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MH 46 9.1% (mh46-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 46 9.1% (mh46-il)
Reynolds number: 50,000
Max Cl/Cd: 33.45 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh46-il-50000-n5.txt
Download as CSV file: xf-mh46-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5597   0.08102   0.07450  -0.0181   1.0000   0.0310
  -8.500  -0.5648   0.07594   0.06946  -0.0218   1.0000   0.0307
  -8.250  -0.5723   0.07125   0.06476  -0.0242   1.0000   0.0305
  -8.000  -0.5766   0.06665   0.06008  -0.0263   1.0000   0.0302
  -7.750  -0.5806   0.06177   0.05504  -0.0280   1.0000   0.0301
  -7.500  -0.5809   0.05713   0.05017  -0.0291   1.0000   0.0300
  -7.250  -0.5779   0.05263   0.04536  -0.0296   1.0000   0.0300
  -7.000  -0.5717   0.04827   0.04057  -0.0296   1.0000   0.0302
  -6.750  -0.5614   0.04439   0.03616  -0.0291   1.0000   0.0308
  -6.500  -0.5495   0.04087   0.03237  -0.0285   1.0000   0.0326
  -6.250  -0.5335   0.03834   0.02960  -0.0278   1.0000   0.0349
  -6.000  -0.5158   0.03562   0.02649  -0.0268   1.0000   0.0374
  -5.750  -0.4959   0.03281   0.02320  -0.0256   1.0000   0.0394
  -5.500  -0.4741   0.03031   0.02022  -0.0242   1.0000   0.0418
  -5.250  -0.4545   0.02835   0.01821  -0.0231   1.0000   0.0476
  -5.000  -0.4329   0.02664   0.01612  -0.0217   1.0000   0.0557
  -4.750  -0.4132   0.02506   0.01446  -0.0202   1.0000   0.0676
  -4.500  -0.3946   0.02349   0.01299  -0.0187   1.0000   0.0858
  -4.250  -0.3755   0.02208   0.01170  -0.0174   1.0000   0.1223
  -4.000  -0.3562   0.02070   0.01065  -0.0164   1.0000   0.1835
  -3.750  -0.3394   0.01972   0.01002  -0.0149   1.0000   0.2632
  -3.500  -0.3238   0.01900   0.00957  -0.0130   1.0000   0.3418
  -3.250  -0.3087   0.01840   0.00923  -0.0109   1.0000   0.4173
  -3.000  -0.2937   0.01790   0.00889  -0.0086   1.0000   0.4937
  -2.750  -0.2785   0.01742   0.00866  -0.0061   1.0000   0.5724
  -2.500  -0.2621   0.01698   0.00850  -0.0036   1.0000   0.6616
  -2.250  -0.2224   0.01658   0.00841  -0.0046   0.9964   0.8006
  -2.000  -0.1303   0.01648   0.00799  -0.0160   0.9999   0.9668
  -1.750  -0.0764   0.01657   0.00766  -0.0221   0.9895   1.0000
  -1.500  -0.0326   0.01667   0.00743  -0.0261   0.9742   1.0000
  -1.250   0.0123   0.01676   0.00722  -0.0302   0.9602   1.0000
  -1.000   0.0565   0.01685   0.00708  -0.0339   0.9462   1.0000
  -0.750   0.0979   0.01693   0.00698  -0.0370   0.9314   1.0000
  -0.500   0.1366   0.01703   0.00691  -0.0393   0.9162   1.0000
  -0.250   0.1726   0.01713   0.00688  -0.0410   0.9007   1.0000
   0.000   0.2032   0.01726   0.00691  -0.0416   0.8837   1.0000
   0.250   0.2316   0.01741   0.00697  -0.0416   0.8665   1.0000
   0.500   0.2586   0.01756   0.00704  -0.0412   0.8497   1.0000
   0.750   0.2844   0.01771   0.00712  -0.0405   0.8332   1.0000
   1.000   0.3090   0.01787   0.00722  -0.0396   0.8169   1.0000
   1.250   0.3318   0.01807   0.00737  -0.0383   0.7993   1.0000
   1.500   0.3549   0.01825   0.00754  -0.0371   0.7822   1.0000
   1.750   0.3780   0.01842   0.00769  -0.0357   0.7655   1.0000
   2.000   0.4011   0.01858   0.00782  -0.0343   0.7490   1.0000
   2.250   0.4236   0.01878   0.00802  -0.0330   0.7311   1.0000
   2.500   0.4462   0.01897   0.00822  -0.0316   0.7129   1.0000
   2.750   0.4692   0.01914   0.00845  -0.0302   0.6952   1.0000
   3.000   0.4922   0.01931   0.00864  -0.0288   0.6770   1.0000
   3.250   0.5151   0.01952   0.00890  -0.0275   0.6571   1.0000
   3.500   0.5386   0.01968   0.00908  -0.0261   0.6383   1.0000
   3.750   0.5617   0.01991   0.00942  -0.0249   0.6170   1.0000
   4.000   0.5851   0.02009   0.00963  -0.0235   0.5968   1.0000
   4.250   0.6082   0.02034   0.00996  -0.0222   0.5739   1.0000
   4.500   0.6314   0.02058   0.01025  -0.0209   0.5514   1.0000
   4.750   0.6545   0.02084   0.01061  -0.0196   0.5279   1.0000
   5.000   0.6772   0.02116   0.01101  -0.0183   0.5026   1.0000
   5.250   0.6997   0.02152   0.01143  -0.0170   0.4762   1.0000
   5.500   0.7219   0.02192   0.01189  -0.0157   0.4488   1.0000
   5.750   0.7437   0.02237   0.01239  -0.0144   0.4201   1.0000
   6.000   0.7649   0.02288   0.01301  -0.0131   0.3902   1.0000
   6.250   0.7854   0.02348   0.01365  -0.0118   0.3583   1.0000
   6.500   0.8051   0.02416   0.01437  -0.0104   0.3247   1.0000
   6.750   0.8237   0.02495   0.01514  -0.0091   0.2906   1.0000
   7.000   0.8412   0.02587   0.01606  -0.0077   0.2547   1.0000
   7.250   0.8574   0.02696   0.01710  -0.0064   0.2189   1.0000
   7.500   0.8721   0.02825   0.01831  -0.0050   0.1852   1.0000
   7.750   0.8859   0.02974   0.01970  -0.0036   0.1549   1.0000
   8.000   0.8984   0.03138   0.02129  -0.0022   0.1276   1.0000
   8.250   0.9112   0.03321   0.02324  -0.0007   0.1073   1.0000
   8.500   0.9218   0.03505   0.02501   0.0007   0.0909   1.0000
   8.750   0.9348   0.03708   0.02715   0.0022   0.0792   1.0000
   9.000   0.9484   0.03920   0.02948   0.0037   0.0697   1.0000
   9.250   0.9588   0.04133   0.03172   0.0051   0.0615   1.0000
   9.500   0.9711   0.04369   0.03427   0.0064   0.0559   1.0000
   9.750   0.9842   0.04650   0.03717   0.0077   0.0522   1.0000
  10.000   0.9905   0.04953   0.04070   0.0091   0.0483   1.0000
  10.250   0.9922   0.05212   0.04351   0.0105   0.0447   1.0000
  10.500   0.9933   0.05467   0.04607   0.0118   0.0420   1.0000
  10.750   0.9886   0.05832   0.04998   0.0130   0.0408   1.0000
  11.000   0.9788   0.06223   0.05423   0.0135   0.0403   1.0000
  11.250   0.9654   0.06667   0.05896   0.0130   0.0399   1.0000
  11.500   0.9500   0.07159   0.06412   0.0115   0.0398   1.0000
  11.750   0.9326   0.07722   0.06995   0.0089   0.0399   1.0000
  12.000   0.9146   0.08346   0.07635   0.0054   0.0401   1.0000
  12.250   0.8946   0.09079   0.08381   0.0009   0.0403   1.0000
  12.500   0.8764   0.09850   0.09161  -0.0039   0.0407   1.0000
  12.750   0.8595   0.10663   0.09979  -0.0088   0.0411   1.0000
  13.000   0.8430   0.11538   0.10855  -0.0138   0.0413   1.0000
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