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MH 113 14.62% (mh113-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 113 14.62% (mh113-il)
Reynolds number: 100,000
Max Cl/Cd: 50.07 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh113-il-100000.txt
Download as CSV file: xf-mh113-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.1182   0.12103   0.11648  -0.0714   0.9363   0.0923
  -8.250  -0.1329   0.12073   0.11623  -0.0798   0.9303   0.0942
  -8.000  -0.1296   0.11715   0.11270  -0.0766   0.9226   0.0950
  -7.750  -0.0960   0.11247   0.10797  -0.0764   0.9196   0.0975
  -7.500  -0.0757   0.10925   0.10474  -0.0793   0.9161   0.1010
  -7.250  -0.0839   0.10812   0.10366  -0.0780   0.9074   0.1038
  -7.000  -0.1049   0.10780   0.10339  -0.0822   0.8995   0.1070
  -6.750  -0.1370   0.10836   0.10403  -0.0793   0.8876   0.1074
  -6.500  -0.0967   0.10218   0.09783  -0.0794   0.8860   0.1100
  -6.250  -0.0681   0.09885   0.09448  -0.0813   0.8830   0.1153
  -6.000  -0.0906   0.09880   0.09449  -0.0768   0.8723   0.1173
  -5.750  -0.1107   0.09697   0.09269  -0.0871   0.8624   0.1219
  -5.500  -0.1232   0.09451   0.09029  -0.0858   0.8528   0.1229
  -5.250  -0.0936   0.09194   0.08771  -0.0790   0.8508   0.1268
  -5.000  -0.0709   0.08836   0.08410  -0.0856   0.8468   0.1351
  -4.750  -0.0925   0.08557   0.08132  -0.0917   0.8338   0.1390
  -4.500  -0.0677   0.08299   0.07876  -0.0877   0.8313   0.1418
  -4.250  -0.0667   0.08065   0.07627  -0.0982   0.8192   0.1540
  -4.000  -0.0477   0.07671   0.07239  -0.0967   0.8157   0.1565
  -3.750   0.0530   0.05236   0.04638  -0.1339   0.8151   0.0833
  -3.500   0.0560   0.05340   0.04778  -0.1299   0.8066   0.0872
  -3.250   0.1204   0.04585   0.03902  -0.1406   0.8035   0.0761
  -3.000   0.1687   0.04324   0.03582  -0.1449   0.7999   0.0784
  -2.750   0.2215   0.04071   0.03267  -0.1491   0.7975   0.0802
  -2.500   0.2377   0.04045   0.03208  -0.1480   0.7887   0.0818
  -2.250   0.2741   0.03919   0.03079  -0.1495   0.7837   0.0874
  -2.000   0.3199   0.03790   0.02941  -0.1520   0.7808   0.0999
  -1.750   0.3358   0.03797   0.02944  -0.1507   0.7721   0.1103
  -1.500   0.3708   0.03723   0.02884  -0.1519   0.7667   0.1421
  -1.250   0.4179   0.03613   0.02798  -0.1547   0.7639   0.2104
  -1.000   0.4304   0.03670   0.02873  -0.1532   0.7542   0.2577
  -0.750   0.4666   0.03614   0.02850  -0.1544   0.7492   0.3422
  -0.500   0.5106   0.03532   0.02798  -0.1563   0.7466   0.4422
  -0.250   0.5167   0.03634   0.02918  -0.1536   0.7356   0.4954
   0.000   0.5531   0.03581   0.02886  -0.1540   0.7315   0.5845
   0.250   0.5927   0.03494   0.02815  -0.1542   0.7291   0.6746
   0.500   0.6301   0.03376   0.02715  -0.1535   0.7276   0.7676
   0.750   0.6141   0.03525   0.02884  -0.1472   0.7135   0.8344
   1.000   0.6413   0.03498   0.02850  -0.1468   0.7077   1.0000
   1.250   0.7135   0.03303   0.02619  -0.1522   0.7102   1.0000
   1.500   0.7109   0.03498   0.02806  -0.1492   0.6959   1.0000
   1.750   0.7164   0.03663   0.02961  -0.1471   0.6839   1.0000
   2.000   0.7596   0.03593   0.02873  -0.1487   0.6806   1.0000
   2.250   0.8093   0.03473   0.02736  -0.1508   0.6791   1.0000
   2.500   0.8625   0.03339   0.02586  -0.1535   0.6781   1.0000
   2.750   0.9184   0.03203   0.02436  -0.1567   0.6769   1.0000
   3.000   0.9082   0.03412   0.02644  -0.1521   0.6626   1.0000
   3.250   0.9634   0.03267   0.02487  -0.1551   0.6613   1.0000
   3.500   1.0240   0.03117   0.02325  -0.1591   0.6601   1.0000
   3.750   1.0100   0.03322   0.02531  -0.1536   0.6460   1.0000
   4.000   1.0700   0.03163   0.02363  -0.1574   0.6445   1.0000
   4.250   1.0592   0.03361   0.02563  -0.1524   0.6312   1.0000
   4.500   1.1182   0.03199   0.02392  -0.1560   0.6291   1.0000
   4.750   1.1856   0.03031   0.02216  -0.1612   0.6271   1.0000
   5.000   1.1699   0.03219   0.02408  -0.1550   0.6142   1.0000
   5.250   1.2364   0.03052   0.02234  -0.1601   0.6114   1.0000
   5.500   1.2280   0.03209   0.02395  -0.1549   0.5999   1.0000
   5.750   1.2895   0.03066   0.02244  -0.1593   0.5957   1.0000
   6.000   1.3025   0.03131   0.02311  -0.1570   0.5867   1.0000
   6.250   1.3438   0.03078   0.02255  -0.1587   0.5797   1.0000
   6.500   1.3842   0.03042   0.02215  -0.1604   0.5729   1.0000
   6.750   1.3985   0.03093   0.02268  -0.1583   0.5634   1.0000
   7.000   1.4402   0.03055   0.02227  -0.1601   0.5562   1.0000
   7.250   1.4525   0.03114   0.02290  -0.1577   0.5466   1.0000
   7.500   1.4861   0.03110   0.02282  -0.1585   0.5386   1.0000
   7.750   1.5045   0.03146   0.02322  -0.1569   0.5293   1.0000
   8.000   1.5272   0.03181   0.02357  -0.1561   0.5207   1.0000
   8.250   1.5543   0.03191   0.02366  -0.1559   0.5117   1.0000
   8.500   1.5656   0.03264   0.02446  -0.1534   0.5026   1.0000
   8.750   1.6039   0.03243   0.02419  -0.1549   0.4939   1.0000
   9.000   1.6020   0.03359   0.02545  -0.1505   0.4846   1.0000
   9.250   1.6539   0.03303   0.02478  -0.1540   0.4757   1.0000
   9.500   1.6363   0.03466   0.02658  -0.1475   0.4665   1.0000
   9.750   1.6890   0.03412   0.02590  -0.1510   0.4575   1.0000
  10.000   1.6683   0.03586   0.02784  -0.1442   0.4485   1.0000
  10.250   1.7080   0.03571   0.02761  -0.1458   0.4395   1.0000
  10.500   1.6981   0.03720   0.02925  -0.1408   0.4306   1.0000
  10.750   1.7259   0.03746   0.02947  -0.1408   0.4217   1.0000
  11.000   1.7266   0.03865   0.03078  -0.1374   0.4128   1.0000
  11.250   1.7423   0.03939   0.03154  -0.1359   0.4039   1.0000
  11.500   1.7539   0.04020   0.03238  -0.1340   0.3949   1.0000
  11.750   1.7570   0.04155   0.03382  -0.1312   0.3864   1.0000
  12.000   1.7803   0.04185   0.03410  -0.1307   0.3771   1.0000
  12.250   1.7688   0.04398   0.03639  -0.1266   0.3690   1.0000
  12.500   1.8067   0.04360   0.03589  -0.1275   0.3593   1.0000
  12.750   1.7782   0.04670   0.03925  -0.1221   0.3518   1.0000
  13.000   1.8215   0.04599   0.03838  -0.1234   0.3419   1.0000
  13.250   1.7851   0.04977   0.04247  -0.1178   0.3348   1.0000
  13.500   1.8233   0.04920   0.04175  -0.1185   0.3251   1.0000
  13.750   1.7893   0.05321   0.04606  -0.1137   0.3181   1.0000
  14.000   1.8234   0.05277   0.04549  -0.1140   0.3086   1.0000
  14.250   1.7904   0.05709   0.05010  -0.1099   0.3017   1.0000
  14.500   1.8221   0.05673   0.04962  -0.1100   0.2924   1.0000
  14.750   1.7887   0.06145   0.05463  -0.1065   0.2857   1.0000
  15.000   1.8193   0.06106   0.05411  -0.1064   0.2765   1.0000
  15.250   1.7839   0.06638   0.05973  -0.1036   0.2701   1.0000
  15.500   1.8163   0.06570   0.05891  -0.1034   0.2609   1.0000
  15.750   1.7770   0.07185   0.06539  -0.1011   0.2550   1.0000
  16.000   1.8135   0.07062   0.06399  -0.1009   0.2458   1.0000
  16.250   1.7692   0.07778   0.07151  -0.0993   0.2405   1.0000
  16.500   1.8113   0.07574   0.06924  -0.0990   0.2310   1.0000
  16.750   1.7617   0.08397   0.07787  -0.0981   0.2264   1.0000
  17.000   1.7873   0.08353   0.07732  -0.0975   0.2179   1.0000
  17.250   1.7572   0.09006   0.08410  -0.0974   0.2127   1.0000
  17.500   1.7324   0.09619   0.09044  -0.0978   0.2069   1.0000
  17.750   1.7575   0.09571   0.08988  -0.0971   0.1993   1.0000
  18.000   1.7048   0.10616   0.10068  -0.0991   0.1953   1.0000
  18.250   1.7637   0.10066   0.09490  -0.0971   0.1861   1.0000
  18.500   1.7008   0.11288   0.10754  -0.1002   0.1832   1.0000
  18.750   1.2580   0.21520   0.20995  -0.1558   0.1672   1.0000
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