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MH 116 9.84% (mh116-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: MH 116 9.84% (mh116-il)
Reynolds number: 200,000
Max Cl/Cd: 89.47 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh116-il-200000.txt
Download as CSV file: xf-mh116-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3578   0.10032   0.09718  -0.0387   1.0000   0.0407
  -8.250  -0.3733   0.09914   0.09609  -0.0362   1.0000   0.0408
  -8.000  -0.3899   0.09810   0.09513  -0.0334   1.0000   0.0408
  -7.750  -0.3830   0.09403   0.09108  -0.0389   0.9957   0.0409
  -7.500  -0.3745   0.08743   0.08451  -0.0408   0.9925   0.0421
  -7.250  -0.3554   0.08412   0.08119  -0.0424   0.9883   0.0434
  -7.000  -0.3338   0.08003   0.07707  -0.0476   0.9836   0.0451
  -6.750  -0.3144   0.07519   0.07221  -0.0546   0.9758   0.0469
  -6.500  -0.2840   0.06776   0.06474  -0.0692   0.9698   0.0509
  -6.250  -0.2592   0.05565   0.05227  -0.0894   0.9584   0.0543
  -6.000  -0.2319   0.05222   0.04888  -0.0920   0.9562   0.0558
  -5.750  -0.2125   0.03620   0.03175  -0.1016   0.9458   0.0311
  -5.500  -0.1784   0.02800   0.02261  -0.1059   0.9432   0.0226
  -5.250  -0.1513   0.02598   0.02006  -0.1059   0.9360   0.0212
  -5.000  -0.1155   0.02330   0.01691  -0.1079   0.9328   0.0208
  -4.750  -0.0770   0.02042   0.01358  -0.1103   0.9308   0.0213
  -4.500  -0.0376   0.01807   0.01104  -0.1127   0.9293   0.0231
  -4.250  -0.0124   0.01716   0.01005  -0.1122   0.9217   0.0272
  -4.000   0.0252   0.01582   0.00867  -0.1142   0.9187   0.0497
  -3.750   0.0641   0.01495   0.00792  -0.1165   0.9163   0.0982
  -3.500   0.0918   0.01449   0.00748  -0.1166   0.9096   0.1333
  -3.250   0.1259   0.01393   0.00703  -0.1179   0.9053   0.1747
  -3.000   0.1626   0.01337   0.00662  -0.1197   0.9023   0.2258
  -2.750   0.1887   0.01308   0.00642  -0.1195   0.8949   0.2758
  -2.500   0.2213   0.01262   0.00615  -0.1205   0.8904   0.3394
  -2.250   0.2530   0.01221   0.00594  -0.1212   0.8859   0.4122
  -2.000   0.2784   0.01191   0.00588  -0.1207   0.8785   0.4922
  -1.750   0.3092   0.01145   0.00571  -0.1210   0.8744   0.5942
  -1.500   0.3301   0.01121   0.00578  -0.1192   0.8662   0.6922
  -1.250   0.3539   0.01086   0.00568  -0.1174   0.8612   0.7991
  -1.000   0.3749   0.01068   0.00565  -0.1150   0.8538   0.9076
  -0.750   0.4243   0.01046   0.00532  -0.1192   0.8493   1.0000
  -0.500   0.4525   0.01049   0.00522  -0.1193   0.8428   1.0000
  -0.250   0.4801   0.01053   0.00514  -0.1192   0.8354   1.0000
   0.000   0.5080   0.01058   0.00507  -0.1191   0.8285   1.0000
   0.250   0.5358   0.01061   0.00501  -0.1190   0.8212   1.0000
   0.500   0.5629   0.01068   0.00500  -0.1188   0.8135   1.0000
   0.750   0.5914   0.01069   0.00493  -0.1187   0.8063   1.0000
   1.000   0.6176   0.01078   0.00497  -0.1183   0.7978   1.0000
   1.250   0.6471   0.01078   0.00489  -0.1184   0.7911   1.0000
   1.500   0.6724   0.01089   0.00497  -0.1179   0.7818   1.0000
   1.750   0.7006   0.01093   0.00495  -0.1178   0.7742   1.0000
   2.000   0.7274   0.01099   0.00500  -0.1174   0.7653   1.0000
   2.250   0.7537   0.01108   0.00507  -0.1170   0.7561   1.0000
   2.500   0.7826   0.01111   0.00503  -0.1170   0.7483   1.0000
   2.750   0.8081   0.01119   0.00513  -0.1164   0.7379   1.0000
   3.000   0.8342   0.01128   0.00524  -0.1159   0.7278   1.0000
   3.250   0.8614   0.01133   0.00528  -0.1156   0.7181   1.0000
   3.500   0.8886   0.01139   0.00530  -0.1152   0.7077   1.0000
   3.750   0.9138   0.01147   0.00543  -0.1146   0.6956   1.0000
   4.000   0.9393   0.01154   0.00553  -0.1139   0.6831   1.0000
   4.250   0.9647   0.01162   0.00562  -0.1133   0.6699   1.0000
   4.500   0.9899   0.01171   0.00572  -0.1126   0.6558   1.0000
   4.750   1.0149   0.01180   0.00583  -0.1118   0.6409   1.0000
   5.000   1.0397   0.01191   0.00597  -0.1110   0.6249   1.0000
   5.250   1.0634   0.01205   0.00614  -0.1101   0.6068   1.0000
   5.500   1.0866   0.01220   0.00632  -0.1090   0.5866   1.0000
   5.750   1.1092   0.01240   0.00651  -0.1079   0.5642   1.0000
   6.000   1.1309   0.01264   0.00673  -0.1066   0.5392   1.0000
   6.250   1.1514   0.01293   0.00703  -0.1051   0.5098   1.0000
   6.500   1.1706   0.01332   0.00735  -0.1034   0.4759   1.0000
   6.750   1.1879   0.01382   0.00774  -0.1014   0.4372   1.0000
   7.000   1.2032   0.01446   0.00822  -0.0992   0.3953   1.0000
   7.250   1.2168   0.01522   0.00881  -0.0968   0.3525   1.0000
   7.500   1.2292   0.01606   0.00948  -0.0943   0.3106   1.0000
   7.750   1.2401   0.01700   0.01022  -0.0917   0.2685   1.0000
   8.000   1.2497   0.01800   0.01107  -0.0889   0.2283   1.0000
   8.250   1.2574   0.01904   0.01192  -0.0859   0.1936   1.0000
   8.500   1.2654   0.02005   0.01281  -0.0829   0.1642   1.0000
   8.750   1.2728   0.02115   0.01379  -0.0800   0.1394   1.0000
   9.000   1.2813   0.02225   0.01482  -0.0773   0.1159   1.0000
   9.250   1.2886   0.02347   0.01598  -0.0746   0.0951   1.0000
   9.500   1.2923   0.02498   0.01735  -0.0717   0.0746   1.0000
   9.750   1.2968   0.02655   0.01884  -0.0690   0.0534   1.0000
  10.000   1.2966   0.02854   0.02076  -0.0659   0.0385   1.0000
  10.250   1.2968   0.03062   0.02285  -0.0631   0.0279   1.0000
  10.500   1.2925   0.03316   0.02542  -0.0601   0.0213   1.0000
  10.750   1.2986   0.03493   0.02735  -0.0582   0.0170   1.0000
  11.000   1.2945   0.03767   0.03014  -0.0560   0.0144   1.0000
  11.250   1.2938   0.04038   0.03299  -0.0539   0.0135   1.0000
  11.500   1.2981   0.04270   0.03548  -0.0523   0.0125   1.0000
  11.750   1.3022   0.04521   0.03814  -0.0507   0.0118   1.0000
  12.000   1.3066   0.04777   0.04086  -0.0494   0.0112   1.0000
  12.250   1.3113   0.05044   0.04369  -0.0482   0.0108   1.0000
  12.500   1.3143   0.05333   0.04673  -0.0471   0.0104   1.0000
  12.750   1.3167   0.05645   0.05004  -0.0462   0.0101   1.0000
  13.000   1.3174   0.05987   0.05367  -0.0453   0.0100   1.0000
  13.250   1.3155   0.06364   0.05768  -0.0447   0.0099   1.0000
  13.500   1.3103   0.06781   0.06212  -0.0444   0.0099   1.0000
  13.750   1.3022   0.07241   0.06698  -0.0445   0.0099   1.0000
  14.000   1.2915   0.07744   0.07230  -0.0451   0.0100   1.0000
  14.250   1.2779   0.08308   0.07822  -0.0463   0.0101   1.0000
  14.500   1.2622   0.08934   0.08477  -0.0482   0.0102   1.0000
  14.750   1.2448   0.09621   0.09191  -0.0508   0.0104   1.0000
  15.000   1.2252   0.10393   0.09990  -0.0545   0.0105   1.0000
  15.250   1.2042   0.11245   0.10867  -0.0592   0.0107   1.0000
  15.500   1.1825   0.12182   0.11829  -0.0649   0.0109   1.0000
  15.750   1.1608   0.13197   0.12864  -0.0715   0.0111   1.0000
  16.000   1.1389   0.14314   0.14000  -0.0791   0.0114   1.0000
  16.250   1.1155   0.15596   0.15297  -0.0877   0.0117   1.0000
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