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MH 116 9.84% (mh116-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: MH 116 9.84% (mh116-il)
Reynolds number: 1,000,000
Max Cl/Cd: 130.96 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh116-il-1000000-n5.txt
Download as CSV file: xf-mh116-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3275   0.02716   0.02461  -0.1192   0.8943   0.0031
  -8.000  -0.3202   0.02285   0.01980  -0.1198   0.8806   0.0030
  -7.750  -0.3052   0.01990   0.01640  -0.1198   0.8700   0.0030
  -7.500  -0.2860   0.01779   0.01393  -0.1195   0.8606   0.0030
  -7.250  -0.2642   0.01613   0.01196  -0.1193   0.8522   0.0030
  -7.000  -0.2412   0.01474   0.01029  -0.1189   0.8444   0.0029
  -6.750  -0.2169   0.01361   0.00894  -0.1187   0.8365   0.0029
  -6.500  -0.1921   0.01264   0.00775  -0.1184   0.8291   0.0029
  -6.250  -0.1664   0.01187   0.00681  -0.1182   0.8217   0.0029
  -6.000  -0.1405   0.01118   0.00596  -0.1180   0.8148   0.0029
  -5.750  -0.1141   0.01059   0.00524  -0.1179   0.8076   0.0029
  -5.500  -0.0874   0.01009   0.00461  -0.1177   0.8010   0.0030
  -5.250  -0.0604   0.00966   0.00406  -0.1176   0.7940   0.0030
  -5.000  -0.0332   0.00929   0.00360  -0.1175   0.7876   0.0030
  -4.750  -0.0058   0.00896   0.00318  -0.1174   0.7807   0.0031
  -4.500   0.0216   0.00870   0.00283  -0.1174   0.7743   0.0032
  -4.250   0.0493   0.00847   0.00252  -0.1173   0.7675   0.0033
  -4.000   0.0769   0.00825   0.00221  -0.1172   0.7612   0.0036
  -3.750   0.1047   0.00805   0.00196  -0.1172   0.7544   0.0048
  -3.500   0.1322   0.00780   0.00173  -0.1172   0.7481   0.0163
  -3.250   0.1599   0.00759   0.00157  -0.1172   0.7413   0.0327
  -3.000   0.1874   0.00742   0.00143  -0.1172   0.7348   0.0522
  -2.750   0.2152   0.00724   0.00132  -0.1173   0.7282   0.0760
  -2.250   0.2706   0.00694   0.00116  -0.1174   0.7147   0.1343
  -2.000   0.2982   0.00684   0.00109  -0.1174   0.7078   0.1615
  -1.750   0.3262   0.00676   0.00104  -0.1174   0.7006   0.1807
  -1.500   0.3538   0.00670   0.00100  -0.1174   0.6931   0.2060
  -1.250   0.3816   0.00663   0.00097  -0.1174   0.6848   0.2308
  -1.000   0.4092   0.00658   0.00094  -0.1174   0.6764   0.2547
  -0.750   0.4368   0.00652   0.00093  -0.1174   0.6674   0.2876
  -0.500   0.4644   0.00645   0.00093  -0.1174   0.6587   0.3233
  -0.250   0.4919   0.00641   0.00094  -0.1174   0.6500   0.3579
   0.000   0.5194   0.00635   0.00095  -0.1174   0.6406   0.3974
   0.250   0.5469   0.00630   0.00097  -0.1174   0.6314   0.4399
   0.500   0.5741   0.00626   0.00101  -0.1173   0.6216   0.4837
   0.750   0.6013   0.00621   0.00106  -0.1173   0.6111   0.5346
   1.000   0.6285   0.00616   0.00111  -0.1172   0.6007   0.5874
   1.250   0.6555   0.00612   0.00118  -0.1171   0.5898   0.6426
   1.500   0.6820   0.00609   0.00126  -0.1169   0.5780   0.7014
   1.750   0.7081   0.00605   0.00135  -0.1165   0.5651   0.7628
   2.000   0.7331   0.00603   0.00145  -0.1159   0.5513   0.8237
   2.250   0.7559   0.00601   0.00154  -0.1147   0.5365   0.8882
   2.750   0.8093   0.00618   0.00169  -0.1142   0.4992   1.0000
   3.000   0.8350   0.00638   0.00181  -0.1139   0.4761   1.0000
   3.250   0.8604   0.00662   0.00195  -0.1135   0.4516   1.0000
   3.500   0.8854   0.00689   0.00210  -0.1130   0.4244   1.0000
   3.750   0.9099   0.00720   0.00228  -0.1125   0.3948   1.0000
   4.000   0.9344   0.00751   0.00247  -0.1120   0.3672   1.0000
   4.250   0.9583   0.00786   0.00269  -0.1114   0.3367   1.0000
   4.500   0.9820   0.00822   0.00292  -0.1108   0.3071   1.0000
   4.750   1.0060   0.00856   0.00314  -0.1102   0.2816   1.0000
   5.000   1.0296   0.00893   0.00340  -0.1095   0.2554   1.0000
   5.250   1.0530   0.00930   0.00367  -0.1089   0.2301   1.0000
   5.500   1.0759   0.00971   0.00395  -0.1081   0.2042   1.0000
   5.750   1.0988   0.01010   0.00424  -0.1074   0.1814   1.0000
   6.000   1.1220   0.01046   0.00453  -0.1067   0.1634   1.0000
   6.250   1.1422   0.01104   0.00494  -0.1055   0.1299   1.0000
   6.500   1.1613   0.01170   0.00540  -0.1042   0.0951   1.0000
   6.750   1.1811   0.01227   0.00583  -0.1030   0.0707   1.0000
   7.000   1.2013   0.01280   0.00626  -0.1018   0.0530   1.0000
   7.250   1.2224   0.01325   0.00665  -0.1008   0.0423   1.0000
   7.500   1.2422   0.01377   0.00711  -0.0996   0.0304   1.0000
   7.750   1.2597   0.01443   0.00769  -0.0980   0.0160   1.0000
   8.000   1.2784   0.01498   0.00821  -0.0966   0.0100   1.0000
   8.250   1.2969   0.01552   0.00873  -0.0951   0.0059   1.0000
   8.500   1.3136   0.01607   0.00929  -0.0933   0.0027   1.0000
   8.750   1.3288   0.01663   0.00987  -0.0913   0.0014   1.0000
   9.000   1.3452   0.01710   0.01039  -0.0894   0.0013   1.0000
   9.250   1.3597   0.01770   0.01103  -0.0873   0.0010   1.0000
   9.500   1.3728   0.01840   0.01182  -0.0850   0.0008   1.0000
   9.750   1.3871   0.01901   0.01251  -0.0830   0.0007   1.0000
  10.000   1.4009   0.01968   0.01323  -0.0810   0.0007   1.0000
  10.250   1.4139   0.02041   0.01403  -0.0790   0.0007   1.0000
  10.500   1.4260   0.02121   0.01491  -0.0769   0.0007   1.0000
  10.750   1.4376   0.02207   0.01585  -0.0748   0.0007   1.0000
  11.000   1.4480   0.02303   0.01689  -0.0727   0.0007   1.0000
  11.250   1.4584   0.02402   0.01795  -0.0707   0.0007   1.0000
  11.500   1.4671   0.02516   0.01919  -0.0687   0.0006   1.0000
  11.750   1.4754   0.02638   0.02050  -0.0666   0.0006   1.0000
  12.000   1.4823   0.02774   0.02196  -0.0646   0.0006   1.0000
  12.250   1.4894   0.02913   0.02345  -0.0628   0.0006   1.0000
  12.500   1.4938   0.03080   0.02524  -0.0609   0.0006   1.0000
  12.750   1.4982   0.03254   0.02708  -0.0592   0.0006   1.0000
  13.000   1.5016   0.03442   0.02907  -0.0575   0.0006   1.0000
  13.250   1.5039   0.03648   0.03125  -0.0560   0.0006   1.0000
  13.500   1.5048   0.03876   0.03365  -0.0547   0.0006   1.0000
  13.750   1.5038   0.04134   0.03636  -0.0534   0.0006   1.0000
  14.000   1.5037   0.04393   0.03906  -0.0525   0.0006   1.0000
  14.250   1.5013   0.04688   0.04214  -0.0517   0.0006   1.0000
  14.500   1.4993   0.04991   0.04530  -0.0512   0.0006   1.0000
  14.750   1.4946   0.05345   0.04897  -0.0510   0.0006   1.0000
  15.000   1.4899   0.05713   0.05279  -0.0511   0.0006   1.0000
  15.250   1.4806   0.06166   0.05748  -0.0515   0.0006   1.0000
  15.500   1.4745   0.06597   0.06192  -0.0523   0.0006   1.0000
  15.750   1.4660   0.07082   0.06691  -0.0534   0.0006   1.0000
  16.000   1.4561   0.07614   0.07238  -0.0550   0.0006   1.0000
  16.250   1.4449   0.08194   0.07833  -0.0570   0.0006   1.0000
  16.500   1.4328   0.08817   0.08471  -0.0595   0.0006   1.0000
  16.750   1.4196   0.09485   0.09154  -0.0624   0.0006   1.0000
  17.000   1.4048   0.10214   0.09900  -0.0658   0.0006   1.0000
  17.250   1.3901   0.10970   0.10671  -0.0696   0.0006   1.0000
  17.500   1.3752   0.11751   0.11467  -0.0737   0.0006   1.0000
  17.750   1.3596   0.12572   0.12302  -0.0782   0.0006   1.0000
  18.000   1.3439   0.13414   0.13157  -0.0830   0.0006   1.0000
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