.11820  -0.0511   0.0377   1.0000
  17.500   1.1868   0.13113   0.12673  -0.0562   0.0371   1.0000
  17.750   1.1621   0.14161   0.13742  -0.0629   0.0370   1.0000
<< Back to MH 201 13.08% (mh201-il)

Polar data table (+)

Polar graphs


<< Back to MH 201 13.08% (mh201-il)