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MH 112 Airfoil (mh112-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: MH 112 Airfoil (mh112-il)
Reynolds number: 200,000
Max Cl/Cd: 79.35 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh112-il-200000-n5.txt
Download as CSV file: xf-mh112-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 112  Airfoil                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500   0.2059   0.09378   0.08924  -0.1506   0.8766   0.0273
 -10.000   0.2098   0.08529   0.08068  -0.1545   0.8617   0.0233
  -9.750   0.2214   0.08317   0.07853  -0.1556   0.8554   0.0230
  -9.500   0.2280   0.08075   0.07611  -0.1561   0.8481   0.0227
  -9.250   0.2352   0.07792   0.07324  -0.1575   0.8419   0.0224
  -9.000   0.2387   0.07497   0.07027  -0.1584   0.8355   0.0220
  -8.750   0.2384   0.07169   0.06700  -0.1592   0.8283   0.0215
  -8.500   0.2004   0.06130   0.05658  -0.1630   0.8210   0.0201
  -8.250   0.1589   0.05263   0.04793  -0.1653   0.8121   0.0196
  -8.000   0.0669   0.03518   0.02998  -0.1809   0.7998   0.0188
  -7.750   0.0614   0.03099   0.02536  -0.1839   0.7921   0.0188
  -7.500   0.0735   0.02812   0.02206  -0.1856   0.7867   0.0189
  -7.250   0.0942   0.02585   0.01937  -0.1871   0.7827   0.0192
  -7.000   0.1130   0.02428   0.01751  -0.1872   0.7774   0.0194
  -6.750   0.1348   0.02297   0.01595  -0.1872   0.7721   0.0197
  -6.500   0.1599   0.02184   0.01458  -0.1876   0.7677   0.0201
  -6.250   0.1878   0.02100   0.01363  -0.1883   0.7640   0.0206
  -6.000   0.2118   0.02033   0.01288  -0.1881   0.7591   0.0211
  -5.750   0.2363   0.01967   0.01213  -0.1879   0.7540   0.0217
  -5.500   0.2632   0.01901   0.01132  -0.1881   0.7495   0.0225
  -5.250   0.2925   0.01836   0.01052  -0.1886   0.7457   0.0234
  -5.000   0.3188   0.01792   0.01006  -0.1887   0.7411   0.0246
  -4.750   0.3443   0.01754   0.00960  -0.1885   0.7359   0.0264
  -4.500   0.3718   0.01713   0.00916  -0.1887   0.7312   0.0285
  -4.250   0.4017   0.01670   0.00861  -0.1892   0.7272   0.0310
  -4.000   0.4294   0.01635   0.00821  -0.1894   0.7228   0.0339
  -3.750   0.4554   0.01605   0.00789  -0.1892   0.7175   0.0379
  -3.500   0.4834   0.01574   0.00757  -0.1893   0.7126   0.0449
  -3.250   0.5134   0.01544   0.00721  -0.1898   0.7085   0.0549
  -3.000   0.5412   0.01521   0.00700  -0.1899   0.7040   0.0682
  -2.750   0.5673   0.01503   0.00687  -0.1897   0.6986   0.0846
  -2.500   0.5953   0.01483   0.00671  -0.1898   0.6937   0.1056
  -2.250   0.6253   0.01464   0.00653  -0.1904   0.6895   0.1312
  -2.000   0.6520   0.01451   0.00649  -0.1903   0.6845   0.1583
  -1.750   0.6783   0.01441   0.00646  -0.1901   0.6791   0.1869
  -1.500   0.7065   0.01431   0.00638  -0.1902   0.6742   0.2186
  -1.250   0.7367   0.01420   0.00628  -0.1907   0.6700   0.2529
  -1.000   0.7613   0.01417   0.00636  -0.1902   0.6643   0.2862
  -0.750   0.7878   0.01414   0.00638  -0.1900   0.6589   0.3227
  -0.500   0.8163   0.01408   0.00637  -0.1901   0.6541   0.3605
  -0.250   0.8434   0.01408   0.00642  -0.1900   0.6491   0.3981
   0.000   0.8681   0.01411   0.00653  -0.1894   0.6432   0.4345
   0.250   0.8949   0.01413   0.00658  -0.1892   0.6379   0.4698
   0.500   0.9234   0.01416   0.00659  -0.1892   0.6333   0.5042
   0.750   0.9463   0.01424   0.00677  -0.1883   0.6270   0.5344
   1.000   0.9715   0.01430   0.00685  -0.1877   0.6212   0.5645
   1.250   0.9985   0.01434   0.00687  -0.1875   0.6159   0.5940
   1.500   1.0204   0.01444   0.00705  -0.1863   0.6091   0.6224
   1.750   1.0442   0.01451   0.00715  -0.1855   0.6026   0.6520
   2.000   1.0693   0.01457   0.00720  -0.1848   0.5968   0.6838
   2.250   1.0892   0.01467   0.00740  -0.1833   0.5898   0.7173
   2.500   1.1108   0.01473   0.00751  -0.1819   0.5834   0.7571
   2.750   1.1308   0.01476   0.00760  -0.1802   0.5778   0.8099
   3.000   1.1431   0.01463   0.00765  -0.1769   0.5712   1.0000
   3.250   1.1673   0.01484   0.00776  -0.1763   0.5650   1.0000
   3.500   1.1906   0.01506   0.00790  -0.1756   0.5591   1.0000
   3.750   1.2106   0.01530   0.00812  -0.1742   0.5524   1.0000
   4.000   1.2331   0.01554   0.00827  -0.1734   0.5462   1.0000
   4.250   1.2540   0.01581   0.00850  -0.1722   0.5401   1.0000
   4.500   1.2732   0.01610   0.00877  -0.1708   0.5333   1.0000
   4.750   1.2950   0.01637   0.00896  -0.1699   0.5270   1.0000
   5.000   1.3134   0.01670   0.00928  -0.1684   0.5204   1.0000
   5.250   1.3321   0.01703   0.00959  -0.1669   0.5135   1.0000
   5.500   1.3525   0.01736   0.00985  -0.1658   0.5071   1.0000
   5.750   1.3689   0.01776   0.01027  -0.1640   0.5001   1.0000
   6.000   1.3869   0.01814   0.01061  -0.1626   0.4931   1.0000
   6.250   1.4039   0.01857   0.01101  -0.1610   0.4860   1.0000
   6.500   1.4197   0.01903   0.01147  -0.1592   0.4786   1.0000
   6.750   1.4370   0.01949   0.01188  -0.1577   0.4717   1.0000
   7.000   1.4508   0.02004   0.01246  -0.1558   0.4637   1.0000
   7.250   1.4663   0.02058   0.01295  -0.1541   0.4563   1.0000
   7.500   1.4801   0.02118   0.01358  -0.1523   0.4485   1.0000
   7.750   1.4933   0.02183   0.01422  -0.1504   0.4403   1.0000
   8.000   1.5067   0.02251   0.01490  -0.1486   0.4326   1.0000
   8.250   1.5188   0.02327   0.01565  -0.1467   0.4240   1.0000
   8.500   1.5310   0.02405   0.01643  -0.1449   0.4159   1.0000
   8.750   1.5419   0.02492   0.01731  -0.1429   0.4071   1.0000
   9.000   1.5531   0.02581   0.01819  -0.1411   0.3988   1.0000
   9.250   1.5628   0.02680   0.01919  -0.1392   0.3899   1.0000
   9.500   1.5731   0.02781   0.02020  -0.1374   0.3816   1.0000
   9.750   1.5819   0.02894   0.02133  -0.1355   0.3726   1.0000
  10.000   1.5912   0.03007   0.02246  -0.1337   0.3643   1.0000
  10.250   1.5994   0.03131   0.02371  -0.1320   0.3557   1.0000
  10.500   1.6079   0.03258   0.02498  -0.1303   0.3477   1.0000
  10.750   1.6157   0.03394   0.02635  -0.1286   0.3394   1.0000
  11.000   1.6234   0.03533   0.02775  -0.1270   0.3317   1.0000
  11.250   1.6310   0.03679   0.02923  -0.1255   0.3238   1.0000
  11.500   1.6381   0.03832   0.03075  -0.1240   0.3168   1.0000
  11.750   1.6458   0.03987   0.03235  -0.1226   0.3092   1.0000
  12.000   1.6518   0.04156   0.03401  -0.1212   0.3024   1.0000
  12.250   1.6598   0.04316   0.03569  -0.1200   0.2954   1.0000
  12.500   1.6658   0.04495   0.03749  -0.1188   0.2887   1.0000
  12.750   1.6724   0.04674   0.03931  -0.1176   0.2824   1.0000
  13.000   1.6789   0.04858   0.04121  -0.1166   0.2757   1.0000
  13.250   1.6835   0.05061   0.04321  -0.1154   0.2696   1.0000
  13.500   1.6905   0.05249   0.04520  -0.1145   0.2633   1.0000
  13.750   1.6950   0.05464   0.04738  -0.1136   0.2570   1.0000
  14.000   1.6998   0.05679   0.04955  -0.1127   0.2512   1.0000
  14.250   1.7050   0.05897   0.05182  -0.1120   0.2449   1.0000
  14.500   1.7079   0.06139   0.05425  -0.1112   0.2391   1.0000
  14.750   1.7126   0.06369   0.05664  -0.1106   0.2333   1.0000
  15.000   1.7158   0.06620   0.05921  -0.1100   0.2273   1.0000
  15.250   1.7176   0.06886   0.06188  -0.1094   0.2218   1.0000
  15.500   1.7214   0.07141   0.06454  -0.1091   0.2159   1.0000
  15.750   1.7226   0.07426   0.06743  -0.1087   0.2102   1.0000
  16.000   1.7243   0.07709   0.07033  -0.1084   0.2048   1.0000
  16.250   1.7261   0.07997   0.07329  -0.1082   0.1989   1.0000
  16.500   1.7252   0.08317   0.07651  -0.1081   0.1937   1.0000
  16.750   1.7273   0.08609   0.07953  -0.1080   0.1883   1.0000
  17.000   1.7268   0.08936   0.08287  -0.1081   0.1829   1.0000
  17.250   1.7264   0.09261   0.08616  -0.1082   0.1781   1.0000
  17.500   1.7267   0.09587   0.08952  -0.1085   0.1727   1.0000
  17.750   1.7249   0.09936   0.09305  -0.1088   0.1678   1.0000
  18.000   1.7246   0.10269   0.09646  -0.1092   0.1631   1.0000
  18.250   1.7236   0.10618   0.10004  -0.1097   0.1581   1.0000
  18.500   1.7213   0.10979   0.10368  -0.1103   0.1537   1.0000
  18.750   1.7210   0.11320   0.10720  -0.1110   0.1492   1.0000
  19.000   1.7194   0.11679   0.11086  -0.1118   0.1446   1.0000
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