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MH 114 13.02% (mh114-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 114 13.02% (mh114-il)
Reynolds number: 100,000
Max Cl/Cd: 56.17 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh114-il-100000.txt
Download as CSV file: xf-mh114-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 114  13.02%                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.1785   0.11174   0.10749  -0.0617   0.9413   0.0817
  -7.000  -0.1963   0.11154   0.10736  -0.0657   0.9328   0.0831
  -6.750  -0.2092   0.11023   0.10611  -0.0710   0.9228   0.0835
  -6.500  -0.1587   0.10316   0.09898  -0.0656   0.9236   0.0880
  -6.250  -0.1556   0.10121   0.09705  -0.0658   0.9171   0.0917
  -6.000  -0.1622   0.09960   0.09548  -0.0664   0.9085   0.0943
  -5.750  -0.1766   0.09804   0.09397  -0.0745   0.8967   0.0969
  -5.500  -0.1618   0.09365   0.08960  -0.0734   0.8927   0.0992
  -5.250  -0.1342   0.09057   0.08649  -0.0734   0.8899   0.1055
  -5.000  -0.1445   0.08898   0.08494  -0.0741   0.8789   0.1094
  -4.750  -0.1187   0.08354   0.07948  -0.0835   0.8743   0.1149
  -4.500  -0.1249   0.08241   0.07839  -0.0793   0.8649   0.1171
  -4.250  -0.0856   0.07612   0.07193  -0.0952   0.8595   0.1293
  -4.000  -0.0587   0.07337   0.06887  -0.1055   0.8503   0.1438
  -3.750  -0.0475   0.06979   0.06549  -0.1017   0.8458   0.1456
  -3.500   0.0645   0.04920   0.04330  -0.1331   0.8458   0.0722
  -3.250   0.1232   0.04384   0.03734  -0.1406   0.8438   0.0650
  -3.000   0.1838   0.04020   0.03288  -0.1473   0.8420   0.0677
  -2.750   0.2018   0.03913   0.03139  -0.1465   0.8327   0.0687
  -2.500   0.2482   0.03710   0.02898  -0.1498   0.8291   0.0755
  -2.250   0.2979   0.03539   0.02706  -0.1532   0.8266   0.0882
  -2.000   0.3132   0.03529   0.02688  -0.1516   0.8171   0.1002
  -1.750   0.3557   0.03418   0.02584  -0.1540   0.8130   0.1318
  -1.500   0.4053   0.03289   0.02483  -0.1575   0.8106   0.2014
  -1.250   0.4181   0.03314   0.02536  -0.1558   0.8003   0.2666
  -1.000   0.4614   0.03230   0.02501  -0.1583   0.7965   0.4070
  -0.750   0.5065   0.03155   0.02460  -0.1603   0.7941   0.5402
  -0.500   0.5120   0.03234   0.02558  -0.1570   0.7825   0.6055
  -0.250   0.5482   0.03164   0.02508  -0.1568   0.7793   0.7113
   0.000   0.5499   0.03225   0.02588  -0.1522   0.7685   0.7859
   0.250   0.5754   0.03129   0.02502  -0.1501   0.7641   1.0000
   0.500   0.6292   0.03070   0.02407  -0.1542   0.7621   1.0000
   0.750   0.6389   0.03189   0.02512  -0.1524   0.7497   1.0000
   1.000   0.6876   0.03122   0.02420  -0.1551   0.7472   1.0000
   1.250   0.7393   0.03032   0.02310  -0.1582   0.7458   1.0000
   1.500   0.7444   0.03166   0.02436  -0.1555   0.7326   1.0000
   1.750   0.7950   0.03067   0.02321  -0.1582   0.7309   1.0000
   2.000   0.8474   0.02967   0.02206  -0.1613   0.7292   1.0000
   2.500   0.8853   0.03075   0.02302  -0.1588   0.7105   1.0000
   2.750   0.9095   0.03099   0.02320  -0.1582   0.7019   1.0000
   3.000   0.9630   0.02980   0.02193  -0.1613   0.6999   1.0000
   3.250   1.0201   0.02855   0.02060  -0.1652   0.6981   1.0000
   3.500   1.0231   0.02968   0.02173  -0.1615   0.6854   1.0000
   3.750   1.0797   0.02840   0.02038  -0.1653   0.6830   1.0000
   4.000   1.0872   0.02934   0.02133  -0.1622   0.6712   1.0000
   4.250   1.1415   0.02813   0.02008  -0.1657   0.6679   1.0000
   4.500   1.1547   0.02881   0.02077  -0.1634   0.6570   1.0000
   4.750   1.2054   0.02776   0.01968  -0.1663   0.6524   1.0000
   5.000   1.2227   0.02823   0.02019  -0.1646   0.6421   1.0000
   5.250   1.2709   0.02733   0.01925  -0.1672   0.6363   1.0000
   5.500   1.2874   0.02782   0.01978  -0.1654   0.6256   1.0000
   5.750   1.3378   0.02690   0.01881  -0.1684   0.6194   1.0000
   6.000   1.3506   0.02751   0.01949  -0.1660   0.6080   1.0000
   6.250   1.3922   0.02702   0.01895  -0.1678   0.6001   1.0000
   6.500   1.4153   0.02721   0.01919  -0.1668   0.5894   1.0000
   6.750   1.4350   0.02758   0.01961  -0.1654   0.5786   1.0000
   7.000   1.4807   0.02702   0.01897  -0.1679   0.5699   1.0000
   7.250   1.4932   0.02761   0.01965  -0.1654   0.5580   1.0000
   7.500   1.5129   0.02800   0.02009  -0.1640   0.5468   1.0000
   7.750   1.5471   0.02791   0.01996  -0.1648   0.5365   1.0000
   8.000   1.5685   0.02822   0.02031  -0.1636   0.5249   1.0000
   8.250   1.5823   0.02882   0.02100  -0.1613   0.5131   1.0000
   8.500   1.6058   0.02913   0.02132  -0.1606   0.5017   1.0000
   8.750   1.6389   0.02918   0.02131  -0.1612   0.4904   1.0000
   9.000   1.6472   0.02991   0.02215  -0.1581   0.4783   1.0000
   9.250   1.6598   0.03058   0.02289  -0.1557   0.4666   1.0000
   9.500   1.6808   0.03100   0.02334  -0.1546   0.4549   1.0000
   9.750   1.7084   0.03128   0.02356  -0.1545   0.4428   1.0000
  10.000   1.7075   0.03220   0.02462  -0.1500   0.4314   1.0000
  10.250   1.7161   0.03299   0.02548  -0.1471   0.4200   1.0000
  10.500   1.7334   0.03356   0.02606  -0.1456   0.4081   1.0000
  10.750   1.7545   0.03403   0.02648  -0.1446   0.3958   1.0000
  11.000   1.7470   0.03532   0.02795  -0.1396   0.3850   1.0000
  11.250   1.7534   0.03631   0.02900  -0.1367   0.3736   1.0000
  11.500   1.7668   0.03708   0.02976  -0.1348   0.3618   1.0000
  11.750   1.7743   0.03804   0.03077  -0.1322   0.3500   1.0000
  12.000   1.7686   0.03964   0.03252  -0.1282   0.3392   1.0000
  12.250   1.7734   0.04089   0.03381  -0.1256   0.3280   1.0000
  12.500   1.7838   0.04191   0.03480  -0.1237   0.3162   1.0000
  12.750   1.7790   0.04368   0.03670  -0.1203   0.3053   1.0000
  13.000   1.7755   0.04558   0.03872  -0.1174   0.2947   1.0000
  13.250   1.7797   0.04710   0.04026  -0.1152   0.2836   1.0000
  13.500   1.7850   0.04857   0.04170  -0.1133   0.2723   1.0000
  13.750   1.7725   0.05132   0.04466  -0.1102   0.2625   1.0000
  14.000   1.7721   0.05339   0.04678  -0.1082   0.2521   1.0000
  14.250   1.7780   0.05502   0.04834  -0.1066   0.2411   1.0000
  14.500   1.7639   0.05829   0.05185  -0.1042   0.2321   1.0000
  14.750   1.7613   0.06083   0.05444  -0.1026   0.2224   1.0000
  15.000   1.7662   0.06272   0.05625  -0.1014   0.2119   1.0000
  15.250   1.7503   0.06667   0.06047  -0.0997   0.2036   1.0000
  15.500   1.7484   0.06943   0.06326  -0.0986   0.1945   1.0000
  15.750   1.7470   0.07212   0.06595  -0.0977   0.1852   1.0000
  16.000   1.7342   0.07635   0.07039  -0.0969   0.1775   1.0000
  16.250   1.7369   0.07878   0.07275  -0.0962   0.1684   1.0000
  16.500   1.7223   0.08341   0.07761  -0.0959   0.1614   1.0000
  16.750   1.7209   0.08652   0.08074  -0.0956   0.1534   1.0000
  17.000   1.7120   0.09064   0.08497  -0.0956   0.1462   1.0000
  17.250   1.7060   0.09453   0.08896  -0.0957   0.1392   1.0000
  17.500   1.7011   0.09821   0.09269  -0.0960   0.1321   1.0000
  17.750   1.6921   0.10272   0.09734  -0.0967   0.1261   1.0000
  18.000   1.6867   0.10663   0.10133  -0.0974   0.1196   1.0000
  18.250   1.6794   0.11101   0.10583  -0.0983   0.1139   1.0000
  18.500   1.6685   0.11601   0.11099  -0.0998   0.1087   1.0000
  18.750   1.6692   0.11911   0.11408  -0.1005   0.1026   1.0000
  19.000   1.6511   0.12557   0.12081  -0.1030   0.0988   1.0000
  19.250   1.6622   0.12680   0.12186  -0.1030   0.0919   1.0000
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