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MH 116 9.84% (mh116-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: MH 116 9.84% (mh116-il)
Reynolds number: 200,000
Max Cl/Cd: 86.09 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh116-il-200000-n5.txt
Download as CSV file: xf-mh116-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3294   0.09991   0.09646  -0.0406   1.0000   0.0124
  -9.000  -0.3338   0.09719   0.09380  -0.0400   1.0000   0.0120
  -8.750  -0.3384   0.09440   0.09107  -0.0396   0.9996   0.0116
  -8.500  -0.3268   0.08910   0.08578  -0.0448   0.9954   0.0110
  -8.250  -0.3188   0.08303   0.07974  -0.0505   0.9893   0.0103
  -8.000  -0.3152   0.07425   0.07100  -0.0588   0.9812   0.0093
  -7.750  -0.3066   0.06865   0.06540  -0.0649   0.9713   0.0091
  -7.500  -0.2957   0.06178   0.05854  -0.0742   0.9604   0.0089
  -7.250  -0.2801   0.05141   0.04808  -0.0890   0.9502   0.0087
  -7.000  -0.2644   0.03703   0.03309  -0.1044   0.9405   0.0083
  -6.750  -0.2455   0.03038   0.02574  -0.1094   0.9319   0.0082
  -6.500  -0.2213   0.02596   0.02063  -0.1118   0.9256   0.0081
  -6.250  -0.1951   0.02306   0.01720  -0.1129   0.9193   0.0082
  -6.000  -0.1643   0.02072   0.01439  -0.1144   0.9153   0.0083
  -5.750  -0.1390   0.01912   0.01246  -0.1143   0.9079   0.0085
  -5.500  -0.1088   0.01772   0.01076  -0.1150   0.9030   0.0089
  -5.250  -0.0813   0.01654   0.00938  -0.1152   0.8966   0.0093
  -5.000  -0.0526   0.01554   0.00820  -0.1157   0.8907   0.0103
  -4.750  -0.0231   0.01479   0.00730  -0.1161   0.8851   0.0123
  -4.500   0.0045   0.01413   0.00655  -0.1161   0.8783   0.0169
  -4.250   0.0346   0.01338   0.00577  -0.1166   0.8732   0.0322
  -4.000   0.0609   0.01288   0.00537  -0.1166   0.8656   0.0604
  -3.750   0.0906   0.01248   0.00496  -0.1170   0.8603   0.0852
  -3.500   0.1174   0.01219   0.00467  -0.1168   0.8528   0.1092
  -3.250   0.1463   0.01189   0.00439  -0.1171   0.8471   0.1371
  -3.000   0.1733   0.01164   0.00418  -0.1170   0.8399   0.1691
  -2.750   0.2017   0.01141   0.00395  -0.1171   0.8338   0.2022
  -2.500   0.2289   0.01120   0.00380  -0.1171   0.8269   0.2382
  -2.250   0.2568   0.01101   0.00364  -0.1171   0.8205   0.2763
  -2.000   0.2842   0.01082   0.00353  -0.1171   0.8139   0.3199
  -1.750   0.3115   0.01062   0.00343  -0.1170   0.8072   0.3702
  -1.500   0.3386   0.01044   0.00336  -0.1169   0.8006   0.4260
  -1.250   0.3654   0.01025   0.00332  -0.1167   0.7937   0.4885
  -1.000   0.3918   0.01006   0.00331  -0.1163   0.7872   0.5574
  -0.750   0.4171   0.00987   0.00330  -0.1157   0.7801   0.6315
  -0.500   0.4414   0.00969   0.00332  -0.1146   0.7735   0.7097
  -0.250   0.4636   0.00952   0.00334  -0.1130   0.7661   0.7904
   0.000   0.4866   0.00938   0.00331  -0.1114   0.7593   0.8762
   0.250   0.5258   0.00925   0.00319  -0.1135   0.7520   0.9928
   0.500   0.5532   0.00933   0.00318  -0.1134   0.7442   1.0000
   0.750   0.5806   0.00940   0.00316  -0.1133   0.7363   1.0000
   1.000   0.6073   0.00949   0.00320  -0.1131   0.7275   1.0000
   1.250   0.6346   0.00958   0.00320  -0.1129   0.7195   1.0000
   1.500   0.6613   0.00967   0.00325  -0.1127   0.7103   1.0000
   1.750   0.6880   0.00977   0.00330  -0.1124   0.7012   1.0000
   2.000   0.7150   0.00988   0.00336  -0.1122   0.6925   1.0000
   2.250   0.7414   0.00999   0.00344  -0.1119   0.6823   1.0000
   2.500   0.7678   0.01010   0.00353  -0.1116   0.6721   1.0000
   2.750   0.7942   0.01022   0.00362  -0.1113   0.6619   1.0000
   3.000   0.8205   0.01035   0.00374  -0.1109   0.6510   1.0000
   3.250   0.8463   0.01048   0.00386  -0.1105   0.6390   1.0000
   3.500   0.8720   0.01063   0.00400  -0.1101   0.6261   1.0000
   3.750   0.8974   0.01078   0.00414  -0.1095   0.6123   1.0000
   4.000   0.9225   0.01095   0.00431  -0.1090   0.5973   1.0000
   4.250   0.9472   0.01114   0.00448  -0.1083   0.5808   1.0000
   4.500   0.9715   0.01134   0.00468  -0.1076   0.5620   1.0000
   4.750   0.9953   0.01157   0.00488  -0.1068   0.5417   1.0000
   5.000   1.0185   0.01183   0.00513  -0.1059   0.5188   1.0000
   5.250   1.0408   0.01214   0.00539  -0.1049   0.4929   1.0000
   5.500   1.0622   0.01251   0.00568  -0.1037   0.4636   1.0000
   5.750   1.0822   0.01296   0.00602  -0.1023   0.4306   1.0000
   6.000   1.1009   0.01348   0.00641  -0.1008   0.3947   1.0000
   6.250   1.1187   0.01408   0.00690  -0.0991   0.3598   1.0000
   6.500   1.1361   0.01470   0.00741  -0.0974   0.3251   1.0000
   6.750   1.1529   0.01537   0.00797  -0.0957   0.2921   1.0000
   7.000   1.1691   0.01608   0.00856  -0.0939   0.2597   1.0000
   7.250   1.1849   0.01681   0.00919  -0.0921   0.2290   1.0000
   7.500   1.2001   0.01757   0.00986  -0.0902   0.2007   1.0000
   7.750   1.2146   0.01836   0.01056  -0.0883   0.1745   1.0000
   8.000   1.2267   0.01920   0.01134  -0.0860   0.1485   1.0000
   8.250   1.2378   0.02010   0.01213  -0.0835   0.1251   1.0000
   8.500   1.2497   0.02097   0.01294  -0.0813   0.1049   1.0000
   8.750   1.2611   0.02189   0.01382  -0.0790   0.0885   1.0000
   9.000   1.2722   0.02285   0.01476  -0.0768   0.0733   1.0000
   9.250   1.2831   0.02385   0.01576  -0.0746   0.0601   1.0000
   9.500   1.2926   0.02497   0.01686  -0.0724   0.0468   1.0000
   9.750   1.3003   0.02627   0.01810  -0.0702   0.0336   1.0000
  10.000   1.3071   0.02767   0.01947  -0.0679   0.0237   1.0000
  10.250   1.3136   0.02915   0.02098  -0.0657   0.0171   1.0000
  10.500   1.3186   0.03082   0.02272  -0.0635   0.0126   1.0000
  10.750   1.3235   0.03254   0.02452  -0.0615   0.0098   1.0000
  11.000   1.3285   0.03431   0.02641  -0.0596   0.0075   1.0000
  11.250   1.3341   0.03606   0.02829  -0.0580   0.0065   1.0000
  11.500   1.3345   0.03838   0.03073  -0.0561   0.0056   1.0000
  11.750   1.3372   0.04055   0.03307  -0.0546   0.0052   1.0000
  12.000   1.3385   0.04292   0.03563  -0.0532   0.0047   1.0000
  12.250   1.3393   0.04543   0.03831  -0.0521   0.0045   1.0000
  12.500   1.3388   0.04818   0.04123  -0.0511   0.0042   1.0000
  12.750   1.3378   0.05107   0.04429  -0.0503   0.0040   1.0000
  13.000   1.3358   0.05418   0.04757  -0.0497   0.0038   1.0000
  13.250   1.3328   0.05752   0.05107  -0.0494   0.0037   1.0000
  13.500   1.3288   0.06115   0.05486  -0.0494   0.0036   1.0000
  13.750   1.3231   0.06517   0.05905  -0.0497   0.0035   1.0000
  14.000   1.3170   0.06940   0.06345  -0.0502   0.0034   1.0000
  14.250   1.3090   0.07412   0.06839  -0.0512   0.0033   1.0000
  14.500   1.3015   0.07897   0.07342  -0.0524   0.0033   1.0000
  14.750   1.2915   0.08441   0.07905  -0.0540   0.0033   1.0000
  15.000   1.2822   0.09000   0.08482  -0.0560   0.0032   1.0000
  15.250   1.2716   0.09605   0.09106  -0.0583   0.0032   1.0000
  15.500   1.2621   0.10212   0.09731  -0.0610   0.0032   1.0000
  15.750   1.2519   0.10857   0.10395  -0.0640   0.0032   1.0000
  16.000   1.2413   0.11536   0.11093  -0.0675   0.0032   1.0000
  16.250   1.2304   0.12245   0.11820  -0.0713   0.0032   1.0000
  16.500   1.2192   0.12986   0.12579  -0.0756   0.0032   1.0000
  16.750   1.2079   0.13750   0.13359  -0.0800   0.0032   1.0000
  17.000   1.1967   0.14544   0.14170  -0.0849   0.0032   1.0000
  17.250   1.1854   0.15366   0.15007  -0.0900   0.0032   1.0000
  17.500   1.1754   0.16183   0.15839  -0.0951   0.0032   1.0000
  17.750   1.1653   0.17044   0.16713  -0.1005   0.0033   1.0000
  18.000   1.1546   0.17966   0.17649  -0.1062   0.0033   1.0000
  18.250   1.1388   0.19139   0.18833  -0.1132   0.0034   1.0000
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