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MH 115 11.06% (mh115-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 115 11.06% (mh115-il)
Reynolds number: 100,000
Max Cl/Cd: 64.91 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh115-il-100000-n5.txt
Download as CSV file: xf-mh115-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 115  11.06%                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.1764   0.09154   0.08684  -0.0659   0.9612   0.0235
  -7.500  -0.1677   0.08785   0.08316  -0.0688   0.9533   0.0226
  -7.000  -0.1576   0.07791   0.07327  -0.0780   0.9352   0.0204
  -6.750  -0.1387   0.07568   0.07105  -0.0808   0.9296   0.0223
  -6.500  -0.1274   0.07115   0.06653  -0.0859   0.9202   0.0223
  -6.250  -0.1138   0.06630   0.06167  -0.0920   0.9115   0.0229
  -6.000  -0.0921   0.05948   0.05479  -0.1020   0.9044   0.0225
  -5.750  -0.0720   0.05126   0.04641  -0.1125   0.8949   0.0221
  -5.500  -0.0368   0.04055   0.03511  -0.1261   0.8893   0.0220
  -5.250  -0.0008   0.03380   0.02754  -0.1337   0.8843   0.0221
  -5.000   0.0306   0.02993   0.02301  -0.1369   0.8779   0.0228
  -4.750   0.0702   0.02656   0.01890  -0.1404   0.8747   0.0244
  -4.500   0.1089   0.02478   0.01680  -0.1431   0.8720   0.0277
  -4.250   0.1343   0.02350   0.01518  -0.1429   0.8641   0.0314
  -4.000   0.1694   0.02226   0.01378  -0.1445   0.8599   0.0363
  -3.750   0.2072   0.02113   0.01249  -0.1465   0.8569   0.0451
  -3.250   0.2672   0.01967   0.01089  -0.1475   0.8443   0.0688
  -3.000   0.3025   0.01892   0.01013  -0.1490   0.8402   0.0874
  -2.750   0.3292   0.01848   0.00969  -0.1489   0.8323   0.1108
  -2.500   0.3644   0.01789   0.00916  -0.1504   0.8279   0.1494
  -2.250   0.3930   0.01753   0.00891  -0.1507   0.8209   0.1964
  -2.000   0.4238   0.01716   0.00866  -0.1513   0.8148   0.2553
  -1.750   0.4590   0.01673   0.00834  -0.1527   0.8105   0.3258
  -1.500   0.4833   0.01660   0.00836  -0.1521   0.8018   0.3910
  -1.250   0.5164   0.01626   0.00816  -0.1529   0.7967   0.4708
  -1.000   0.5414   0.01614   0.00818  -0.1521   0.7886   0.5451
  -0.750   0.5704   0.01589   0.00807  -0.1519   0.7825   0.6253
  -0.500   0.5934   0.01576   0.00807  -0.1504   0.7749   0.7024
  -0.250   0.6151   0.01553   0.00795  -0.1485   0.7679   0.7856
   0.000   0.6339   0.01525   0.00779  -0.1458   0.7603   0.9097
   0.250   0.6664   0.01522   0.00760  -0.1466   0.7528   1.0000
   0.500   0.6961   0.01532   0.00754  -0.1470   0.7452   1.0000
   0.750   0.7259   0.01542   0.00749  -0.1473   0.7374   1.0000
   1.000   0.7545   0.01554   0.00749  -0.1475   0.7293   1.0000
   1.250   0.7841   0.01563   0.00746  -0.1477   0.7214   1.0000
   1.500   0.8113   0.01580   0.00754  -0.1476   0.7127   1.0000
   1.750   0.8414   0.01587   0.00751  -0.1479   0.7049   1.0000
   2.000   0.8670   0.01607   0.00766  -0.1475   0.6954   1.0000
   2.250   0.8978   0.01614   0.00762  -0.1479   0.6878   1.0000
   2.500   0.9221   0.01636   0.00782  -0.1472   0.6774   1.0000
   2.750   0.9494   0.01652   0.00792  -0.1471   0.6683   1.0000
   3.000   0.9771   0.01666   0.00803  -0.1469   0.6589   1.0000
   3.250   1.0018   0.01688   0.00823  -0.1463   0.6484   1.0000
   3.500   1.0289   0.01704   0.00835  -0.1461   0.6387   1.0000
   3.750   1.0550   0.01722   0.00850  -0.1457   0.6282   1.0000
   4.000   1.0791   0.01745   0.00877  -0.1450   0.6168   1.0000
   4.250   1.1045   0.01766   0.00897  -0.1445   0.6057   1.0000
   4.500   1.1305   0.01785   0.00912  -0.1441   0.5947   1.0000
   4.750   1.1543   0.01810   0.00941  -0.1433   0.5824   1.0000
   5.000   1.1775   0.01837   0.00970  -0.1424   0.5696   1.0000
   5.250   1.2009   0.01865   0.00999  -0.1416   0.5567   1.0000
   5.500   1.2240   0.01893   0.01028  -0.1407   0.5435   1.0000
   5.750   1.2467   0.01923   0.01061  -0.1398   0.5299   1.0000
   6.000   1.2689   0.01955   0.01094  -0.1387   0.5157   1.0000
   6.250   1.2903   0.01991   0.01131  -0.1376   0.5012   1.0000
   6.500   1.3109   0.02029   0.01172  -0.1363   0.4861   1.0000
   6.750   1.3308   0.02071   0.01215  -0.1350   0.4706   1.0000
   7.000   1.3498   0.02116   0.01262  -0.1335   0.4547   1.0000
   7.250   1.3678   0.02165   0.01314  -0.1319   0.4385   1.0000
   7.500   1.3849   0.02218   0.01369  -0.1301   0.4219   1.0000
   7.750   1.4008   0.02275   0.01427  -0.1282   0.4053   1.0000
   8.000   1.4150   0.02336   0.01488  -0.1260   0.3889   1.0000
   8.250   1.4280   0.02402   0.01557  -0.1237   0.3727   1.0000
   8.500   1.4402   0.02474   0.01630  -0.1213   0.3568   1.0000
   8.750   1.4516   0.02552   0.01710  -0.1189   0.3411   1.0000
   9.000   1.4622   0.02636   0.01796  -0.1165   0.3257   1.0000
   9.250   1.4723   0.02727   0.01890  -0.1141   0.3109   1.0000
   9.500   1.4815   0.02825   0.01994  -0.1116   0.2963   1.0000
   9.750   1.4901   0.02931   0.02104  -0.1093   0.2821   1.0000
  10.000   1.4981   0.03045   0.02223  -0.1069   0.2683   1.0000
  10.250   1.5051   0.03169   0.02352  -0.1046   0.2547   1.0000
  10.500   1.5115   0.03303   0.02491  -0.1024   0.2416   1.0000
  10.750   1.5172   0.03448   0.02641  -0.1002   0.2291   1.0000
  11.000   1.5216   0.03606   0.02805  -0.0981   0.2169   1.0000
  11.250   1.5259   0.03774   0.02980  -0.0961   0.2049   1.0000
  11.500   1.5303   0.03949   0.03164  -0.0942   0.1934   1.0000
  11.750   1.5335   0.04140   0.03364  -0.0925   0.1824   1.0000
  12.000   1.5353   0.04350   0.03579  -0.0908   0.1722   1.0000
  12.250   1.5364   0.04574   0.03810  -0.0893   0.1624   1.0000
  12.500   1.5383   0.04801   0.04051  -0.0879   0.1525   1.0000
  12.750   1.5383   0.05054   0.04311  -0.0867   0.1437   1.0000
  13.000   1.5369   0.05328   0.04592  -0.0856   0.1352   1.0000
  13.250   1.5368   0.05602   0.04880  -0.0847   0.1265   1.0000
  13.500   1.5336   0.05918   0.05200  -0.0840   0.1193   1.0000
  13.750   1.5317   0.06233   0.05530  -0.0835   0.1112   1.0000
  14.000   1.5283   0.06576   0.05883  -0.0832   0.1043   1.0000
  14.250   1.5240   0.06945   0.06263  -0.0831   0.0975   1.0000
  14.500   1.5200   0.07323   0.06654  -0.0832   0.0911   1.0000
  14.750   1.5139   0.07743   0.07084  -0.0836   0.0851   1.0000
  15.000   1.5084   0.08167   0.07524  -0.0842   0.0794   1.0000
  15.250   1.5012   0.08631   0.08001  -0.0851   0.0739   1.0000
  15.500   1.4939   0.09111   0.08493  -0.0862   0.0691   1.0000
  15.750   1.4863   0.09609   0.09007  -0.0875   0.0641   1.0000
  16.000   1.4760   0.10160   0.09564  -0.0893   0.0604   1.0000
  16.250   1.4691   0.10675   0.10101  -0.0910   0.0555   1.0000
  16.500   1.4585   0.11262   0.10697  -0.0933   0.0521   1.0000
  16.750   1.4501   0.11821   0.11271  -0.0956   0.0485   1.0000
  17.000   1.4410   0.12405   0.11870  -0.0982   0.0450   1.0000
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