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MH 44 9.66% (mh44-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MH 44 9.66% (mh44-il)
Reynolds number: 50,000
Max Cl/Cd: 29.12 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh44-il-50000.txt
Download as CSV file: xf-mh44-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 44  9.66%                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.5037   0.09644   0.09026   0.0042   1.0000   0.2839
  -7.750  -0.4781   0.09114   0.08495   0.0053   1.0000   0.2922
  -7.000  -0.5557   0.06222   0.05569  -0.0287   1.0000   0.1143
  -6.750  -0.5569   0.05569   0.04875  -0.0301   1.0000   0.1036
  -6.500  -0.5453   0.05128   0.04413  -0.0297   1.0000   0.0986
  -6.250  -0.5371   0.04660   0.03906  -0.0290   1.0000   0.0942
  -6.000  -0.5299   0.04234   0.03371  -0.0272   1.0000   0.0889
  -5.750  -0.5149   0.03889   0.02991  -0.0255   1.0000   0.0885
  -5.500  -0.4998   0.03577   0.02650  -0.0238   1.0000   0.0902
  -5.250  -0.4829   0.03346   0.02416  -0.0221   1.0000   0.0958
  -5.000  -0.4651   0.03103   0.02126  -0.0200   1.0000   0.0997
  -4.750  -0.4450   0.02860   0.01852  -0.0180   1.0000   0.1043
  -4.500  -0.4255   0.02676   0.01660  -0.0162   1.0000   0.1177
  -4.250  -0.4057   0.02494   0.01486  -0.0142   1.0000   0.1394
  -4.000  -0.3873   0.02303   0.01324  -0.0120   1.0000   0.1895
  -3.750  -0.3775   0.02062   0.01202  -0.0083   1.0000   0.3614
  -3.500  -0.3724   0.01990   0.01184  -0.0034   1.0000   0.4782
  -3.250  -0.3645   0.01937   0.01168   0.0013   1.0000   0.5707
  -3.000  -0.3525   0.01869   0.01138   0.0057   1.0000   0.6597
  -2.750  -0.3340   0.01796   0.01106   0.0098   1.0000   0.7717
  -2.500  -0.0731   0.01785   0.00956  -0.0289   1.0000   1.0000
  -2.250  -0.0973   0.01747   0.00915  -0.0233   1.0000   1.0000
  -2.000  -0.1051   0.01739   0.00884  -0.0191   1.0000   1.0000
  -1.750  -0.1035   0.01745   0.00866  -0.0159   1.0000   1.0000
  -1.500  -0.0977   0.01759   0.00858  -0.0133   1.0000   1.0000
  -1.250  -0.0898   0.01779   0.00858  -0.0110   1.0000   1.0000
  -1.000  -0.0804   0.01805   0.00864  -0.0089   1.0000   1.0000
  -0.750  -0.0698   0.01836   0.00878  -0.0071   1.0000   1.0000
  -0.500  -0.0583   0.01872   0.00895  -0.0056   1.0000   1.0000
  -0.250  -0.0460   0.01914   0.00922  -0.0042   1.0000   1.0000
   0.000  -0.0334   0.01961   0.00956  -0.0031   1.0000   1.0000
   0.250  -0.0204   0.02014   0.00997  -0.0021   1.0000   1.0000
   0.500   0.0252   0.02107   0.01079  -0.0074   0.9874   1.0000
   0.750   0.0884   0.02219   0.01180  -0.0157   0.9678   1.0000
   1.000   0.1456   0.02309   0.01267  -0.0225   0.9467   1.0000
   1.250   0.2048   0.02391   0.01348  -0.0293   0.9260   1.0000
   1.500   0.2587   0.02457   0.01418  -0.0348   0.9040   1.0000
   1.750   0.3156   0.02509   0.01478  -0.0404   0.8824   1.0000
   2.000   0.3687   0.02543   0.01521  -0.0448   0.8605   1.0000
   2.250   0.4082   0.02580   0.01565  -0.0465   0.8378   1.0000
   2.500   0.4520   0.02591   0.01589  -0.0482   0.8166   1.0000
   2.750   0.4784   0.02626   0.01631  -0.0473   0.7930   1.0000
   3.000   0.5127   0.02623   0.01636  -0.0468   0.7721   1.0000
   3.250   0.5360   0.02646   0.01665  -0.0449   0.7486   1.0000
   3.500   0.5612   0.02653   0.01684  -0.0430   0.7263   1.0000
   3.750   0.5874   0.02640   0.01678  -0.0408   0.7045   1.0000
   4.000   0.6094   0.02652   0.01697  -0.0384   0.6807   1.0000
   4.250   0.6351   0.02627   0.01679  -0.0357   0.6591   1.0000
   4.500   0.6571   0.02635   0.01693  -0.0332   0.6341   1.0000
   4.750   0.6791   0.02648   0.01712  -0.0307   0.6084   1.0000
   5.000   0.7016   0.02658   0.01726  -0.0282   0.5822   1.0000
   5.250   0.7242   0.02671   0.01741  -0.0257   0.5552   1.0000
   5.500   0.7466   0.02693   0.01768  -0.0233   0.5271   1.0000
   5.750   0.7686   0.02725   0.01801  -0.0210   0.4979   1.0000
   6.000   0.7905   0.02767   0.01841  -0.0188   0.4679   1.0000
   6.250   0.8123   0.02817   0.01890  -0.0167   0.4377   1.0000
   6.500   0.8341   0.02873   0.01944  -0.0147   0.4073   1.0000
   6.750   0.8558   0.02939   0.02000  -0.0128   0.3771   1.0000
   7.000   0.8757   0.03035   0.02097  -0.0110   0.3470   1.0000
   7.250   0.8952   0.03144   0.02208  -0.0092   0.3175   1.0000
   7.500   0.9145   0.03263   0.02326  -0.0075   0.2893   1.0000
   7.750   0.9344   0.03398   0.02454  -0.0059   0.2631   1.0000
   8.000   0.9524   0.03542   0.02605  -0.0042   0.2376   1.0000
   8.250   0.9677   0.03765   0.02853  -0.0026   0.2167   1.0000
   8.500   0.9881   0.03919   0.02986  -0.0012   0.1948   1.0000
   8.750   1.0009   0.04193   0.03292   0.0005   0.1793   1.0000
   9.000   1.0122   0.04458   0.03583   0.0022   0.1646   1.0000
   9.250   1.0245   0.04737   0.03877   0.0037   0.1520   1.0000
   9.500   1.0234   0.05150   0.04348   0.0057   0.1457   1.0000
   9.750   1.0301   0.05484   0.04698   0.0072   0.1374   1.0000
  10.000   1.0175   0.05929   0.05189   0.0089   0.1339   1.0000
  10.250   1.0317   0.06232   0.05487   0.0100   0.1258   1.0000
  10.500   1.0138   0.06728   0.06016   0.0113   0.1256   1.0000
  10.750   0.9923   0.07229   0.06539   0.0121   0.1259   1.0000
  11.000   0.9705   0.07725   0.07044   0.0126   0.1264   1.0000
  11.250   0.8147   0.10518   0.09806  -0.0103   0.1660   1.0000
  11.500   0.8061   0.11250   0.10536  -0.0133   0.1677   1.0000
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