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MH 46 9.1% (mh46-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MH 46 9.1% (mh46-il)
Reynolds number: 50,000
Max Cl/Cd: 30.29 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh46-il-50000.txt
Download as CSV file: xf-mh46-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 46  9.1%                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5115   0.11026   0.10374   0.0115   1.0000   0.2405
  -8.750  -0.5092   0.10663   0.10017   0.0106   1.0000   0.2491
  -8.500  -0.5257   0.10526   0.09894   0.0083   1.0000   0.2586
  -8.250  -0.5023   0.09976   0.09342   0.0095   1.0000   0.2690
  -8.000  -0.4989   0.09613   0.08986   0.0089   1.0000   0.2769
  -7.500  -0.5143   0.09083   0.08478   0.0069   1.0000   0.3002
  -7.250  -0.4943   0.08549   0.07945   0.0073   1.0000   0.3045
  -6.750  -0.5564   0.05962   0.05279  -0.0288   1.0000   0.1078
  -6.500  -0.5429   0.05492   0.04805  -0.0287   1.0000   0.1063
  -6.250  -0.5308   0.05031   0.04325  -0.0287   1.0000   0.1031
  -6.000  -0.5204   0.04524   0.03767  -0.0286   1.0000   0.0988
  -5.750  -0.5077   0.04080   0.03220  -0.0275   1.0000   0.0942
  -5.500  -0.4898   0.03713   0.02807  -0.0262   1.0000   0.0942
  -5.250  -0.4708   0.03373   0.02444  -0.0250   1.0000   0.0974
  -5.000  -0.4513   0.03140   0.02169  -0.0233   1.0000   0.1067
  -4.750  -0.4307   0.02887   0.01903  -0.0218   1.0000   0.1177
  -4.500  -0.4111   0.02670   0.01677  -0.0200   1.0000   0.1386
  -4.250  -0.3910   0.02462   0.01475  -0.0181   1.0000   0.1706
  -4.000  -0.3726   0.02266   0.01303  -0.0158   1.0000   0.2296
  -3.750  -0.3584   0.02102   0.01198  -0.0131   1.0000   0.3273
  -3.500  -0.3464   0.01981   0.01138  -0.0097   1.0000   0.4344
  -3.250  -0.3351   0.01884   0.01089  -0.0057   1.0000   0.5396
  -3.000  -0.3241   0.01793   0.01049  -0.0011   1.0000   0.6494
  -2.750  -0.3065   0.01712   0.01020   0.0037   1.0000   0.7895
  -2.500  -0.0830   0.01679   0.00850  -0.0293   1.0000   1.0000
  -2.250  -0.0979   0.01651   0.00812  -0.0247   1.0000   1.0000
  -2.000  -0.1024   0.01650   0.00790  -0.0209   1.0000   1.0000
  -1.750  -0.1000   0.01661   0.00777  -0.0178   1.0000   1.0000
  -1.500  -0.0940   0.01679   0.00773  -0.0152   1.0000   1.0000
  -1.250  -0.0855   0.01701   0.00773  -0.0130   1.0000   1.0000
  -1.000  -0.0752   0.01727   0.00779  -0.0110   1.0000   1.0000
  -0.750  -0.0634   0.01758   0.00792  -0.0094   1.0000   1.0000
  -0.500  -0.0507   0.01793   0.00807  -0.0080   1.0000   1.0000
  -0.250  -0.0372   0.01832   0.00831  -0.0068   1.0000   1.0000
   0.000  -0.0233   0.01876   0.00861  -0.0058   1.0000   1.0000
   0.250  -0.0090   0.01926   0.00899  -0.0050   1.0000   1.0000
   0.500   0.0129   0.01988   0.00950  -0.0058   0.9970   1.0000
   0.750   0.0730   0.02095   0.01046  -0.0136   0.9785   1.0000
   1.000   0.1305   0.02190   0.01138  -0.0206   0.9592   1.0000
   1.250   0.1884   0.02277   0.01224  -0.0274   0.9398   1.0000
   1.500   0.2392   0.02349   0.01298  -0.0326   0.9190   1.0000
   1.750   0.3000   0.02410   0.01367  -0.0392   0.8995   1.0000
   2.000   0.3468   0.02461   0.01430  -0.0430   0.8777   1.0000
   2.250   0.3980   0.02497   0.01476  -0.0469   0.8572   1.0000
   2.500   0.4353   0.02537   0.01526  -0.0482   0.8350   1.0000
   2.750   0.4707   0.02570   0.01575  -0.0488   0.8134   1.0000
   3.000   0.5041   0.02593   0.01610  -0.0486   0.7918   1.0000
   3.250   0.5294   0.02631   0.01657  -0.0473   0.7691   1.0000
   3.500   0.5602   0.02632   0.01669  -0.0459   0.7485   1.0000
   3.750   0.5812   0.02670   0.01722  -0.0437   0.7245   1.0000
   4.000   0.6048   0.02689   0.01751  -0.0415   0.7018   1.0000
   4.250   0.6301   0.02679   0.01751  -0.0389   0.6797   1.0000
   4.500   0.6514   0.02700   0.01783  -0.0364   0.6546   1.0000
   4.750   0.6737   0.02708   0.01806  -0.0337   0.6293   1.0000
   5.000   0.6964   0.02706   0.01815  -0.0310   0.6032   1.0000
   5.250   0.7192   0.02701   0.01818  -0.0282   0.5757   1.0000
   5.500   0.7419   0.02697   0.01820  -0.0254   0.5464   1.0000
   5.750   0.7651   0.02687   0.01811  -0.0226   0.5155   1.0000
   6.000   0.7869   0.02703   0.01837  -0.0199   0.4813   1.0000
   6.250   0.8094   0.02714   0.01839  -0.0172   0.4451   1.0000
   6.500   0.8298   0.02756   0.01878  -0.0148   0.4051   1.0000
   6.750   0.8498   0.02806   0.01914  -0.0123   0.3628   1.0000
   7.000   0.8681   0.02885   0.01978  -0.0099   0.3179   1.0000
   7.250   0.8846   0.02997   0.02078  -0.0077   0.2720   1.0000
   7.500   0.9010   0.03150   0.02211  -0.0055   0.2292   1.0000
   7.750   0.9179   0.03350   0.02393  -0.0037   0.1934   1.0000
   8.000   0.9340   0.03574   0.02616  -0.0019   0.1645   1.0000
   8.250   0.9535   0.03835   0.02876  -0.0006   0.1437   1.0000
   8.500   0.9707   0.04146   0.03201   0.0008   0.1293   1.0000
   8.750   0.9852   0.04435   0.03508   0.0021   0.1162   1.0000
   9.000   0.9906   0.04853   0.04006   0.0041   0.1119   1.0000
   9.250   0.9951   0.05285   0.04487   0.0056   0.1085   1.0000
   9.500   1.0074   0.05682   0.04884   0.0066   0.1028   1.0000
   9.750   0.9978   0.06135   0.05391   0.0081   0.1016   1.0000
  10.000   0.9839   0.06602   0.05895   0.0092   0.1010   1.0000
  10.250   0.9667   0.07080   0.06398   0.0097   0.1013   1.0000
  10.500   0.9477   0.07549   0.06881   0.0101   0.1020   1.0000
  10.750   0.9277   0.08057   0.07396   0.0094   0.1026   1.0000
  11.000   0.9132   0.08618   0.07961   0.0077   0.1033   1.0000
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