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

MH 116 9.84% (mh116-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 116 9.84% (mh116-il)
Reynolds number: 100,000
Max Cl/Cd: 63.01 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh116-il-100000.txt
Download as CSV file: xf-mh116-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 116  9.84%                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3411   0.10974   0.10510  -0.0421   1.0000   0.0790
  -8.750  -0.3574   0.10879   0.10428  -0.0422   1.0000   0.0794
  -8.500  -0.3762   0.10796   0.10358  -0.0410   1.0000   0.0795
  -8.250  -0.3400   0.10049   0.09602  -0.0370   1.0000   0.0824
  -8.000  -0.3428   0.09853   0.09413  -0.0347   1.0000   0.0842
  -7.750  -0.3518   0.09695   0.09263  -0.0323   1.0000   0.0860
  -7.500  -0.3649   0.09567   0.09145  -0.0298   1.0000   0.0874
  -7.250  -0.3813   0.09463   0.09051  -0.0271   1.0000   0.0885
  -7.000  -0.4023   0.09386   0.08984  -0.0241   1.0000   0.0897
  -6.750  -0.4230   0.09275   0.08883  -0.0228   1.0000   0.0910
  -6.500  -0.4472   0.09070   0.08690  -0.0302   1.0000   0.0928
  -6.250  -0.4529   0.08677   0.08301  -0.0326   1.0000   0.0935
  -6.000  -0.4508   0.08421   0.08048  -0.0264   1.0000   0.0948
  -5.750  -0.4498   0.08191   0.07822  -0.0236   1.0000   0.0966
  -5.500  -0.4281   0.07771   0.07398  -0.0287   0.9955   0.1016
  -5.250  -0.3967   0.07038   0.06651  -0.0426   0.9879   0.1091
  -5.000  -0.3677   0.06659   0.06267  -0.0464   0.9828   0.1155
  -4.750  -0.3129   0.04541   0.04022  -0.0682   0.9783   0.0512
  -4.500  -0.2765   0.03959   0.03387  -0.0733   0.9739   0.0480
  -4.250  -0.2332   0.03470   0.02815  -0.0782   0.9705   0.0490
  -4.000  -0.1962   0.03110   0.02377  -0.0806   0.9659   0.0502
  -3.750  -0.1579   0.02841   0.02035  -0.0824   0.9612   0.0523
  -3.500  -0.1166   0.02661   0.01817  -0.0850   0.9573   0.0660
  -3.250  -0.0851   0.02508   0.01667  -0.0860   0.9515   0.0876
  -3.000  -0.0485   0.02395   0.01553  -0.0879   0.9462   0.1271
  -2.750  -0.0095   0.02325   0.01487  -0.0902   0.9416   0.1780
  -2.500   0.0188   0.02276   0.01457  -0.0908   0.9343   0.2260
  -2.250   0.0586   0.02226   0.01429  -0.0934   0.9298   0.2958
  -2.000   0.0844   0.02189   0.01418  -0.0934   0.9222   0.3674
  -1.750   0.1199   0.02140   0.01414  -0.0949   0.9171   0.4795
  -1.500   0.1443   0.02101   0.01428  -0.0941   0.9101   0.6211
  -1.250   0.1653   0.02040   0.01437  -0.0911   0.9042   0.8595
  -1.000   0.2082   0.02046   0.01415  -0.0944   0.8977   1.0000
  -0.750   0.2429   0.02071   0.01410  -0.0961   0.8908   1.0000
  -0.500   0.2763   0.02099   0.01415  -0.0975   0.8840   1.0000
  -0.250   0.3098   0.02123   0.01420  -0.0988   0.8769   1.0000
   0.000   0.3419   0.02151   0.01430  -0.0999   0.8699   1.0000
   0.250   0.3760   0.02171   0.01437  -0.1012   0.8629   1.0000
   0.500   0.4064   0.02200   0.01454  -0.1019   0.8554   1.0000
   0.750   0.4429   0.02211   0.01454  -0.1035   0.8488   1.0000
   1.000   0.4713   0.02240   0.01476  -0.1038   0.8406   1.0000
   1.250   0.5114   0.02236   0.01466  -0.1059   0.8346   1.0000
   1.500   0.5387   0.02264   0.01490  -0.1059   0.8259   1.0000
   1.750   0.5817   0.02246   0.01468  -0.1083   0.8205   1.0000
   2.000   0.6077   0.02272   0.01493  -0.1080   0.8111   1.0000
   2.250   0.6506   0.02239   0.01460  -0.1100   0.8061   1.0000
   2.500   0.6749   0.02266   0.01489  -0.1094   0.7958   1.0000
   2.750   0.7203   0.02212   0.01437  -0.1116   0.7914   1.0000
   3.000   0.7438   0.02235   0.01462  -0.1107   0.7803   1.0000
   3.250   0.7742   0.02229   0.01461  -0.1106   0.7711   1.0000
   3.500   0.8143   0.02176   0.01416  -0.1118   0.7643   1.0000
   3.750   0.8408   0.02178   0.01424  -0.1111   0.7532   1.0000
   4.000   0.8717   0.02157   0.01410  -0.1109   0.7430   1.0000
   4.250   0.9129   0.02084   0.01346  -0.1120   0.7352   1.0000
   4.500   0.9406   0.02067   0.01337  -0.1112   0.7225   1.0000
   4.750   0.9695   0.02042   0.01320  -0.1106   0.7094   1.0000
   5.000   0.9992   0.02010   0.01296  -0.1100   0.6956   1.0000
   5.250   1.0295   0.01972   0.01270  -0.1094   0.6809   1.0000
   5.500   1.0590   0.01938   0.01243  -0.1086   0.6648   1.0000
   5.750   1.0820   0.01930   0.01245  -0.1071   0.6452   1.0000
   6.000   1.1101   0.01900   0.01220  -0.1061   0.6255   1.0000
   6.250   1.1328   0.01892   0.01226  -0.1045   0.6021   1.0000
   6.500   1.1559   0.01884   0.01223  -0.1028   0.5763   1.0000
   6.750   1.1768   0.01886   0.01229  -0.1009   0.5465   1.0000
   7.000   1.1966   0.01899   0.01238  -0.0988   0.5129   1.0000
   7.250   1.2123   0.01933   0.01269  -0.0962   0.4732   1.0000
   7.500   1.2260   0.01988   0.01310  -0.0934   0.4297   1.0000
   7.750   1.2364   0.02069   0.01372  -0.0902   0.3827   1.0000
   8.000   1.2445   0.02175   0.01461  -0.0869   0.3366   1.0000
   8.250   1.2505   0.02298   0.01560  -0.0835   0.2932   1.0000
   8.500   1.2555   0.02433   0.01674  -0.0801   0.2542   1.0000
   8.750   1.2580   0.02574   0.01791  -0.0764   0.2213   1.0000
   9.000   1.2606   0.02722   0.01923  -0.0729   0.1914   1.0000
   9.250   1.2627   0.02879   0.02065  -0.0696   0.1647   1.0000
   9.500   1.2645   0.03050   0.02225  -0.0664   0.1403   1.0000
   9.750   1.2666   0.03236   0.02408  -0.0634   0.1174   1.0000
  10.000   1.2674   0.03454   0.02613  -0.0606   0.0973   1.0000
  10.250   1.2698   0.03683   0.02840  -0.0579   0.0795   1.0000
  10.500   1.2727   0.03919   0.03072  -0.0556   0.0658   1.0000
  10.750   1.2784   0.04170   0.03326  -0.0535   0.0546   1.0000
  11.000   1.2850   0.04437   0.03608  -0.0517   0.0456   1.0000
  11.250   1.3018   0.04778   0.03946  -0.0506   0.0389   1.0000
  11.500   1.3046   0.05012   0.04213  -0.0486   0.0347   1.0000
  11.750   1.3110   0.05286   0.04495  -0.0472   0.0314   1.0000
  12.000   1.3275   0.05841   0.05078  -0.0465   0.0295   1.0000
  12.250   1.3242   0.06203   0.05478  -0.0446   0.0291   1.0000
  12.500   1.3159   0.06602   0.05915  -0.0429   0.0287   1.0000
  12.750   1.3043   0.07026   0.06374  -0.0416   0.0285   1.0000
  13.000   1.2903   0.07483   0.06863  -0.0408   0.0285   1.0000
  13.250   1.2741   0.07973   0.07383  -0.0407   0.0285   1.0000
  13.500   1.2563   0.08505   0.07943  -0.0412   0.0285   1.0000
  13.750   1.2370   0.09078   0.08541  -0.0425   0.0286   1.0000
  14.000   1.2178   0.09697   0.09183  -0.0445   0.0288   1.0000
  14.250   1.1979   0.10362   0.09869  -0.0473   0.0290   1.0000
  14.500   1.1787   0.11076   0.10600  -0.0507   0.0293   1.0000
  14.750   1.1603   0.11840   0.11379  -0.0547   0.0296   1.0000
  15.000   1.1441   0.12575   0.12133  -0.0594   0.0300   1.0000
  15.250   1.0675   0.15292   0.14884  -0.0808   0.0355   1.0000
  15.500   1.0523   0.16474   0.16062  -0.0874   0.0377   1.0000
  15.750   1.0465   0.17325   0.16908  -0.0918   0.0386   1.0000
  16.000   1.0442   0.18052   0.17631  -0.0954   0.0392   1.0000
  16.250   0.8404   0.19688   0.19327  -0.0925   0.1000   1.0000
  16.500   0.8303   0.20124   0.19762  -0.0963   0.0997   1.0000
<< Back to MH 116 9.84% (mh116-il)

Polar data table (+)

Polar graphs


<< Back to MH 116 9.84% (mh116-il)