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MH 112 Airfoil (mh112-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 112 Airfoil (mh112-il)
Reynolds number: 100,000
Max Cl/Cd: 48.6 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh112-il-100000-n5.txt
Download as CSV file: xf-mh112-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500   0.1542   0.09575   0.09006  -0.1358   0.8845   0.0391
  -9.250   0.1728   0.09289   0.08718  -0.1378   0.8806   0.0380
  -8.750   0.1777   0.08550   0.07977  -0.1414   0.8677   0.0345
  -8.500   0.1885   0.08247   0.07673  -0.1433   0.8626   0.0340
  -8.250   0.2010   0.07895   0.07318  -0.1463   0.8587   0.0335
  -8.000   0.1950   0.07691   0.07119  -0.1449   0.8494   0.0332
  -7.500   0.1989   0.06948   0.06375  -0.1489   0.8383   0.0323
  -7.250   0.1806   0.06711   0.06145  -0.1464   0.8280   0.0320
  -7.000   0.1316   0.05657   0.05088  -0.1513   0.8193   0.0305
  -6.750   0.1044   0.05221   0.04652  -0.1522   0.8076   0.0302
  -6.500   0.0968   0.04235   0.03603  -0.1650   0.8016   0.0298
  -6.250   0.0852   0.03945   0.03275  -0.1637   0.7910   0.0301
  -6.000   0.1084   0.03592   0.02868  -0.1672   0.7867   0.0310
  -5.750   0.1405   0.03435   0.02693  -0.1696   0.7840   0.0325
  -5.500   0.1607   0.03248   0.02466  -0.1701   0.7786   0.0337
  -5.250   0.1769   0.03092   0.02269  -0.1694   0.7717   0.0348
  -5.000   0.2075   0.02970   0.02135  -0.1706   0.7681   0.0359
  -4.750   0.2426   0.02831   0.01973  -0.1723   0.7655   0.0375
  -4.500   0.2804   0.02692   0.01808  -0.1744   0.7633   0.0397
  -4.250   0.2851   0.02697   0.01815  -0.1709   0.7541   0.0413
  -4.000   0.3155   0.02622   0.01728  -0.1716   0.7501   0.0453
  -3.750   0.3506   0.02535   0.01629  -0.1730   0.7472   0.0498
  -3.500   0.3889   0.02450   0.01536  -0.1750   0.7448   0.0563
  -3.250   0.3981   0.02459   0.01545  -0.1721   0.7365   0.0619
  -3.000   0.4271   0.02412   0.01499  -0.1726   0.7320   0.0722
  -2.750   0.4624   0.02350   0.01436  -0.1740   0.7288   0.0890
  -2.500   0.5011   0.02286   0.01373  -0.1761   0.7263   0.1136
  -2.250   0.5129   0.02307   0.01399  -0.1736   0.7185   0.1324
  -2.000   0.5403   0.02284   0.01383  -0.1737   0.7136   0.1613
  -1.750   0.5751   0.02243   0.01347  -0.1750   0.7102   0.1981
  -1.500   0.6135   0.02198   0.01305  -0.1769   0.7076   0.2413
  -1.250   0.6237   0.02234   0.01354  -0.1741   0.6997   0.2702
  -1.000   0.6504   0.02227   0.01353  -0.1740   0.6947   0.3118
  -0.750   0.6849   0.02199   0.01331  -0.1751   0.6913   0.3606
  -0.500   0.7231   0.02167   0.01301  -0.1767   0.6887   0.4123
  -0.250   0.7288   0.02225   0.01372  -0.1731   0.6800   0.4426
   0.000   0.7566   0.02222   0.01372  -0.1729   0.6754   0.4860
   0.250   0.7917   0.02200   0.01350  -0.1739   0.6721   0.5312
   0.500   0.8153   0.02213   0.01365  -0.1730   0.6670   0.5689
   0.750   0.8283   0.02251   0.01411  -0.1705   0.6598   0.6009
   1.000   0.8583   0.02238   0.01400  -0.1705   0.6556   0.6407
   1.250   0.8936   0.02209   0.01370  -0.1713   0.6525   0.6839
   1.500   0.8968   0.02266   0.01439  -0.1672   0.6444   0.7179
   1.750   0.9165   0.02264   0.01444  -0.1653   0.6391   0.7663
   2.000   0.9426   0.02223   0.01410  -0.1641   0.6354   0.8409
   2.250   0.9508   0.02247   0.01439  -0.1607   0.6283   1.0000
   2.500   0.9724   0.02281   0.01462  -0.1599   0.6219   1.0000
   2.750   1.0108   0.02265   0.01429  -0.1616   0.6177   1.0000
   3.000   1.0286   0.02309   0.01466  -0.1602   0.6111   1.0000
   3.250   1.0461   0.02353   0.01503  -0.1587   0.6040   1.0000
   3.500   1.0828   0.02338   0.01475  -0.1600   0.5995   1.0000
   3.750   1.0971   0.02394   0.01527  -0.1581   0.5926   1.0000
   4.000   1.1154   0.02437   0.01565  -0.1567   0.5857   1.0000
   4.250   1.1514   0.02422   0.01538  -0.1579   0.5811   1.0000
   4.500   1.1606   0.02498   0.01614  -0.1553   0.5736   1.0000
   4.750   1.1808   0.02536   0.01648  -0.1542   0.5670   1.0000
   5.000   1.2173   0.02518   0.01620  -0.1554   0.5625   1.0000
   5.250   1.2198   0.02621   0.01728  -0.1520   0.5542   1.0000
   5.500   1.2433   0.02647   0.01749  -0.1514   0.5479   1.0000
   5.750   1.2786   0.02631   0.01722  -0.1524   0.5431   1.0000
   6.000   1.2756   0.02763   0.01862  -0.1484   0.5340   1.0000
   6.250   1.3039   0.02768   0.01862  -0.1484   0.5282   1.0000
   6.500   1.3168   0.02843   0.01937  -0.1466   0.5210   1.0000
   6.750   1.3300   0.02915   0.02010  -0.1448   0.5133   1.0000
   7.000   1.3653   0.02889   0.01974  -0.1457   0.5081   1.0000
   7.250   1.3599   0.03052   0.02149  -0.1418   0.4987   1.0000
   7.500   1.3856   0.03065   0.02157  -0.1415   0.4923   1.0000
   7.750   1.3924   0.03179   0.02275  -0.1392   0.4840   1.0000
   8.000   1.4079   0.03247   0.02342  -0.1379   0.4764   1.0000
   8.250   1.4261   0.03303   0.02398  -0.1368   0.4693   1.0000
   8.500   1.4313   0.03432   0.02533  -0.1346   0.4604   1.0000
   8.750   1.4578   0.03439   0.02533  -0.1343   0.4539   1.0000
   9.000   1.4544   0.03631   0.02735  -0.1314   0.4443   1.0000
   9.250   1.4812   0.03631   0.02729  -0.1312   0.4377   1.0000
   9.500   1.4761   0.03846   0.02956  -0.1284   0.4279   1.0000
   9.750   1.4985   0.03874   0.02979  -0.1278   0.4210   1.0000
  10.000   1.4967   0.04080   0.03195  -0.1254   0.4116   1.0000
  10.250   1.5150   0.04137   0.03250  -0.1246   0.4043   1.0000
  10.500   1.5160   0.04335   0.03455  -0.1226   0.3954   1.0000
  10.750   1.5304   0.04423   0.03542  -0.1215   0.3877   1.0000
  11.000   1.5343   0.04608   0.03734  -0.1199   0.3794   1.0000
  11.250   1.5448   0.04735   0.03863  -0.1188   0.3716   1.0000
  11.500   1.5518   0.04899   0.04031  -0.1175   0.3638   1.0000
  11.750   1.5581   0.05072   0.04208  -0.1162   0.3558   1.0000
  12.000   1.5699   0.05197   0.04333  -0.1152   0.3487   1.0000
  12.250   1.5708   0.05431   0.04578  -0.1139   0.3406   1.0000
  12.500   1.5891   0.05493   0.04633  -0.1132   0.3343   1.0000
  12.750   1.5837   0.05804   0.04960  -0.1118   0.3261   1.0000
  13.000   1.5988   0.05898   0.05050  -0.1111   0.3196   1.0000
  13.250   1.5977   0.06178   0.05342  -0.1101   0.3123   1.0000
  13.500   1.6041   0.06371   0.05539  -0.1093   0.3053   1.0000
  13.750   1.6132   0.06541   0.05711  -0.1085   0.2990   1.0000
  14.000   1.6103   0.06855   0.06037  -0.1077   0.2917   1.0000
  14.250   1.6270   0.06931   0.06109  -0.1072   0.2859   1.0000
  14.500   1.6187   0.07325   0.06521  -0.1065   0.2788   1.0000
  14.750   1.6238   0.07549   0.06750  -0.1060   0.2724   1.0000
  15.000   1.6303   0.07759   0.06964  -0.1056   0.2665   1.0000
  15.250   1.6236   0.08151   0.07370  -0.1053   0.2596   1.0000
  15.500   1.6371   0.08266   0.07483  -0.1049   0.2541   1.0000
  15.750   1.6273   0.08711   0.07946  -0.1048   0.2476   1.0000
  16.000   1.6275   0.09018   0.08262  -0.1048   0.2414   1.0000
  16.250   1.6367   0.09196   0.08440  -0.1046   0.2361   1.0000
  16.500   1.6229   0.09718   0.08982  -0.1051   0.2295   1.0000
  16.750   1.6309   0.09913   0.09179  -0.1050   0.2241   1.0000
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