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MH 115 11.06% (mh115-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: MH 115 11.06% (mh115-il)
Reynolds number: 500,000
Max Cl/Cd: 130.69 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh115-il-500000.txt
Download as CSV file: xf-mh115-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.1712   0.10211   0.09984  -0.0693   0.9851   0.0164
  -9.250  -0.1576   0.09753   0.09527  -0.0742   0.9825   0.0165
  -9.000  -0.1467   0.09350   0.09125  -0.0763   0.9785   0.0167
  -8.750  -0.1286   0.09066   0.08841  -0.0785   0.9760   0.0170
  -8.500  -0.1103   0.08724   0.08499  -0.0821   0.9739   0.0174
  -8.250  -0.0911   0.08359   0.08133  -0.0866   0.9721   0.0179
  -8.000  -0.0803   0.08025   0.07800  -0.0892   0.9647   0.0184
  -7.750  -0.0628   0.07592   0.07367  -0.0946   0.9614   0.0192
  -7.500  -0.0517   0.06977   0.06754  -0.1028   0.9528   0.0204
  -7.250  -0.0296   0.06284   0.06060  -0.1138   0.9471   0.0205
  -7.000  -0.0141   0.05823   0.05599  -0.1194   0.9392   0.0209
  -6.750   0.0127   0.05492   0.05265  -0.1254   0.9338   0.0214
  -6.500   0.0362   0.05052   0.04821  -0.1331   0.9235   0.0219
  -6.250   0.0623   0.04404   0.04161  -0.1442   0.9122   0.0228
  -6.000   0.0694   0.01706   0.01227  -0.1633   0.8920   0.0104
  -5.750   0.0991   0.01572   0.01061  -0.1641   0.8853   0.0102
  -5.500   0.1253   0.01424   0.00885  -0.1641   0.8767   0.0102
  -5.250   0.1540   0.01286   0.00725  -0.1646   0.8699   0.0104
  -5.000   0.1809   0.01200   0.00628  -0.1646   0.8614   0.0108
  -4.750   0.2098   0.01141   0.00560  -0.1649   0.8544   0.0116
  -4.500   0.2376   0.01093   0.00499  -0.1648   0.8461   0.0130
  -4.250   0.2665   0.01041   0.00439  -0.1651   0.8388   0.0155
  -4.000   0.2946   0.00993   0.00387  -0.1651   0.8307   0.0215
  -3.750   0.3232   0.00962   0.00355  -0.1653   0.8234   0.0336
  -3.500   0.3510   0.00944   0.00336  -0.1653   0.8152   0.0450
  -3.250   0.3794   0.00921   0.00312  -0.1654   0.8077   0.0589
  -3.000   0.4074   0.00897   0.00290  -0.1654   0.7996   0.0800
  -2.750   0.4358   0.00875   0.00272  -0.1656   0.7921   0.1114
  -2.500   0.4637   0.00855   0.00260  -0.1657   0.7840   0.1482
  -2.250   0.4919   0.00840   0.00250  -0.1658   0.7765   0.1892
  -2.000   0.5198   0.00826   0.00243  -0.1658   0.7685   0.2347
  -1.750   0.5479   0.00812   0.00239  -0.1659   0.7609   0.2862
  -1.500   0.5757   0.00799   0.00236  -0.1660   0.7529   0.3464
  -1.250   0.6037   0.00787   0.00236  -0.1660   0.7453   0.4061
  -1.000   0.6314   0.00777   0.00237  -0.1660   0.7374   0.4671
  -0.750   0.6591   0.00769   0.00240  -0.1660   0.7298   0.5273
  -0.500   0.6865   0.00762   0.00243  -0.1659   0.7218   0.5880
  -0.250   0.7136   0.00756   0.00248  -0.1657   0.7140   0.6486
   0.000   0.7401   0.00750   0.00253  -0.1653   0.7061   0.7078
   0.250   0.7658   0.00745   0.00260  -0.1647   0.6981   0.7673
   0.500   0.7894   0.00739   0.00264  -0.1635   0.6901   0.8299
   0.750   0.8075   0.00726   0.00266  -0.1610   0.6822   0.9112
   1.000   0.8351   0.00725   0.00260  -0.1608   0.6740   1.0000
   1.250   0.8628   0.00733   0.00264  -0.1608   0.6653   1.0000
   1.500   0.8903   0.00747   0.00267  -0.1607   0.6570   1.0000
   1.750   0.9175   0.00756   0.00274  -0.1606   0.6478   1.0000
   2.000   0.9446   0.00768   0.00279  -0.1605   0.6392   1.0000
   2.250   0.9715   0.00780   0.00286  -0.1603   0.6296   1.0000
   2.500   0.9982   0.00792   0.00294  -0.1601   0.6200   1.0000
   2.750   1.0246   0.00808   0.00303  -0.1598   0.6106   1.0000
   3.000   1.0510   0.00820   0.00313  -0.1595   0.6001   1.0000
   3.250   1.0771   0.00834   0.00323  -0.1592   0.5898   1.0000
   3.500   1.1028   0.00851   0.00336  -0.1588   0.5791   1.0000
   3.750   1.1283   0.00867   0.00348  -0.1583   0.5675   1.0000
   4.000   1.1538   0.00883   0.00362  -0.1579   0.5556   1.0000
   4.250   1.1788   0.00902   0.00377  -0.1574   0.5433   1.0000
   4.500   1.2034   0.00922   0.00394  -0.1568   0.5304   1.0000
   4.750   1.2276   0.00944   0.00411  -0.1561   0.5168   1.0000
   5.000   1.2514   0.00968   0.00430  -0.1554   0.5023   1.0000
   5.250   1.2748   0.00993   0.00452  -0.1546   0.4870   1.0000
   5.500   1.2978   0.01020   0.00474  -0.1538   0.4707   1.0000
   5.750   1.3203   0.01050   0.00499  -0.1529   0.4538   1.0000
   6.000   1.3423   0.01081   0.00526  -0.1519   0.4363   1.0000
   6.250   1.3635   0.01116   0.00555  -0.1507   0.4183   1.0000
   6.500   1.3842   0.01154   0.00586  -0.1495   0.4008   1.0000
   6.750   1.4046   0.01192   0.00620  -0.1483   0.3842   1.0000
   7.250   1.4436   0.01275   0.00693  -0.1455   0.3508   1.0000
   7.500   1.4617   0.01316   0.00731  -0.1438   0.3348   1.0000
   7.750   1.4786   0.01361   0.00772  -0.1420   0.3186   1.0000
   8.000   1.4951   0.01407   0.00815  -0.1401   0.3034   1.0000
   8.250   1.5111   0.01457   0.00861  -0.1381   0.2884   1.0000
   8.500   1.5263   0.01510   0.00911  -0.1361   0.2730   1.0000
   8.750   1.5413   0.01566   0.00965  -0.1340   0.2582   1.0000
   9.000   1.5555   0.01627   0.01022  -0.1319   0.2438   1.0000
   9.250   1.5691   0.01692   0.01084  -0.1298   0.2291   1.0000
   9.500   1.5819   0.01761   0.01151  -0.1276   0.2148   1.0000
   9.750   1.5940   0.01838   0.01224  -0.1253   0.2000   1.0000
  10.000   1.6047   0.01924   0.01306  -0.1230   0.1834   1.0000
  10.250   1.6142   0.02019   0.01395  -0.1206   0.1669   1.0000
  10.500   1.6232   0.02121   0.01492  -0.1182   0.1520   1.0000
  10.750   1.6324   0.02226   0.01594  -0.1159   0.1393   1.0000
  11.000   1.6411   0.02337   0.01704  -0.1137   0.1277   1.0000
  11.250   1.6491   0.02457   0.01823  -0.1115   0.1171   1.0000
  11.500   1.6557   0.02591   0.01956  -0.1093   0.1073   1.0000
  11.750   1.6637   0.02720   0.02087  -0.1074   0.0981   1.0000
  12.000   1.6707   0.02862   0.02230  -0.1055   0.0894   1.0000
  12.250   1.6760   0.03021   0.02389  -0.1035   0.0812   1.0000
  12.500   1.6807   0.03192   0.02559  -0.1017   0.0729   1.0000
  12.750   1.6860   0.03364   0.02733  -0.1000   0.0648   1.0000
  13.000   1.6895   0.03557   0.02927  -0.0984   0.0568   1.0000
  13.250   1.6914   0.03773   0.03142  -0.0968   0.0490   1.0000
  13.500   1.6922   0.04008   0.03377  -0.0954   0.0419   1.0000
  13.750   1.6928   0.04254   0.03625  -0.0941   0.0352   1.0000
  14.000   1.6922   0.04522   0.03896  -0.0929   0.0294   1.0000
  14.250   1.6905   0.04814   0.04192  -0.0919   0.0243   1.0000
  14.500   1.6877   0.05129   0.04513  -0.0910   0.0202   1.0000
  14.750   1.6840   0.05468   0.04857  -0.0904   0.0172   1.0000
  15.000   1.6800   0.05825   0.05221  -0.0900   0.0148   1.0000
  15.250   1.6764   0.06189   0.05597  -0.0897   0.0129   1.0000
  15.500   1.6700   0.06602   0.06018  -0.0897   0.0114   1.0000
  15.750   1.6653   0.07005   0.06434  -0.0899   0.0099   1.0000
  16.000   1.6567   0.07482   0.06920  -0.0905   0.0088   1.0000
  16.250   1.6495   0.07953   0.07405  -0.0912   0.0076   1.0000
  16.500   1.6394   0.08480   0.07943  -0.0923   0.0067   1.0000
  16.750   1.6272   0.09065   0.08542  -0.0937   0.0060   1.0000
  17.000   1.6183   0.09606   0.09098  -0.0952   0.0054   1.0000
  17.250   1.6062   0.10216   0.09720  -0.0972   0.0050   1.0000
  17.500   1.5889   0.10937   0.10456  -0.0999   0.0047   1.0000
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