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MH 112 Airfoil (mh112-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: MH 112 Airfoil (mh112-il)
Reynolds number: 200,000
Max Cl/Cd: 79.96 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh112-il-200000.txt
Download as CSV file: xf-mh112-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250   0.1936   0.10020   0.09621  -0.1438   0.9301   0.0510
 -10.000   0.2032   0.09782   0.09384  -0.1448   0.9227   0.0525
  -9.750   0.2001   0.09376   0.08977  -0.1534   0.9168   0.0551
  -9.500   0.2362   0.09056   0.08653  -0.1537   0.9151   0.0563
  -9.250   0.2517   0.08807   0.08403  -0.1553   0.9094   0.0577
  -9.000   0.2604   0.08550   0.08145  -0.1572   0.9021   0.0599
  -8.750   0.2614   0.08131   0.07723  -0.1638   0.8961   0.0618
  -8.500   0.2742   0.07967   0.07560  -0.1617   0.8888   0.0625
  -8.250   0.2898   0.07749   0.07340  -0.1624   0.8827   0.0638
  -8.000   0.3040   0.07477   0.07064  -0.1651   0.8778   0.0662
  -7.750   0.2674   0.07179   0.06774  -0.1672   0.8645   0.0687
  -7.500   0.2961   0.06963   0.06553  -0.1664   0.8613   0.0695
  -7.250   0.3116   0.06787   0.06375  -0.1662   0.8563   0.0708
  -7.000   0.3108   0.06639   0.06231  -0.1645   0.8479   0.0724
  -6.500   0.2721   0.06054   0.05654  -0.1669   0.8300   0.0770
  -6.250   0.2124   0.03721   0.03229  -0.1882   0.8202   0.0445
  -6.000   0.2029   0.03163   0.02590  -0.1877   0.8103   0.0389
  -5.750   0.2291   0.02903   0.02299  -0.1892   0.8062   0.0384
  -5.500   0.2611   0.02651   0.02003  -0.1913   0.8031   0.0381
  -5.250   0.2871   0.02482   0.01795  -0.1918   0.7987   0.0383
  -5.000   0.3059   0.02377   0.01662  -0.1905   0.7919   0.0388
  -4.750   0.3359   0.02250   0.01518  -0.1911   0.7878   0.0398
  -4.500   0.3696   0.02153   0.01413  -0.1922   0.7847   0.0418
  -4.250   0.4055   0.02064   0.01308  -0.1937   0.7819   0.0451
  -4.000   0.4191   0.02051   0.01298  -0.1913   0.7741   0.0481
  -3.750   0.4483   0.01980   0.01227  -0.1916   0.7696   0.0522
  -3.500   0.4821   0.01903   0.01146  -0.1926   0.7662   0.0587
  -3.250   0.5188   0.01836   0.01078  -0.1943   0.7633   0.0716
  -3.000   0.5356   0.01820   0.01072  -0.1925   0.7561   0.0864
  -2.750   0.5649   0.01775   0.01036  -0.1929   0.7511   0.1116
  -2.500   0.5992   0.01731   0.00995  -0.1942   0.7474   0.1453
  -2.250   0.6360   0.01690   0.00961  -0.1959   0.7444   0.1857
  -2.000   0.6533   0.01697   0.00980  -0.1942   0.7372   0.2194
  -1.750   0.6822   0.01674   0.00969  -0.1944   0.7321   0.2630
  -1.500   0.7163   0.01644   0.00946  -0.1956   0.7283   0.3119
  -1.250   0.7502   0.01627   0.00935  -0.1967   0.7248   0.3618
  -1.000   0.7682   0.01640   0.00963  -0.1949   0.7176   0.4013
  -0.750   0.7973   0.01629   0.00959  -0.1950   0.7126   0.4474
  -0.500   0.8313   0.01614   0.00945  -0.1959   0.7088   0.4937
  -0.250   0.8570   0.01623   0.00960  -0.1954   0.7037   0.5327
   0.000   0.8790   0.01632   0.00976  -0.1943   0.6972   0.5685
   0.250   0.9092   0.01622   0.00968  -0.1944   0.6926   0.6055
   0.500   0.9433   0.01610   0.00953  -0.1953   0.6889   0.6421
   0.750   0.9599   0.01629   0.00985  -0.1931   0.6818   0.6733
   1.000   0.9852   0.01624   0.00984  -0.1924   0.6761   0.7081
   1.250   1.0161   0.01606   0.00966  -0.1925   0.6717   0.7464
   1.500   1.0343   0.01612   0.00983  -0.1905   0.6654   0.7860
   1.750   1.0509   0.01603   0.00985  -0.1879   0.6590   0.8368
   2.000   1.0747   0.01563   0.00949  -0.1864   0.6542   1.0000
   2.250   1.1035   0.01582   0.00957  -0.1868   0.6482   1.0000
   2.500   1.1282   0.01599   0.00969  -0.1865   0.6414   1.0000
   2.750   1.1616   0.01602   0.00956  -0.1875   0.6362   1.0000
   3.000   1.1882   0.01622   0.00969  -0.1874   0.6304   1.0000
   3.250   1.2103   0.01643   0.00988  -0.1865   0.6236   1.0000
   3.500   1.2419   0.01648   0.00981  -0.1872   0.6182   1.0000
   3.750   1.2672   0.01671   0.00998  -0.1868   0.6123   1.0000
   4.000   1.2881   0.01693   0.01020  -0.1856   0.6053   1.0000
   4.250   1.3191   0.01701   0.01017  -0.1862   0.5997   1.0000
   4.500   1.3411   0.01728   0.01043  -0.1852   0.5933   1.0000
   4.750   1.3623   0.01750   0.01063  -0.1841   0.5863   1.0000
   5.000   1.3941   0.01759   0.01060  -0.1849   0.5806   1.0000
   5.250   1.4099   0.01793   0.01099  -0.1828   0.5733   1.0000
   5.500   1.4328   0.01812   0.01114  -0.1820   0.5664   1.0000
   5.750   1.4625   0.01829   0.01122  -0.1824   0.5604   1.0000
   6.000   1.4738   0.01865   0.01164  -0.1796   0.5524   1.0000
   6.250   1.5003   0.01881   0.01173  -0.1794   0.5458   1.0000
   6.500   1.5157   0.01916   0.01210  -0.1773   0.5384   1.0000
   6.750   1.5314   0.01942   0.01235  -0.1752   0.5308   1.0000
   7.000   1.5561   0.01967   0.01253  -0.1747   0.5238   1.0000
   7.250   1.5621   0.02010   0.01303  -0.1710   0.5156   1.0000
   7.500   1.5904   0.02029   0.01310  -0.1712   0.5084   1.0000
   7.750   1.5920   0.02086   0.01377  -0.1669   0.4999   1.0000
   8.000   1.6121   0.02116   0.01400  -0.1657   0.4921   1.0000
   8.250   1.6193   0.02175   0.01464  -0.1625   0.4836   1.0000
   8.500   1.6343   0.02218   0.01503  -0.1606   0.4754   1.0000
   8.750   1.6439   0.02280   0.01568  -0.1580   0.4669   1.0000
   9.000   1.6554   0.02337   0.01624  -0.1557   0.4582   1.0000
   9.250   1.6651   0.02408   0.01696  -0.1533   0.4495   1.0000
   9.500   1.6750   0.02477   0.01764  -0.1509   0.4407   1.0000
   9.750   1.6837   0.02560   0.01848  -0.1485   0.4319   1.0000
  10.000   1.6932   0.02639   0.01927  -0.1462   0.4231   1.0000
  10.250   1.7006   0.02736   0.02026  -0.1438   0.4143   1.0000
  10.500   1.7098   0.02826   0.02115  -0.1417   0.4056   1.0000
  10.750   1.7163   0.02936   0.02228  -0.1394   0.3969   1.0000
  11.000   1.7252   0.03037   0.02328  -0.1374   0.3884   1.0000
  11.250   1.7314   0.03159   0.02453  -0.1352   0.3799   1.0000
  11.500   1.7391   0.03274   0.02566  -0.1333   0.3716   1.0000
  11.750   1.7457   0.03404   0.02699  -0.1313   0.3634   1.0000
  12.000   1.7521   0.03535   0.02832  -0.1294   0.3553   1.0000
  12.250   1.7601   0.03666   0.02964  -0.1278   0.3476   1.0000
  12.500   1.7642   0.03822   0.03124  -0.1259   0.3397   1.0000
  12.750   1.7743   0.03948   0.03246  -0.1245   0.3323   1.0000
  13.000   1.7757   0.04133   0.03441  -0.1226   0.3246   1.0000
  13.250   1.7894   0.04239   0.03537  -0.1216   0.3175   1.0000
  13.500   1.7871   0.04463   0.03777  -0.1197   0.3101   1.0000
  13.750   1.7983   0.04590   0.03896  -0.1186   0.3031   1.0000
  14.000   1.7986   0.04810   0.04129  -0.1170   0.2961   1.0000
  14.250   1.8029   0.04998   0.04319  -0.1158   0.2891   1.0000
  14.500   1.8102   0.05169   0.04490  -0.1147   0.2825   1.0000
  14.750   1.8089   0.05420   0.04753  -0.1134   0.2756   1.0000
  15.000   1.8227   0.05532   0.04853  -0.1127   0.2690   1.0000
  15.250   1.8160   0.05848   0.05190  -0.1113   0.2626   1.0000
  15.500   1.8195   0.06065   0.05408  -0.1104   0.2562   1.0000
  15.750   1.8231   0.06290   0.05637  -0.1096   0.2499   1.0000
  16.000   1.8202   0.06590   0.05949  -0.1088   0.2435   1.0000
  16.250   1.8315   0.06730   0.06079  -0.1082   0.2373   1.0000
  16.500   1.8229   0.07110   0.06480  -0.1075   0.2313   1.0000
  16.750   1.8243   0.07372   0.06744  -0.1070   0.2253   1.0000
  17.000   1.8263   0.07633   0.07010  -0.1066   0.2195   1.0000
  17.250   1.8215   0.07988   0.07377  -0.1063   0.2135   1.0000
  17.500   1.8312   0.08148   0.07526  -0.1060   0.2077   1.0000
  17.750   1.8212   0.08585   0.07986  -0.1060   0.2022   1.0000
  18.000   1.8204   0.08896   0.08302  -0.1059   0.1966   1.0000
  18.250   1.8231   0.09157   0.08563  -0.1059   0.1913   1.0000
  18.500   1.8162   0.09568   0.08989  -0.1062   0.1858   1.0000
  18.750   1.8208   0.09802   0.09219  -0.1063   0.1807   1.0000
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