Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

MH 113 14.62% (mh113-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: MH 113 14.62% (mh113-il)
Reynolds number: 500,000
Max Cl/Cd: 124.29 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh113-il-500000.txt
Download as CSV file: xf-mh113-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500   0.1587   0.09450   0.09197  -0.1304   0.9341   0.0248
 -11.250   0.1731   0.09053   0.08796  -0.1341   0.9304   0.0258
 -11.000   0.1622   0.08440   0.08181  -0.1392   0.9224   0.0268
 -10.750   0.1825   0.08142   0.07879  -0.1407   0.9167   0.0271
 -10.500   0.1993   0.07907   0.07640  -0.1417   0.9090   0.0275
 -10.250   0.2117   0.07629   0.07357  -0.1432   0.9012   0.0279
 -10.000   0.2210   0.07367   0.07092  -0.1443   0.8933   0.0287
  -9.750   0.1595   0.08367   0.08097  -0.1452   0.9245   0.0278
  -9.500   0.1818   0.08046   0.07771  -0.1498   0.9174   0.0286
  -9.250   0.1978   0.07728   0.07448  -0.1536   0.9081   0.0295
  -9.000   0.1914   0.07032   0.06746  -0.1608   0.8947   0.0313
  -8.750   0.2076   0.06909   0.06618  -0.1607   0.8861   0.0316
  -8.500   0.2230   0.06768   0.06473  -0.1612   0.8781   0.0322
  -8.250   0.2302   0.06550   0.06252  -0.1618   0.8686   0.0327
  -8.000   0.2362   0.06319   0.06017  -0.1627   0.8600   0.0337
  -7.750   0.1986   0.05404   0.05100  -0.1687   0.8464   0.0361
  -7.500   0.2028   0.05281   0.04979  -0.1672   0.8386   0.0363
  -7.250   0.0987   0.02386   0.01933  -0.1899   0.8204   0.0227
  -7.000   0.1188   0.02128   0.01641  -0.1908   0.8153   0.0224
  -6.750   0.1416   0.01933   0.01412  -0.1913   0.8103   0.0223
  -6.500   0.1654   0.01787   0.01240  -0.1914   0.8048   0.0224
  -6.250   0.1916   0.01674   0.01101  -0.1916   0.8000   0.0226
  -6.000   0.2200   0.01593   0.00995  -0.1920   0.7955   0.0228
  -5.750   0.2452   0.01506   0.00896  -0.1918   0.7903   0.0231
  -5.500   0.2714   0.01413   0.00798  -0.1918   0.7853   0.0235
  -5.250   0.2996   0.01358   0.00737  -0.1921   0.7806   0.0241
  -5.000   0.3271   0.01317   0.00691  -0.1921   0.7759   0.0249
  -4.750   0.3542   0.01279   0.00648  -0.1920   0.7706   0.0260
  -4.500   0.3824   0.01246   0.00604  -0.1921   0.7656   0.0268
  -4.250   0.4115   0.01190   0.00544  -0.1926   0.7610   0.0279
  -4.000   0.4385   0.01157   0.00512  -0.1924   0.7557   0.0292
  -3.750   0.4666   0.01129   0.00479  -0.1925   0.7504   0.0308
  -3.500   0.4962   0.01097   0.00441  -0.1929   0.7456   0.0332
  -3.250   0.5241   0.01072   0.00415  -0.1929   0.7403   0.0369
  -3.000   0.5522   0.01045   0.00391  -0.1930   0.7347   0.0465
  -2.750   0.5816   0.01011   0.00366  -0.1934   0.7296   0.0790
  -2.500   0.6099   0.00994   0.00355  -0.1936   0.7243   0.1074
  -2.250   0.6375   0.00978   0.00347  -0.1936   0.7184   0.1371
  -2.000   0.6661   0.00965   0.00339  -0.1938   0.7130   0.1722
  -1.750   0.6943   0.00952   0.00336  -0.1939   0.7074   0.2135
  -1.500   0.7218   0.00938   0.00335  -0.1939   0.7013   0.2628
  -1.250   0.7503   0.00928   0.00333  -0.1941   0.6956   0.3125
  -1.000   0.7780   0.00921   0.00335  -0.1941   0.6897   0.3564
  -0.750   0.8052   0.00914   0.00336  -0.1940   0.6831   0.3978
  -0.500   0.8334   0.00913   0.00337  -0.1941   0.6772   0.4404
  -0.250   0.8602   0.00908   0.00343  -0.1939   0.6706   0.4830
   0.000   0.8872   0.00907   0.00346  -0.1937   0.6639   0.5230
   0.250   0.9144   0.00909   0.00352  -0.1935   0.6576   0.5618
   0.500   0.9407   0.00908   0.00359  -0.1931   0.6503   0.5982
   0.750   0.9674   0.00913   0.00364  -0.1929   0.6436   0.6344
   1.000   0.9931   0.00913   0.00373  -0.1924   0.6363   0.6702
   1.250   1.0186   0.00917   0.00380  -0.1919   0.6289   0.7071
   1.500   1.0436   0.00919   0.00390  -0.1912   0.6217   0.7457
   1.750   1.0673   0.00921   0.00400  -0.1903   0.6139   0.7889
   2.000   1.0888   0.00922   0.00409  -0.1888   0.6066   0.8420
   2.250   1.1033   0.00906   0.00409  -0.1857   0.5988   0.9624
   2.500   1.1298   0.00922   0.00415  -0.1855   0.5910   1.0000
   2.750   1.1551   0.00935   0.00425  -0.1851   0.5824   1.0000
   3.000   1.1798   0.00954   0.00436  -0.1845   0.5745   1.0000
   3.250   1.2043   0.00969   0.00448  -0.1839   0.5657   1.0000
   3.500   1.2280   0.00990   0.00461  -0.1832   0.5575   1.0000
   3.750   1.2516   0.01007   0.00475  -0.1824   0.5485   1.0000
   4.000   1.2743   0.01029   0.00491  -0.1815   0.5400   1.0000
   4.250   1.2967   0.01049   0.00507  -0.1805   0.5309   1.0000
   4.500   1.3175   0.01072   0.00525  -0.1792   0.5223   1.0000
   4.750   1.3376   0.01093   0.00543  -0.1778   0.5131   1.0000
   5.000   1.3572   0.01118   0.00564  -0.1763   0.5044   1.0000
   5.250   1.3762   0.01145   0.00586  -0.1747   0.4952   1.0000
   5.500   1.3957   0.01172   0.00611  -0.1733   0.4864   1.0000
   5.750   1.4136   0.01204   0.00638  -0.1715   0.4771   1.0000
   6.000   1.4327   0.01232   0.00665  -0.1701   0.4682   1.0000
   6.250   1.4496   0.01270   0.00697  -0.1682   0.4592   1.0000
   6.500   1.4683   0.01301   0.00728  -0.1667   0.4502   1.0000
   7.000   1.5026   0.01377   0.00800  -0.1633   0.4325   1.0000
   7.250   1.5178   0.01425   0.00843  -0.1614   0.4238   1.0000
   7.500   1.5352   0.01465   0.00884  -0.1598   0.4149   1.0000
   7.750   1.5499   0.01517   0.00932  -0.1578   0.4065   1.0000
   8.000   1.5665   0.01563   0.00979  -0.1562   0.3979   1.0000
   8.250   1.5806   0.01621   0.01034  -0.1542   0.3897   1.0000
   8.500   1.5965   0.01673   0.01087  -0.1526   0.3813   1.0000
   8.750   1.6098   0.01739   0.01150  -0.1506   0.3732   1.0000
   9.000   1.6249   0.01797   0.01211  -0.1490   0.3649   1.0000
   9.250   1.6374   0.01871   0.01283  -0.1470   0.3571   1.0000
   9.500   1.6519   0.01937   0.01351  -0.1454   0.3488   1.0000
   9.750   1.6634   0.02022   0.01432  -0.1434   0.3411   1.0000
  10.000   1.6775   0.02094   0.01508  -0.1418   0.3329   1.0000
  10.250   1.6876   0.02190   0.01602  -0.1398   0.3252   1.0000
  10.500   1.7015   0.02269   0.01685  -0.1384   0.3174   1.0000
  10.750   1.7102   0.02380   0.01793  -0.1363   0.3096   1.0000
  11.000   1.7240   0.02464   0.01882  -0.1349   0.3021   1.0000
  11.250   1.7314   0.02590   0.02005  -0.1329   0.2941   1.0000
  11.500   1.7445   0.02683   0.02104  -0.1316   0.2867   1.0000
  11.750   1.7513   0.02821   0.02239  -0.1297   0.2788   1.0000
  12.000   1.7631   0.02929   0.02353  -0.1283   0.2713   1.0000
  12.250   1.7694   0.03079   0.02502  -0.1265   0.2637   1.0000
  12.500   1.7798   0.03204   0.02631  -0.1252   0.2561   1.0000
  12.750   1.7855   0.03368   0.02794  -0.1235   0.2484   1.0000
  13.000   1.7944   0.03511   0.02943  -0.1222   0.2410   1.0000
  13.250   1.7992   0.03692   0.03123  -0.1207   0.2333   1.0000
  13.500   1.8070   0.03854   0.03289  -0.1194   0.2259   1.0000
  13.750   1.8106   0.04056   0.03491  -0.1180   0.2183   1.0000
  14.000   1.8176   0.04232   0.03672  -0.1169   0.2111   1.0000
  14.250   1.8198   0.04458   0.03898  -0.1156   0.2036   1.0000
  14.500   1.8255   0.04656   0.04101  -0.1146   0.1967   1.0000
  14.750   1.8271   0.04901   0.04346  -0.1134   0.1894   1.0000
  15.000   1.8310   0.05128   0.04578  -0.1125   0.1827   1.0000
  15.250   1.8319   0.05390   0.04842  -0.1116   0.1757   1.0000
  15.500   1.8342   0.05644   0.05101  -0.1108   0.1693   1.0000
  15.750   1.8345   0.05928   0.05388  -0.1101   0.1627   1.0000
  16.000   1.8344   0.06221   0.05684  -0.1095   0.1567   1.0000
  16.250   1.8356   0.06506   0.05974  -0.1090   0.1505   1.0000
  16.500   1.8315   0.06860   0.06330  -0.1086   0.1448   1.0000
  16.750   1.8331   0.07150   0.06628  -0.1083   0.1388   1.0000
  17.000   1.8276   0.07538   0.07017  -0.1081   0.1332   1.0000
  17.250   1.8285   0.07848   0.07335  -0.1081   0.1278   1.0000
  17.500   1.8235   0.08243   0.07734  -0.1082   0.1224   1.0000
  17.750   1.8200   0.08621   0.08117  -0.1084   0.1176   1.0000
  18.000   1.8181   0.08983   0.08486  -0.1087   0.1127   1.0000
  18.250   1.8096   0.09447   0.08952  -0.1092   0.1081   1.0000
  18.500   1.8087   0.09803   0.09317  -0.1097   0.1038   1.0000
  18.750   1.8029   0.10234   0.09754  -0.1105   0.0994   1.0000
  19.000   1.7955   0.10694   0.10218  -0.1114   0.0955   1.0000
  19.250   1.7942   0.11064   0.10597  -0.1122   0.0917   1.0000
<< Back to MH 113 14.62% (mh113-il)

Polar data table (+)

Polar graphs


<< Back to MH 113 14.62% (mh113-il)