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MH 116 9.84% (mh116-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MH 116 9.84% (mh116-il)
Reynolds number: 50,000
Max Cl/Cd: 38.98 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh116-il-50000.txt
Download as CSV file: xf-mh116-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3520   0.10486   0.09876  -0.0294   1.0000   0.2038
  -7.500  -0.3440   0.10096   0.09493  -0.0273   1.0000   0.2092
  -7.250  -0.3544   0.09970   0.09378  -0.0249   1.0000   0.2153
  -7.000  -0.3865   0.10042   0.09469  -0.0216   1.0000   0.2180
  -6.750  -0.3748   0.09641   0.09072  -0.0192   1.0000   0.2270
  -6.500  -0.4030   0.09646   0.09094  -0.0166   1.0000   0.2316
  -6.250  -0.4023   0.09352   0.08807  -0.0139   1.0000   0.2378
  -6.000  -0.4221   0.09277   0.08745  -0.0132   1.0000   0.2460
  -5.750  -0.4191   0.08975   0.08448  -0.0099   1.0000   0.2567
  -5.500  -0.4283   0.08760   0.08243  -0.0089   1.0000   0.2650
  -5.250  -0.4387   0.08572   0.08063  -0.0092   1.0000   0.2768
  -5.000  -0.4436   0.08362   0.07858  -0.0097   1.0000   0.2901
  -4.750  -0.4417   0.08062   0.07565  -0.0067   1.0000   0.3053
  -4.500  -0.4405   0.07793   0.07300  -0.0053   1.0000   0.3198
  -4.250  -0.4377   0.07503   0.07014  -0.0036   1.0000   0.3352
  -4.000  -0.3318   0.04972   0.04302  -0.0538   1.0000   0.1184
  -3.750  -0.2992   0.04405   0.03677  -0.0579   1.0000   0.1114
  -3.500  -0.2673   0.03998   0.03207  -0.0606   1.0000   0.1149
  -3.250  -0.2349   0.03654   0.02790  -0.0627   1.0000   0.1230
  -3.000  -0.2066   0.03416   0.02511  -0.0634   1.0000   0.1376
  -2.750  -0.1790   0.03220   0.02283  -0.0637   1.0000   0.1586
  -2.500  -0.1526   0.03082   0.02110  -0.0638   1.0000   0.1907
  -2.250  -0.1296   0.02978   0.02013  -0.0633   1.0000   0.2295
  -2.000  -0.1059   0.02889   0.01926  -0.0630   1.0000   0.2779
  -1.750  -0.0829   0.02820   0.01868  -0.0624   1.0000   0.3355
  -1.500  -0.0589   0.02760   0.01828  -0.0619   1.0000   0.4096
  -1.250  -0.0358   0.02699   0.01809  -0.0610   1.0000   0.5171
  -1.000  -0.0210   0.02601   0.01808  -0.0575   1.0000   0.6961
  -0.750  -0.0096   0.02504   0.01727  -0.0551   1.0000   1.0000
  -0.500   0.0151   0.02566   0.01731  -0.0560   1.0000   1.0000
  -0.250   0.0372   0.02632   0.01755  -0.0564   1.0000   1.0000
   0.000   0.0583   0.02701   0.01791  -0.0566   1.0000   1.0000
   0.250   0.0789   0.02775   0.01836  -0.0567   1.0000   1.0000
   0.500   0.0990   0.02852   0.01885  -0.0568   1.0000   1.0000
   0.750   0.1302   0.02968   0.01975  -0.0590   0.9950   1.0000
   1.000   0.1722   0.03115   0.02096  -0.0632   0.9839   1.0000
   1.250   0.2094   0.03242   0.02201  -0.0665   0.9726   1.0000
   1.500   0.2447   0.03364   0.02306  -0.0693   0.9612   1.0000
   1.750   0.2793   0.03485   0.02414  -0.0720   0.9496   1.0000
   2.000   0.3140   0.03606   0.02523  -0.0746   0.9376   1.0000
   2.250   0.3486   0.03726   0.02635  -0.0771   0.9253   1.0000
   2.500   0.3829   0.03845   0.02747  -0.0794   0.9128   1.0000
   2.750   0.4168   0.03961   0.02860  -0.0817   0.8997   1.0000
   3.000   0.4500   0.04075   0.02972  -0.0836   0.8863   1.0000
   3.250   0.4821   0.04185   0.03081  -0.0854   0.8726   1.0000
   3.500   0.5122   0.04291   0.03190  -0.0867   0.8583   1.0000
   3.750   0.5406   0.04395   0.03296  -0.0878   0.8433   1.0000
   4.000   0.5688   0.04498   0.03407  -0.0887   0.8279   1.0000
   4.250   0.5974   0.04600   0.03515  -0.0896   0.8122   1.0000
   4.500   0.6281   0.04695   0.03618  -0.0905   0.7961   1.0000
   4.750   0.6619   0.04779   0.03712  -0.0917   0.7798   1.0000
   5.000   0.7001   0.04845   0.03796  -0.0932   0.7637   1.0000
   5.250   0.7247   0.04933   0.03896  -0.0930   0.7458   1.0000
   5.500   0.7510   0.05010   0.03987  -0.0929   0.7273   1.0000
   5.750   0.7898   0.05030   0.04031  -0.0937   0.7097   1.0000
   6.000   0.8278   0.05031   0.04053  -0.0941   0.6916   1.0000
   6.250   0.8516   0.05083   0.04123  -0.0931   0.6709   1.0000
   6.500   0.9051   0.04936   0.04013  -0.0937   0.6529   1.0000
   6.750   0.9311   0.04932   0.04031  -0.0922   0.6310   1.0000
   7.000   1.0062   0.04496   0.03643  -0.0924   0.6123   1.0000
   7.250   1.0681   0.04134   0.03329  -0.0919   0.5879   1.0000
   7.500   1.1565   0.03526   0.02765  -0.0926   0.5553   1.0000
   7.750   1.2021   0.03269   0.02520  -0.0908   0.5127   1.0000
   8.000   1.2245   0.03208   0.02456  -0.0875   0.4658   1.0000
   8.250   1.2462   0.03197   0.02425  -0.0843   0.4135   1.0000
   8.500   1.2580   0.03300   0.02503  -0.0808   0.3640   1.0000
   8.750   1.2712   0.03445   0.02608  -0.0778   0.3165   1.0000
   9.000   1.2807   0.03629   0.02764  -0.0748   0.2748   1.0000
   9.250   1.2883   0.03837   0.02962  -0.0717   0.2386   1.0000
   9.500   1.2978   0.04064   0.03164  -0.0690   0.2044   1.0000
   9.750   1.3040   0.04304   0.03397  -0.0661   0.1753   1.0000
  10.000   1.3134   0.04581   0.03664  -0.0636   0.1490   1.0000
  10.250   1.3305   0.04925   0.03989  -0.0623   0.1254   1.0000
  10.500   1.3357   0.05237   0.04322  -0.0596   0.1109   1.0000
  10.750   1.3495   0.05645   0.04746  -0.0580   0.0990   1.0000
  11.000   1.3434   0.05997   0.05163  -0.0543   0.0939   1.0000
  11.250   1.3495   0.06369   0.05538  -0.0526   0.0858   1.0000
  11.500   1.3337   0.06708   0.05924  -0.0486   0.0839   1.0000
  11.750   1.3178   0.07094   0.06348  -0.0454   0.0825   1.0000
  12.000   1.3000   0.07516   0.06805  -0.0429   0.0820   1.0000
  12.250   1.2793   0.07972   0.07291  -0.0412   0.0821   1.0000
  12.500   1.2558   0.08474   0.07822  -0.0404   0.0825   1.0000
  12.750   1.2312   0.09029   0.08401  -0.0406   0.0832   1.0000
  13.000   1.2061   0.09642   0.09034  -0.0419   0.0842   1.0000
  13.250   1.1821   0.10310   0.09711  -0.0441   0.0852   1.0000
  13.500   1.1602   0.11031   0.10444  -0.0471   0.0861   1.0000
  13.750   1.1412   0.11791   0.11212  -0.0505   0.0869   1.0000
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