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MH 113 14.62% (mh113-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: MH 113 14.62% (mh113-il)
Reynolds number: 200,000
Max Cl/Cd: 84.65 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh113-il-200000.txt
Download as CSV file: xf-mh113-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 113  14.62%                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750   0.0464   0.10377   0.10005  -0.1113   0.9408   0.0507
  -9.500   0.0591   0.10043   0.09670  -0.1149   0.9365   0.0529
  -9.250   0.0585   0.09576   0.09205  -0.1266   0.9326   0.0546
  -9.000   0.0903   0.09186   0.08813  -0.1265   0.9321   0.0553
  -8.750   0.1190   0.08845   0.08469  -0.1296   0.9311   0.0568
  -8.500   0.1295   0.08603   0.08228  -0.1307   0.9241   0.0585
  -8.250   0.1363   0.08195   0.07819  -0.1392   0.9182   0.0621
  -8.000   0.1541   0.07701   0.07325  -0.1451   0.9154   0.0632
  -7.750   0.1700   0.07513   0.07137  -0.1437   0.9092   0.0642
  -7.500   0.1879   0.07273   0.06895  -0.1451   0.9038   0.0659
  -7.250   0.2056   0.06922   0.06542  -0.1500   0.8993   0.0694
  -6.750   0.1986   0.06270   0.05891  -0.1552   0.8816   0.0732
  -6.500   0.1988   0.06182   0.05806  -0.1515   0.8721   0.0742
  -6.250   0.2160   0.05933   0.05555  -0.1536   0.8671   0.0764
  -5.750   0.1997   0.03386   0.02889  -0.1816   0.8473   0.0487
  -5.500   0.2050   0.03093   0.02555  -0.1802   0.8375   0.0459
  -5.250   0.2374   0.02759   0.02168  -0.1831   0.8339   0.0455
  -5.000   0.2741   0.02470   0.01826  -0.1858   0.8312   0.0445
  -4.750   0.2934   0.02335   0.01662  -0.1847   0.8241   0.0444
  -4.500   0.3231   0.02200   0.01497  -0.1852   0.8192   0.0449
  -4.250   0.3584   0.02072   0.01342  -0.1865   0.8159   0.0462
  -4.000   0.3954   0.01954   0.01207  -0.1881   0.8132   0.0482
  -3.750   0.4118   0.01929   0.01189  -0.1861   0.8051   0.0510
  -3.500   0.4436   0.01855   0.01105  -0.1868   0.8006   0.0554
  -3.250   0.4792   0.01777   0.01026  -0.1881   0.7973   0.0613
  -3.000   0.5038   0.01732   0.00985  -0.1876   0.7910   0.0706
  -2.750   0.5327   0.01671   0.00935  -0.1879   0.7853   0.0967
  -2.500   0.5676   0.01607   0.00885  -0.1894   0.7813   0.1426
  -2.250   0.5987   0.01575   0.00865  -0.1901   0.7765   0.1933
  -2.000   0.6228   0.01561   0.00867  -0.1895   0.7694   0.2456
  -1.750   0.6556   0.01527   0.00845  -0.1905   0.7648   0.3048
  -1.500   0.6890   0.01503   0.00829  -0.1915   0.7605   0.3633
  -1.250   0.7108   0.01503   0.00842  -0.1903   0.7528   0.4127
  -1.000   0.7423   0.01483   0.00829  -0.1909   0.7478   0.4683
  -0.750   0.7733   0.01469   0.00823  -0.1912   0.7428   0.5211
  -0.500   0.7954   0.01472   0.00837  -0.1900   0.7353   0.5661
  -0.250   0.8263   0.01456   0.00825  -0.1903   0.7301   0.6148
   0.000   0.8522   0.01453   0.00829  -0.1896   0.7240   0.6586
   0.250   0.8751   0.01450   0.00835  -0.1884   0.7169   0.7017
   0.500   0.9044   0.01432   0.00819  -0.1882   0.7118   0.7486
   0.750   0.9223   0.01434   0.00832  -0.1859   0.7044   0.7960
   1.000   0.9409   0.01416   0.00822  -0.1834   0.6979   0.8544
   1.250   0.9664   0.01384   0.00790  -0.1823   0.6925   1.0000
   1.500   0.9914   0.01401   0.00801  -0.1820   0.6840   1.0000
   1.750   1.0254   0.01402   0.00784  -0.1832   0.6781   1.0000
   2.000   1.0497   0.01420   0.00797  -0.1826   0.6700   1.0000
   2.250   1.0796   0.01425   0.00791  -0.1830   0.6630   1.0000
   2.500   1.1066   0.01439   0.00797  -0.1829   0.6556   1.0000
   2.750   1.1329   0.01450   0.00801  -0.1826   0.6476   1.0000
   3.000   1.1619   0.01462   0.00802  -0.1828   0.6406   1.0000
   3.250   1.1853   0.01478   0.00816  -0.1820   0.6318   1.0000
   3.500   1.2152   0.01489   0.00815  -0.1824   0.6248   1.0000
   3.750   1.2365   0.01509   0.00836  -0.1812   0.6155   1.0000
   4.000   1.2659   0.01522   0.00837  -0.1815   0.6082   1.0000
   4.250   1.2862   0.01545   0.00861  -0.1801   0.5987   1.0000
   4.500   1.3140   0.01562   0.00868  -0.1801   0.5908   1.0000
   4.750   1.3343   0.01586   0.00893  -0.1788   0.5813   1.0000
   5.000   1.3603   0.01607   0.00906  -0.1785   0.5731   1.0000
   5.250   1.3807   0.01632   0.00930  -0.1771   0.5635   1.0000
   5.500   1.4044   0.01659   0.00953  -0.1765   0.5549   1.0000
   5.750   1.4255   0.01684   0.00976  -0.1753   0.5455   1.0000
   6.000   1.4463   0.01716   0.01005  -0.1741   0.5363   1.0000
   6.250   1.4687   0.01743   0.01027  -0.1732   0.5274   1.0000
   6.500   1.4859   0.01779   0.01065  -0.1714   0.5177   1.0000
   6.750   1.5101   0.01810   0.01085  -0.1709   0.5091   1.0000
   7.000   1.5222   0.01848   0.01129  -0.1681   0.4993   1.0000
   7.250   1.5449   0.01883   0.01156  -0.1673   0.4907   1.0000
   7.500   1.5548   0.01925   0.01205  -0.1643   0.4812   1.0000
   7.750   1.5743   0.01966   0.01240  -0.1630   0.4725   1.0000
   8.000   1.5859   0.02013   0.01291  -0.1603   0.4633   1.0000
   8.250   1.6027   0.02061   0.01335  -0.1586   0.4545   1.0000
   8.500   1.6152   0.02112   0.01389  -0.1563   0.4455   1.0000
   8.750   1.6297   0.02168   0.01444  -0.1543   0.4368   1.0000
   9.000   1.6425   0.02225   0.01501  -0.1521   0.4280   1.0000
   9.250   1.6549   0.02289   0.01568  -0.1499   0.4194   1.0000
   9.500   1.6678   0.02352   0.01630  -0.1478   0.4108   1.0000
   9.750   1.6783   0.02426   0.01708  -0.1455   0.4023   1.0000
  10.000   1.6908   0.02497   0.01778  -0.1435   0.3939   1.0000
  10.250   1.6999   0.02582   0.01868  -0.1412   0.3854   1.0000
  10.500   1.7116   0.02661   0.01946  -0.1392   0.3772   1.0000
  10.750   1.7194   0.02758   0.02050  -0.1368   0.3688   1.0000
  11.000   1.7301   0.02848   0.02139  -0.1349   0.3607   1.0000
  11.250   1.7370   0.02958   0.02256  -0.1326   0.3525   1.0000
  11.500   1.7463   0.03060   0.02357  -0.1306   0.3443   1.0000
  11.750   1.7522   0.03183   0.02488  -0.1284   0.3362   1.0000
  12.000   1.7601   0.03300   0.02605  -0.1265   0.3282   1.0000
  12.250   1.7653   0.03438   0.02751  -0.1244   0.3201   1.0000
  12.500   1.7719   0.03570   0.02884  -0.1225   0.3122   1.0000
  12.750   1.7761   0.03725   0.03047  -0.1206   0.3042   1.0000
  13.000   1.7812   0.03876   0.03200  -0.1188   0.2963   1.0000
  13.250   1.7846   0.04047   0.03379  -0.1169   0.2884   1.0000
  13.500   1.7882   0.04221   0.03555  -0.1152   0.2805   1.0000
  13.750   1.7909   0.04412   0.03754  -0.1136   0.2727   1.0000
  14.000   1.7937   0.04605   0.03949  -0.1121   0.2649   1.0000
  14.250   1.7955   0.04818   0.04171  -0.1107   0.2573   1.0000
  14.500   1.7972   0.05035   0.04391  -0.1093   0.2497   1.0000
  14.750   1.7983   0.05268   0.04631  -0.1081   0.2421   1.0000
  15.000   1.7987   0.05512   0.04880  -0.1069   0.2346   1.0000
  15.250   1.7991   0.05766   0.05140  -0.1059   0.2273   1.0000
  15.500   1.7981   0.06040   0.05419  -0.1050   0.2199   1.0000
  15.750   1.7984   0.06308   0.05693  -0.1042   0.2128   1.0000
  16.000   1.7961   0.06615   0.06008  -0.1035   0.2057   1.0000
  16.250   1.7963   0.06897   0.06292  -0.1030   0.1990   1.0000
  16.500   1.7926   0.07236   0.06643  -0.1026   0.1921   1.0000
  16.750   1.7931   0.07521   0.06924  -0.1022   0.1857   1.0000
  17.000   1.7879   0.07898   0.07319  -0.1021   0.1791   1.0000
  17.250   1.7896   0.08171   0.07581  -0.1018   0.1728   1.0000
  17.500   1.7826   0.08590   0.08024  -0.1020   0.1668   1.0000
  17.750   1.7802   0.08936   0.08370  -0.1022   0.1609   1.0000
  18.000   1.7768   0.09307   0.08750  -0.1025   0.1552   1.0000
  18.250   1.7720   0.09703   0.09156  -0.1030   0.1496   1.0000
  18.500   1.7723   0.10012   0.09461  -0.1033   0.1442   1.0000
  18.750   1.7652   0.10460   0.09927  -0.1042   0.1390   1.0000
  19.000   1.7639   0.10801   0.10267  -0.1048   0.1340   1.0000
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