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MH 106 13.07% (mh106-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 106 13.07% (mh106-il)
Reynolds number: 100,000
Max Cl/Cd: 42.08 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh106-il-100000.txt
Download as CSV file: xf-mh106-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 106  13.07%                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.5548   0.09658   0.09222  -0.0081   1.0000   0.0533
 -11.250  -0.5632   0.09013   0.08578  -0.0103   1.0000   0.0517
 -11.000  -0.6865   0.08269   0.07796  -0.0178   1.0000   0.0522
 -10.750  -0.7096   0.07554   0.07077  -0.0229   1.0000   0.0513
 -10.500  -0.7349   0.06960   0.06472  -0.0266   1.0000   0.0506
 -10.250  -0.7590   0.06477   0.05975  -0.0279   1.0000   0.0496
 -10.000  -0.7829   0.06070   0.05550  -0.0268   1.0000   0.0485
  -9.750  -0.8084   0.05652   0.05098  -0.0242   1.0000   0.0468
  -9.500  -0.8367   0.05312   0.04674  -0.0199   1.0000   0.0438
  -9.250  -0.8277   0.05010   0.04346  -0.0184   1.0000   0.0427
  -9.000  -0.8226   0.04594   0.03903  -0.0167   1.0000   0.0420
  -8.750  -0.8147   0.04242   0.03518  -0.0149   1.0000   0.0415
  -8.500  -0.8035   0.03927   0.03164  -0.0131   1.0000   0.0412
  -8.250  -0.7887   0.03644   0.02846  -0.0114   1.0000   0.0411
  -8.000  -0.7714   0.03422   0.02588  -0.0098   1.0000   0.0421
  -7.750  -0.7522   0.03179   0.02317  -0.0084   1.0000   0.0439
  -7.500  -0.7299   0.02924   0.02066  -0.0078   1.0000   0.0467
  -7.250  -0.7071   0.02737   0.01873  -0.0067   1.0000   0.0493
  -7.000  -0.6845   0.02564   0.01692  -0.0054   1.0000   0.0530
  -6.750  -0.6672   0.02378   0.01518  -0.0037   1.0000   0.0588
  -6.500  -0.6516   0.02227   0.01367  -0.0016   1.0000   0.0687
  -6.250  -0.6396   0.02058   0.01213   0.0011   1.0000   0.0864
  -6.000  -0.6393   0.01768   0.01035   0.0051   1.0000   0.2034
  -5.750  -0.6290   0.01717   0.01023   0.0081   1.0000   0.3126
  -5.500  -0.6139   0.01709   0.01017   0.0105   1.0000   0.3540
  -5.250  -0.5987   0.01698   0.01009   0.0128   1.0000   0.3851
  -5.000  -0.5852   0.01687   0.01003   0.0152   1.0000   0.4126
  -4.750  -0.5765   0.01679   0.00995   0.0182   1.0000   0.4372
  -4.500  -0.5553   0.01674   0.00997   0.0185   0.9937   0.4632
  -4.250  -0.4998   0.01646   0.00965   0.0128   0.9722   0.4963
  -4.000  -0.4453   0.01606   0.00925   0.0077   0.9514   0.5259
  -3.750  -0.3961   0.01566   0.00884   0.0039   0.9279   0.5547
  -3.500  -0.3548   0.01533   0.00852   0.0019   0.9009   0.5821
  -3.250  -0.3225   0.01511   0.00829   0.0019   0.8727   0.6090
  -3.000  -0.2962   0.01496   0.00810   0.0030   0.8454   0.6363
  -2.750  -0.2718   0.01485   0.00797   0.0046   0.8209   0.6652
  -2.500  -0.2477   0.01478   0.00790   0.0063   0.7970   0.6959
  -2.250  -0.2232   0.01476   0.00784   0.0079   0.7763   0.7285
  -2.000  -0.1981   0.01479   0.00787   0.0093   0.7561   0.7630
  -1.750  -0.1695   0.01492   0.00796   0.0104   0.7380   0.7956
  -1.500  -0.1377   0.01515   0.00810   0.0108   0.7211   0.8270
  -1.250  -0.1020   0.01547   0.00830   0.0105   0.7052   0.8555
  -1.000  -0.0637   0.01584   0.00852   0.0094   0.6902   0.8814
  -0.750  -0.0151   0.01627   0.00879   0.0064   0.6752   0.9000
  -0.500   0.0368   0.01667   0.00902   0.0024   0.6607   0.9168
  -0.250   0.0891   0.01700   0.00920  -0.0019   0.6471   0.9333
   0.000   0.1399   0.01724   0.00932  -0.0063   0.6342   0.9503
   0.250   0.1910   0.01742   0.00940  -0.0110   0.6222   0.9673
   0.500   0.2451   0.01747   0.00934  -0.0165   0.6114   0.9826
   0.750   0.3012   0.01732   0.00906  -0.0226   0.6012   0.9969
   1.000   0.3282   0.01731   0.00905  -0.0235   0.5917   1.0000
   1.250   0.3471   0.01737   0.00902  -0.0225   0.5852   1.0000
   1.500   0.3670   0.01749   0.00917  -0.0219   0.5766   1.0000
   1.750   0.3871   0.01762   0.00922  -0.0209   0.5703   1.0000
   2.000   0.4078   0.01782   0.00948  -0.0203   0.5621   1.0000
   2.250   0.4285   0.01800   0.00956  -0.0192   0.5562   1.0000
   2.500   0.4494   0.01830   0.00996  -0.0185   0.5479   1.0000
   2.750   0.4706   0.01851   0.01010  -0.0174   0.5419   1.0000
   3.000   0.4915   0.01889   0.01058  -0.0167   0.5337   1.0000
   3.250   0.5132   0.01912   0.01075  -0.0156   0.5275   1.0000
   3.500   0.5341   0.01956   0.01131  -0.0149   0.5193   1.0000
   3.750   0.5561   0.01980   0.01150  -0.0138   0.5129   1.0000
   4.000   0.5769   0.02028   0.01210  -0.0129   0.5043   1.0000
   4.250   0.5994   0.02049   0.01225  -0.0118   0.4978   1.0000
   4.500   0.6199   0.02099   0.01291  -0.0109   0.4885   1.0000
   4.750   0.6425   0.02123   0.01311  -0.0097   0.4813   1.0000
   5.000   0.6634   0.02163   0.01362  -0.0087   0.4717   1.0000
   5.250   0.6848   0.02200   0.01406  -0.0076   0.4628   1.0000
   5.500   0.7081   0.02213   0.01417  -0.0064   0.4543   1.0000
   5.750   0.7285   0.02255   0.01472  -0.0053   0.4436   1.0000
   6.000   0.7505   0.02280   0.01502  -0.0041   0.4337   1.0000
   6.250   0.7747   0.02281   0.01497  -0.0030   0.4244   1.0000
   6.500   0.7952   0.02310   0.01542  -0.0017   0.4123   1.0000
   6.750   0.8165   0.02332   0.01574  -0.0004   0.4003   1.0000
   7.000   0.8386   0.02342   0.01589   0.0008   0.3881   1.0000
   7.250   0.8610   0.02344   0.01594   0.0021   0.3754   1.0000
   7.500   0.8832   0.02342   0.01598   0.0034   0.3616   1.0000
   7.750   0.9046   0.02341   0.01603   0.0048   0.3465   1.0000
   8.000   0.9252   0.02337   0.01606   0.0063   0.3298   1.0000
   8.250   0.9456   0.02329   0.01603   0.0078   0.3121   1.0000
   8.500   0.9662   0.02317   0.01585   0.0093   0.2937   1.0000
   8.750   0.9824   0.02345   0.01624   0.0112   0.2715   1.0000
   9.000   0.9993   0.02375   0.01646   0.0129   0.2505   1.0000
   9.250   1.0128   0.02447   0.01718   0.0149   0.2277   1.0000
   9.500   1.0262   0.02540   0.01797   0.0168   0.2079   1.0000
   9.750   1.0371   0.02653   0.01911   0.0188   0.1885   1.0000
  10.000   1.0479   0.02775   0.02028   0.0208   0.1717   1.0000
  10.250   1.0576   0.02905   0.02152   0.0228   0.1567   1.0000
  10.500   1.0665   0.03046   0.02291   0.0248   0.1432   1.0000
  10.750   1.0737   0.03197   0.02445   0.0269   0.1311   1.0000
  11.000   1.0799   0.03358   0.02613   0.0289   0.1204   1.0000
  11.250   1.0871   0.03527   0.02777   0.0308   0.1107   1.0000
  11.500   1.0884   0.03675   0.02928   0.0332   0.1024   1.0000
  11.750   1.0879   0.03871   0.03138   0.0356   0.0954   1.0000
  12.000   1.0968   0.04063   0.03311   0.0368   0.0869   1.0000
  12.250   1.0870   0.04283   0.03565   0.0387   0.0828   1.0000
  12.500   1.0890   0.04485   0.03766   0.0397   0.0770   1.0000
  12.750   1.0866   0.04767   0.04061   0.0404   0.0721   1.0000
  13.000   1.0788   0.05067   0.04384   0.0407   0.0685   1.0000
  13.250   1.0895   0.05314   0.04612   0.0414   0.0625   1.0000
  13.500   1.0746   0.05681   0.05011   0.0408   0.0610   1.0000
  13.750   1.0606   0.06089   0.05446   0.0397   0.0590   1.0000
  14.000   1.0482   0.06513   0.05892   0.0383   0.0572   1.0000
  14.250   1.0363   0.06952   0.06348   0.0366   0.0556   1.0000
  14.500   1.0454   0.07240   0.06620   0.0373   0.0516   1.0000
  14.750   1.0264   0.07796   0.07197   0.0348   0.0513   1.0000
  15.000   1.0042   0.08424   0.07848   0.0315   0.0512   1.0000
  15.250   0.9807   0.09100   0.08544   0.0277   0.0513   1.0000
  15.500   0.7941   0.13608   0.13103  -0.0010   0.0747   1.0000
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