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MH 114 13.02% (mh114-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 114 13.02% (mh114-il)
Reynolds number: 100,000
Max Cl/Cd: 60.75 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh114-il-100000-n5.txt
Download as CSV file: xf-mh114-il-100000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.0345   0.10246   0.09743  -0.0935   0.9290   0.0463
  -8.500  -0.0224   0.09909   0.09406  -0.0965   0.9244   0.0470
  -8.250  -0.0175   0.09193   0.08688  -0.1033   0.9207   0.0300
  -8.000  -0.0111   0.08980   0.08474  -0.1025   0.9127   0.0290
  -7.750   0.0020   0.08623   0.08117  -0.1056   0.9084   0.0287
  -7.500   0.0160   0.08181   0.07675  -0.1107   0.9051   0.0290
  -7.250   0.0136   0.07973   0.07471  -0.1097   0.8949   0.0287
  -7.000   0.0250   0.07564   0.07061  -0.1138   0.8905   0.0287
  -6.750   0.0184   0.07348   0.06850  -0.1126   0.8799   0.0284
  -6.500   0.0322   0.06906   0.06407  -0.1176   0.8751   0.0276
  -6.250   0.0281   0.06592   0.06096  -0.1186   0.8647   0.0270
  -6.000   0.0420   0.05255   0.04738  -0.1369   0.8582   0.0247
  -5.750   0.0428   0.04826   0.04295  -0.1393   0.8475   0.0245
  -5.500   0.0751   0.04042   0.03450  -0.1501   0.8437   0.0242
  -5.250   0.1031   0.03509   0.02844  -0.1556   0.8381   0.0244
  -5.000   0.1321   0.03146   0.02408  -0.1585   0.8323   0.0248
  -4.750   0.1683   0.02930   0.02161  -0.1614   0.8293   0.0258
  -4.500   0.2075   0.02753   0.01945  -0.1643   0.8271   0.0286
  -4.250   0.2321   0.02644   0.01812  -0.1643   0.8210   0.0310
  -4.000   0.2614   0.02529   0.01677  -0.1648   0.8159   0.0336
  -3.750   0.2977   0.02406   0.01536  -0.1666   0.8128   0.0373
  -3.500   0.3363   0.02300   0.01416  -0.1687   0.8104   0.0438
  -3.250   0.3563   0.02264   0.01371  -0.1674   0.8028   0.0504
  -3.000   0.3895   0.02188   0.01294  -0.1686   0.7984   0.0617
  -2.750   0.4274   0.02111   0.01213  -0.1706   0.7954   0.0815
  -2.500   0.4554   0.02067   0.01176  -0.1709   0.7898   0.1085
  -2.250   0.4835   0.02028   0.01148  -0.1712   0.7837   0.1483
  -2.000   0.5192   0.01973   0.01105  -0.1728   0.7800   0.2092
  -1.750   0.5507   0.01938   0.01085  -0.1736   0.7754   0.2764
  -1.500   0.5743   0.01931   0.01092  -0.1730   0.7681   0.3382
  -1.250   0.6084   0.01897   0.01069  -0.1741   0.7639   0.4107
  -1.000   0.6365   0.01885   0.01066  -0.1740   0.7583   0.4743
  -0.750   0.6610   0.01883   0.01072  -0.1732   0.7513   0.5322
  -0.500   0.6939   0.01857   0.01050  -0.1738   0.7471   0.5938
  -0.250   0.7147   0.01863   0.01065  -0.1723   0.7397   0.6455
   0.000   0.7400   0.01851   0.01058  -0.1713   0.7336   0.7004
   0.250   0.7699   0.01819   0.01028  -0.1710   0.7295   0.7612
   0.500   0.7787   0.01831   0.01053  -0.1670   0.7203   0.8230
   0.750   0.8040   0.01787   0.01009  -0.1657   0.7150   1.0000
   1.000   0.8284   0.01812   0.01023  -0.1653   0.7070   1.0000
   1.250   0.8601   0.01816   0.01011  -0.1661   0.7007   1.0000
   1.500   0.8890   0.01828   0.01011  -0.1663   0.6938   1.0000
   1.750   0.9155   0.01844   0.01017  -0.1662   0.6861   1.0000
   2.000   0.9479   0.01846   0.01006  -0.1669   0.6800   1.0000
   2.250   0.9701   0.01873   0.01028  -0.1660   0.6711   1.0000
   2.500   1.0037   0.01870   0.01013  -0.1670   0.6651   1.0000
   2.750   1.0237   0.01903   0.01044  -0.1657   0.6555   1.0000
   3.000   1.0558   0.01904   0.01035  -0.1664   0.6489   1.0000
   3.250   1.0763   0.01936   0.01065  -0.1652   0.6392   1.0000
   3.500   1.1053   0.01945   0.01067  -0.1654   0.6317   1.0000
   3.750   1.1278   0.01972   0.01092  -0.1645   0.6223   1.0000
   4.000   1.1535   0.01991   0.01108  -0.1641   0.6138   1.0000
   4.250   1.1786   0.02011   0.01124  -0.1636   0.6048   1.0000
   4.500   1.2008   0.02040   0.01152  -0.1627   0.5954   1.0000
   4.750   1.2290   0.02053   0.01161  -0.1627   0.5870   1.0000
   5.000   1.2477   0.02092   0.01202  -0.1612   0.5765   1.0000
   5.250   1.2730   0.02114   0.01220  -0.1608   0.5675   1.0000
   5.500   1.2942   0.02146   0.01252  -0.1597   0.5575   1.0000
   5.750   1.3139   0.02182   0.01291  -0.1584   0.5474   1.0000
   6.000   1.3395   0.02205   0.01308  -0.1580   0.5382   1.0000
   6.250   1.3549   0.02251   0.01360  -0.1560   0.5273   1.0000
   6.500   1.3747   0.02291   0.01401  -0.1548   0.5173   1.0000
   6.750   1.3967   0.02325   0.01432  -0.1538   0.5075   1.0000
   7.000   1.4114   0.02379   0.01492  -0.1518   0.4965   1.0000
   7.250   1.4300   0.02425   0.01538  -0.1504   0.4864   1.0000
   7.500   1.4487   0.02472   0.01585  -0.1490   0.4762   1.0000
   7.750   1.4623   0.02535   0.01655  -0.1470   0.4653   1.0000
   8.000   1.4791   0.02591   0.01711  -0.1454   0.4551   1.0000
   8.250   1.4949   0.02650   0.01773  -0.1437   0.4447   1.0000
   8.500   1.5071   0.02725   0.01855  -0.1416   0.4340   1.0000
   8.750   1.5219   0.02793   0.01925  -0.1398   0.4239   1.0000
   9.000   1.5351   0.02869   0.02004  -0.1379   0.4134   1.0000
   9.250   1.5457   0.02958   0.02102  -0.1358   0.4028   1.0000
   9.500   1.5585   0.03041   0.02187  -0.1339   0.3928   1.0000
   9.750   1.5689   0.03137   0.02289  -0.1319   0.3824   1.0000
  10.000   1.5781   0.03243   0.02404  -0.1298   0.3721   1.0000
  10.250   1.5888   0.03344   0.02508  -0.1279   0.3622   1.0000
  10.500   1.5966   0.03465   0.02637  -0.1258   0.3518   1.0000
  10.750   1.6042   0.03592   0.02772  -0.1238   0.3417   1.0000
  11.000   1.6127   0.03715   0.02897  -0.1219   0.3320   1.0000
  11.250   1.6178   0.03866   0.03060  -0.1199   0.3215   1.0000
  11.500   1.6236   0.04018   0.03221  -0.1180   0.3116   1.0000
  11.750   1.6297   0.04169   0.03373  -0.1162   0.3020   1.0000
  12.000   1.6325   0.04354   0.03573  -0.1143   0.2917   1.0000
  12.250   1.6363   0.04536   0.03763  -0.1126   0.2821   1.0000
  12.500   1.6394   0.04727   0.03958  -0.1110   0.2725   1.0000
  12.750   1.6407   0.04946   0.04192  -0.1094   0.2625   1.0000
  13.000   1.6426   0.05164   0.04416  -0.1079   0.2532   1.0000
  13.250   1.6431   0.05402   0.04662  -0.1066   0.2437   1.0000
  13.500   1.6431   0.05658   0.04930  -0.1054   0.2342   1.0000
  13.750   1.6430   0.05917   0.05193  -0.1042   0.2254   1.0000
  14.000   1.6414   0.06207   0.05496  -0.1033   0.2161   1.0000
  14.250   1.6399   0.06504   0.05803  -0.1025   0.2074   1.0000
  14.500   1.6376   0.06816   0.06121  -0.1018   0.1990   1.0000
  14.750   1.6346   0.07153   0.06473  -0.1013   0.1903   1.0000
  15.000   1.6315   0.07491   0.06814  -0.1009   0.1826   1.0000
  15.250   1.6274   0.07861   0.07200  -0.1008   0.1744   1.0000
  15.500   1.6235   0.08231   0.07577  -0.1007   0.1670   1.0000
  15.750   1.6186   0.08627   0.07985  -0.1009   0.1595   1.0000
  16.000   1.6139   0.09024   0.08392  -0.1012   0.1526   1.0000
  16.250   1.6082   0.09448   0.08826  -0.1017   0.1456   1.0000
  16.500   1.6031   0.09867   0.09256  -0.1023   0.1392   1.0000
  16.750   1.5970   0.10312   0.09713  -0.1032   0.1327   1.0000
  17.000   1.5917   0.10746   0.10156  -0.1042   0.1267   1.0000
  17.250   1.5853   0.11210   0.10634  -0.1054   0.1207   1.0000
  17.500   1.5803   0.11646   0.11073  -0.1067   0.1154   1.0000
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