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MH 32 8.7% (mh32-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: MH 32 8.7% (mh32-il)
Reynolds number: 1,000,000
Max Cl/Cd: 96.31 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh32-il-1000000-n5.txt
Download as CSV file: xf-mh32-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 32  8.7%                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.4093   0.04390   0.04204  -0.0665   0.9541   0.0024
  -7.000  -0.4060   0.03667   0.03449  -0.0679   0.9371   0.0023
  -6.750  -0.4048   0.02843   0.02574  -0.0674   0.9234   0.0022
  -6.500  -0.3973   0.02164   0.01828  -0.0658   0.9131   0.0020
  -6.250  -0.3806   0.01762   0.01368  -0.0644   0.9049   0.0019
  -6.000  -0.3595   0.01506   0.01068  -0.0634   0.8983   0.0019
  -5.750  -0.3360   0.01339   0.00870  -0.0626   0.8915   0.0018
  -5.500  -0.3116   0.01214   0.00720  -0.0619   0.8854   0.0018
  -5.250  -0.2865   0.01116   0.00603  -0.0613   0.8786   0.0018
  -5.000  -0.2609   0.01041   0.00512  -0.0608   0.8721   0.0018
  -4.750  -0.2348   0.00980   0.00439  -0.0604   0.8648   0.0018
  -4.500  -0.2084   0.00931   0.00378  -0.0601   0.8576   0.0019
  -4.250  -0.1817   0.00888   0.00322  -0.0598   0.8493   0.0020
  -4.000  -0.1547   0.00854   0.00279  -0.0595   0.8412   0.0021
  -3.500  -0.1001   0.00806   0.00215  -0.0591   0.8242   0.0025
  -3.250  -0.0728   0.00783   0.00187  -0.0589   0.8154   0.0039
  -2.750  -0.0181   0.00749   0.00149  -0.0586   0.7954   0.0151
  -2.500   0.0091   0.00727   0.00133  -0.0585   0.7844   0.0363
  -2.250   0.0358   0.00695   0.00117  -0.0584   0.7722   0.0894
  -2.000   0.0625   0.00668   0.00105  -0.0582   0.7584   0.1470
  -1.750   0.0894   0.00649   0.00096  -0.0581   0.7427   0.1953
  -1.500   0.1160   0.00633   0.00087  -0.0579   0.7238   0.2476
  -1.250   0.1428   0.00622   0.00081  -0.0578   0.7023   0.2951
  -1.000   0.1695   0.00612   0.00076  -0.0576   0.6812   0.3443
  -0.750   0.1962   0.00601   0.00074  -0.0574   0.6600   0.4015
  -0.500   0.2228   0.00593   0.00072  -0.0572   0.6394   0.4541
  -0.250   0.2495   0.00586   0.00072  -0.0571   0.6184   0.5069
   0.000   0.2761   0.00580   0.00073  -0.0569   0.5991   0.5611
   0.250   0.3026   0.00574   0.00075  -0.0567   0.5792   0.6164
   0.500   0.3290   0.00570   0.00079  -0.0564   0.5600   0.6685
   0.750   0.3552   0.00567   0.00083  -0.0561   0.5404   0.7200
   1.000   0.3810   0.00565   0.00088  -0.0556   0.5204   0.7705
   1.250   0.4063   0.00563   0.00094  -0.0550   0.4995   0.8206
   1.500   0.4308   0.00563   0.00102  -0.0542   0.4785   0.8709
   1.750   0.4551   0.00565   0.00109  -0.0533   0.4571   0.9223
   2.000   0.4900   0.00576   0.00115  -0.0548   0.4324   0.9684
   2.250   0.5281   0.00593   0.00122  -0.0572   0.4074   0.9936
   2.500   0.5575   0.00612   0.00131  -0.0577   0.3847   1.0000
   2.750   0.5832   0.00630   0.00142  -0.0573   0.3626   1.0000
   3.000   0.6090   0.00650   0.00152  -0.0570   0.3404   1.0000
   3.250   0.6347   0.00672   0.00164  -0.0567   0.3167   1.0000
   3.500   0.6604   0.00695   0.00177  -0.0563   0.2928   1.0000
   3.750   0.6862   0.00718   0.00193  -0.0560   0.2720   1.0000
   4.000   0.7119   0.00742   0.00209  -0.0557   0.2494   1.0000
   4.250   0.7376   0.00767   0.00225  -0.0554   0.2286   1.0000
   4.750   0.7888   0.00819   0.00264  -0.0548   0.1895   1.0000
   5.000   0.8133   0.00857   0.00288  -0.0543   0.1584   1.0000
   5.250   0.8382   0.00893   0.00312  -0.0539   0.1344   1.0000
   5.500   0.8632   0.00925   0.00338  -0.0535   0.1162   1.0000
   5.750   0.8882   0.00958   0.00364  -0.0531   0.1001   1.0000
   6.000   0.9132   0.00990   0.00391  -0.0528   0.0863   1.0000
   6.250   0.9379   0.01025   0.00423  -0.0523   0.0722   1.0000
   6.500   0.9622   0.01065   0.00456  -0.0519   0.0568   1.0000
   6.750   0.9855   0.01115   0.00496  -0.0513   0.0389   1.0000
   7.000   1.0078   0.01176   0.00544  -0.0505   0.0205   1.0000
   7.250   1.0310   0.01225   0.00589  -0.0499   0.0121   1.0000
   7.500   1.0549   0.01266   0.00629  -0.0494   0.0082   1.0000
   7.750   1.0772   0.01322   0.00683  -0.0487   0.0034   1.0000
   8.000   1.1005   0.01366   0.00729  -0.0481   0.0023   1.0000
   8.250   1.1233   0.01417   0.00786  -0.0473   0.0015   1.0000
   8.500   1.1462   0.01461   0.00836  -0.0467   0.0012   1.0000
   8.750   1.1686   0.01511   0.00892  -0.0460   0.0010   1.0000
   9.000   1.1905   0.01564   0.00950  -0.0452   0.0009   1.0000
   9.250   1.2115   0.01624   0.01016  -0.0443   0.0007   1.0000
   9.500   1.2313   0.01695   0.01097  -0.0432   0.0006   1.0000
   9.750   1.2508   0.01765   0.01176  -0.0420   0.0005   1.0000
  10.000   1.2706   0.01827   0.01244  -0.0410   0.0005   1.0000
  10.250   1.2897   0.01890   0.01315  -0.0399   0.0005   1.0000
  10.500   1.3076   0.01962   0.01398  -0.0386   0.0004   1.0000
  10.750   1.3241   0.02042   0.01488  -0.0371   0.0004   1.0000
  11.000   1.3392   0.02127   0.01583  -0.0355   0.0004   1.0000
  11.250   1.3524   0.02218   0.01683  -0.0336   0.0003   1.0000
  11.500   1.3609   0.02314   0.01792  -0.0309   0.0003   1.0000
  11.750   1.3678   0.02416   0.01904  -0.0281   0.0003   1.0000
  12.000   1.3728   0.02533   0.02034  -0.0253   0.0003   1.0000
  12.250   1.3775   0.02658   0.02171  -0.0227   0.0003   1.0000
  12.500   1.3800   0.02805   0.02331  -0.0201   0.0002   1.0000
  12.750   1.3829   0.02957   0.02496  -0.0180   0.0003   1.0000
  13.000   1.3819   0.03148   0.02701  -0.0158   0.0002   1.0000
  13.250   1.3796   0.03366   0.02933  -0.0139   0.0002   1.0000
  13.500   1.3748   0.03622   0.03206  -0.0124   0.0002   1.0000
  13.750   1.3734   0.03865   0.03461  -0.0115   0.0002   1.0000
  14.000   1.3649   0.04203   0.03817  -0.0110   0.0002   1.0000
  14.250   1.3590   0.04544   0.04173  -0.0111   0.0002   1.0000
  14.500   1.3496   0.04958   0.04602  -0.0119   0.0002   1.0000
  14.750   1.3374   0.05450   0.05111  -0.0135   0.0002   1.0000
  15.000   1.3218   0.06038   0.05715  -0.0159   0.0002   1.0000
  15.250   1.3080   0.06644   0.06336  -0.0188   0.0002   1.0000
  15.500   1.2868   0.07428   0.07138  -0.0230   0.0002   1.0000
  15.750   1.2677   0.08223   0.07948  -0.0273   0.0002   1.0000
  16.000   1.2453   0.09124   0.08865  -0.0324   0.0002   1.0000
  16.250   1.2253   0.10015   0.09768  -0.0374   0.0002   1.0000
  16.500   1.2025   0.10997   0.10761  -0.0428   0.0002   1.0000
  16.750   1.1714   0.12205   0.11984  -0.0496   0.0002   1.0000
  17.000   1.1514   0.13182   0.12972  -0.0550   0.0002   1.0000
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